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User's Manual - The Water Rocket Explorer

1. Arianespace January 2006 A2 5 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft A1 1 Spacecraft description and mission summary Manufactured by Model Bus DESTINATION Telecommunication Meteorological Scientific Direct broadcasting Remote sensing Radiolocalisation MASS DIMENSIONS Total mass at launch Stowed for launch Mass of satellite in Deployed on orbit target orbit FINAL ORBIT LIFETIME Zp X Za X inclination w RAAN TBD years PAYLOAD TBD operational channels of TBD bandwith Traveling wave tube amplifiers TBD if used Transmit Frequency range TBD W Receive Frequency range TBD W EIRP TBD ANTENNAS TM TC Antenna direction and location PROPULSION SUB SYSTEM Brief description TBD liquid solid number of thrusters ELECTRICAL POWER Solar array description L x W Beginning of life power TBD W End of life power TBD W Batteries description TBD type capacity ATTITUDE CONTROL Type TBD STABILIZATION Spin 3 axis COVERAGE ZONES OF THE SATELLITE TBD figure Note to be selected A1 2 Arianespace January 2006 Soyuz CSG Manual Application to use Issue Draft Arianespace s launch vehicle A1 2 Mission characteristics A1 2 1 Orbit description Orbit parameters and its dispersions Spacecraft final orbit Separation orbit if different e Perigee altitude km km e Apogee altitude km km e Semi major a
2. Fuel Tank Kerosene Intermediate Bay Avionics Telemetry Reaction Nozzle For deorbitation and 7 PR collision avoidance a reaction nozzle IS positioned on the side of the stage and vents the oxygen tank Helium Tanks 5 Skirt 3 jettisoned parts RD 0110 and RD 0124 engines RD 0110 Engine RD 0124 Engine w vernier thrusters w gimbaled nozzles A5 4 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft A5 1 5 SOYUZ avionics A5 1 5 1 Control System The control system performs the following functions for flight of the first three stages of the Soyuz e Attitude control stabilization e Navigation and guidance and e Vehicle management including health monitoring propellant control and monitoring and delivery of pyrotechnic commands The control system of the Soyuz operated from the CSG is based on a digital computer and four axis gimbaled inertial measurement units IMU communicating through the digital bus with other sub systems and actuators through analog digital converters Most of the front end equipment remains identical to the conventional design ones The navigation parameters comes from the IMU and from GPS GLONASS receivers The control system is unique for the first three stages and is located primarily in the equipment bay of the third stage IMU and digital computer The system uses a triplex architecture with a 2 out of 3 voting logic The IMU and on board comput
3. SOYUZ from the Guiana Space Centre User s Manual Issue Draft January 06 Issued and approved by Arianespace Edouard Perez Senior Vice President Engineering Soyuz CSG User s Manual Issue Draft Preface This Soyuz User s Manual provides essential data on the Soyuz launch system which together with Ariane 5 and Vega constitutes the European Space Transportation union These launch systems are operated by Arianespace from the same spaceport the Guiana Space Centre This document contains the essential data which is necessary To assess compatibility of a spacecraft and spacecraft mission with launch System To constitute the general launch service provisions and specifications To initiate the preparation of all technical and operational documentation related to a launch of any spacecraft on the launch vehicle Inquiries concerning clarification or interpretation of this manual should be directed to the addresses listed below Comments and suggestions on all aspects of this manual are encouraged and appreciated France Headquarters USA U S Subsidiary Arianespace Arianespace Inc Boulevard de l Europe 601 13th Street N W Suite 710 N BP 177 91006 Evry Courcouronnes Cedex France Washington DC 20005 USA Tel 33 1 60 87 60 00 Tel 1 202 628 3936 Fax 33 1 60 87 63 04 Fax 1 202 628 3949 Singapore Asean Office Japan Tokyo Office Arianespace Arianespace Shenton House 25 06 Kas
4. and a mobile servicing gantry used for launch vehicle preparation integration with the upper composite and launch The support arms and launch table servicing equipment are identical to the other Soyuz launch pads used in Baikonur and Plesetsk The mobile servicing gantry is equipped with a ceiling traveling crane for upper composite installation The mobile servicing gantry protect from the outside environment and constitute a protected room for all activity with the upper composite and satellite 3 Stage Soyuz on launch pad po Ee ie MA oec i FFI OO E gappi HH et i ae aa m e c f nn gaa t D Ty s D Payload composite hoisting on l Launch Vehicle Y gt X ih b e 7 6 13 Soyuz Launch Pad and Servicing gantry The ground board electrical connection is performed at the Fregat interstage section by a dedicated umbilical mast The launch tower is equipped with an air conditioning system providing clean air under the fairing 6 14 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft t oT Connection RATS arms HE Br PS L V erected j KD M ANS L V transfer from MIK Supporting arms Fer LT NUTS eo L 1 Encapsulated payload transfer from S3 Figure 6 14 Soyuz Launch Pad Two launch pad Customer s rooms for accommodation of Customers check out terminal equipment COTE are located
5. e The readiness of the CSG facilities and information on the LV preparation e The readiness of the Spacecraft e The mass of the payload in its final launch configuration 7 5 4 7 Transfer readiness review TRR A Transfer Readiness Review is held before the transportation of the fully integrated Upper composite to the launch pad usually 5 days before launch The purpose of the review is to authorize the transfer of the Upper Composite and LV stages to the launch pad and to authorize their integration and final launch preparation The review is intended to provide a detailed presentation on the status of the mission It can serve as a preliminary Launch Readiness Review providing more specific and detailed presentation on the mission aspects The review covers e The mission system aspects launch date windows and mission analysis conclusion e A synthesis of the previous launch campaign operations with the Upper Composite and the LV and any non conformities and waivers encountered e the readiness of the launch pad facilities and associated services e the status of the launch vehicle stages preparation e An overview and organizational description of the launch pad activities 7 5 4 8 Launch readiness review LRR or RAL Revue d Aptitude au Lancement A Launch Readiness Review is held one day before launch and after the launch rehearsal It authorizes the filling of the LV stages and the pursuit of the final countdown and
6. 2 x 10 Pa Frequency Hz 63 12 25 50 1000 Note OASPL Overall Acoustic Sound Pressure Level LEE MN 12 4 5 2 4 6 4 5 1 1 This maximum environment is applied during a period of approximately 60 seconds 15 seconds for lift off and 45 seconds for atmospheric flight Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft 3 2 5 Shocks The spacecraft is subject to shock primarily during stage separations fairing jettisoning and actual spacecraft separation The envelope acceleration shock response spectrum SRS at the spacecraft base computed with a Q factor of 10 is presented in Table 3 4 Table 3 5 and Figure 3 12 These levels are applied simultaneously in axial and radial directions For customers wishing to use their own adapter the acceptable envelope at the launch vehicle interface will be provided on a peculiar base Arianespace January 2006 3 5 Environmental conditions Soyuz CSG User s Manual Issue Draft Table 3 4 Shock Response Spectra at Stage Separations and Fairing Jettisoning Frequency Hz 100 1000 1000 5000 Flight Event SRS Shock Response Spectra Q 10 9 Fairing separation upper stage separation Table 3 5 Shock Response Spectra for off the shelf Clampband Separation Systems Spacecraft Band Frequency Hz me Tengen 200 sa was 1800 2000 50 sms mur Diameter SRS Shock Response Spectra Q 10
7. I j i i 16 CSG dedicated technical room i I i Ground floor Upper floor CSG dedicated technical room Figure 6 9 Layout of Hazardous and Upper Composite Integration Facilities at S3 area S3A and S3B Arianespace January 2006 6 9 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 2 2 3 55 Payload Processing amp Hazardous Facility The S5 Payload amp Hazardous Processing Facility consists of a few clean rooms fueling rooms and offices connected by environmentally protected corridors It is safely located on the south west bank of the main CSG road far from launch pads and other industrial sites providing all the year round access EPCU S5 enables an entire autonomous preparation from satellite arrival to fuelling taking place on a single site The building configuration allows for up to 4 spacecraft preparations simultaneously including fueling and in the same time provides easy short and safe transfers between halls S5C 3e 29 17 99 S5D Processing aera Fueling a ra Decontamination building n o _ Faeling preparation TiN FI Figure 6 10 PPF HPF S5 area overview 6 10 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft The main facility is composed of 3 areas equipped by airlocks and connected by two access corridors the S5C area dedicated to the spacecraft non hazardous processing and to the launch team housing is ma
8. g 8S9 3163 35 2000 2000 2000 2000 2000 lt 937 27 7 20 3200 4147 4550 4550 type B 700 88 5000 5000 5000 soo 3500 5500 ELE TO BE ISSUED LATER Figure 3 2 Envelope acceleration shock response spectrum SRS at the spacecraft base 3 6 Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft 3 2 6 Static pressure under the fairing 3 2 6 1 On Ground After encapsulation the air velocity around the spacecraft due to the ventilation system is lower than 5 m sec value experienced in front of the air inlet The velocity may locally exceed this value contact Arianespace for specific concern 3 2 6 2 In Flight The payload compartment is vented during the ascent phase through one way vent doors insuring a low depressurization rate of the fairing compartment The static pressure evolution under the fairing is shown in Figure 3 3 The depressurization rate does not exceed 2 0 kPa s 20 mbar s for a sustained length of time Locally at the time of maximum dynamic pressure at 50s there is a short period of about 2 seconds when the depressurization rate can reach 3 5 kPa s 35 mbar s The difference between the pressure under fairing and free stream external static pressures at the moment of the fairing jettisoning is lower than 0 2 kPa 2 mbar Pressure variation under fairing mm ou x d ad
9. 1631 1632 1633 1634 1635 1636 1637 1638 1639 1640 1641 1642 1643 1644 1645 1646 1647 1648 1649 1650 1651 1652 1653 1654 1655 1656 1657 1658 1659 1660 1661 1662 1663 1664 198 199 800 801 802 803 804 805 806 807 808 809 810 811 812 813 814 815 816 817 818 819 820 821 822 823 824 825 826 827 828 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft November 26 2001 February 25 2002 March 21 2002 April 1 2002 April 25 2002 June 26 2002 September 25 2002 October 15 2002 October 30 2002 December 24 2002 February 02 2003 April 02 2003 April 26 2003 June 02 2003 June 08 2003 June 19 2003 August 12 2003 August 29 2003 October 18 2003 December 27 2003 January 29 2004 February 18 2004 April 19 2004 May 25 2004 August 11 2004 September 24 2004 October 14 2004 November 8 2004 December 24 2004 Baikonur Plesetsk Baikonur Plesetsk Baikonur Baikonur Baikonur Plesetsk Baikonur Plesetsk Baikonur Plesetsk Baikonur Baikonur Baikonur Plesetsk Baikonur Baikonur Baikonur Baikonur Baikonur Plesetsk Baikonur Baikonur Baikonur Baikonur Baikonur Plesetsk Baikonur Arianespace January 2006 M Soyuz FG Soyuz U Soyuz U Molniya M Soyuz U Soyuz U Soyuz FG Soyuz U Soyuz FG Molniya
10. Acceptance tests and hazardous operations Before campaign The submission of the final description of operational preparation visit or procedures involving the Spacecraft and GSE hazardous L 6m systems as well as the results of their acceptance tests if any Approval of the Spacecraft compliance with CSG Safety Before S C consent Regulation and approbation of the procedures for to fuel meeting autonomous and combined operations Note e Shorter submission process can be implemented in case of recurrent Spacecraft having already demonstrated its compliance with the CSG safety Regulations Arianespace January 2006 7 29 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 6 4 Safety measures during hazardous operations 7 30 The Spacecraft Authority is responsible for all Spacecraft and associated ground equipment operations The CSG safety department representatives monitor and coordinate these operations for all that concerns the safety of the staff and facilities Any activity involving a potential source of danger is to be reported to the CSG safety department representative which in return takes all steps necessary to provide and operate adequate collective protection and to activate the emergency facilities Each member of the Spacecraft team must comply with the safety rules regarding personal protection equipment and personal activity The CSG safety department representative permanen
11. DDO COEL Range Operations sy CM Launch Pad DULL ed Mission Director Cperations Manager RCUA l ROW A Program Director 1 Program Director 2 EE ACU RSG ee CSG Services Pavioad p Launch Safety Responsible H suite Team Y Arianespace management Figure 7 2 Launch campaign organization in case of dual launch Arianespace January 2006 7 15 Soyuz CSG User s Manual Mission integration and Issue Draft management Table 7 1 The post designations and responsibilities The Customer Representatives DMS Responsible for Spacecraft Spacecraft Mission preparation to launch and Director Directeur de Spacecraft launch campaign la Mission Satellite DMS reports S C and S C ground network readiness during final countdown DMS provides confirmation of the Spacecraft acquisition after separation The Spacecraft Manufacturers Representatives CPS The CPS managed the S C RPS Responsible for the Spacecraft Project preparation team Usually he Spacecraft preparation activation and Manager is representative of the S C Preparation checkout of the Spacecraft Chef de Projet Satellite manufacturer Manager Provides final S C status to Responsable de la DMS during countdown Pr paration ARS Responsible of Satellite Satellite Satellite Ground Orbital Operations Centre Stations Network Provides the final Satellite Assistant Network readiness to DMS Adjoint Reseau Stations during countdown sol sat
12. January 2006 A4 5 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft ACTUATORS RELEASED SEP PLANE microswitch SP4543 Two places NO MLI ON SPACECRAFT FRAME FACING MICROSWITCHES Figure A4 1 4 Adapter 937 SF Actuators and microswitches A4 6 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters 1219 Spacecraft connector 10 3 Two places Connector keyway 940 Max allowable volume for screw head Limit of allowable S C usable volume Lu 62 56 37 pins 64 51 61 pins SEPARATION PLANE 10 7 37 pins 12 65 61 pins br Connector keyway Adaptor connector in free position Two places ZT 0 2 91 86 20 3 Gn omm GERS ee wm mb jeje ue uu NE NE dae Figure A4 1 5 Adapter 937 SF Umbilical connectors A4 7 Arianespace January 2006 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft TO BE ISSUED LATER Figure A4 1 6 Adapter 937 SF Usable volume A4 8 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters A4 2 Adapter 1194 SF The adapter 1194 SF was developed by EADS Launch Vehicles within the framework of the Cluster Il launch services program and is currently flight proven on the Soyuz LV three successful flights were performed in 2000 The adapter is an aluminium monolithic struc
13. Performance and launch mission Issue Draft LV Performance kg a R e e 1400 Apogee Altitude km 12000 14000 16000 18000 20000 22000 24000 26000 28000 Apogee Altitude km 0 2000 4000 6000 8000 10000 Figure 2 10 LV performance data for elliptical orbit with 51 8 deg inclination and a perigee altitude of 200 km for apogee up to 25 000 km TO BE ISSUED LATER Figure 2 11 LV performance data for elliptical orbit with 51 8 deg inclination and a perigee altitude of 200 km for apogee up to 400 000 km 2 15 Arianespace January 2006 Performance and launch mission Soyuz CSG User s Manual Issue Draft 2 4 4 Earth escape missions The performance data for earth escape missions is presented in Figure 2 12 as a function of the parameter C square of velocity at infinity For more accurate data users should contact Arianespace for a performance estimate and a mission adapted profile 1700 1600 1500 1400 1300 1200 1100 1000 900 800 700 600 500 400 300 LV Performance kg 0 2 4 6 8 10 12 14 16 18 20 22 24 26 28 30 32 34 36 38 40 42 44 46 C 3 km s transition between sub orbital and direct injection profile curves is simplified Figure 2 12 preliminary LV performance data for escape missions TBC For
14. Qjo3 Q9 1 B 0 2 456 7 0 5 BOLTED INTERFACE 2000 8 holes 18 T 2044 t 0 2 FREGAT INTERFACE PLANE 8 ACTUATORS LOCATION 45 APART ON 21585 OVERHEAD VIEW 7 2 UMBILICAL CONNECTORS 180 APART ON 1885 Figure A4 4 2 Adapter 1666 SF General view A4 18 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters TO BE ISSUED LATER Figure A4 2 3 Adapter 1666 SF Interface frames Arianespace January 2006 A4 19 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft NO MLI ON SPACECRAFT FRAME FACING ACTUATORS AND MICROSWITCHES ACTUATORS 66 3 1 Nominal Stroke 15 3 0 6 NN Y SEPARATION PLANE RELEASED microswitch SP4543 Two places S C e F re e Asis o ___ SEPARATION PLANE af SSS SS CAES Ti Figure A4 4 4 Adapter 1666 SF Actuators and microswitches A4 20 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters Spacecraft connector Q 1885 Two places Limit of local allowable wD a S C usable volume amp 0 3 4 56 hs x m E Pe M s ADS cu 103 S C j ez o aN gt i 2d mL lem sud as SK SEP PLANE ke Max 6 Connector 1666 Max allowable volume li 1666 for screw head keyway z N SEP PLANE 0 oct S JE N eo MER n E Adjustable 1885 Connector ke
15. Simultaneously operating thrusters are located p A angle corresponding to the operation of the thrusters located in the I III plane and o B angle corresponding to the operation of the thrusters located in the II IV plane Jet direction Hanipae 6bIXIIOI 1a Pb PETAT Figure 3 7 Heat flow distribution along the spacecraft bottom surface Arianespace January 2006 3 13 Environmental conditions Soyuz CSG User s Manual Issue Draft 3 4 Cleanliness and contamination 3 4 1 Cleanliness The following standard practices ensure that spacecraft cleanliness conditions are met e A clean environment is provided during production test and delivery of all upper composite components upper stage interstage section fairing and adapter to prevent contamination and accumulation of dust The LV materials are selected not to generate significant organic deposit during all ground phases of the launch preparation e All spacecraft operations are carried out in EPCU buildings PPF HPF and UCIF in controlled Class 100 000 clean rooms During transfer between buildings the Spacecraft is transported in payload containers CCU with the cleanliness Class 100 000 All handling equipment is clean room compatible and it is cleaned and inspected before its entry in the facilities e Prior to the encapsulation of the spacecraft the cleanliness of the upper stages and fairing are verified based on the Visibly Clean Level 2 cr
16. Soyuz CSG User s Manual Issue Draft SPACECRAFT INTERFACES Chapter 5 5 1 Introduction The Soyuz launch vehicle provides standard interfaces that fit most of spacecraft buses and satellites and allows an easy switch between the launch vehicles of the European Transportation Fleet This chapter covers the definition of the spacecraft interfaces with the payload adapter the fairing the dual launch structure and the on board and ground electrical equipment The spacecraft is mated to the LV through a dedicated structure called an adapter that provides mechanical interface electrical harnesses routing and systems to assure the Spacecraft separation Off the shelf adapters with separation interface diameter of 937 mm 1194 mm and 1666 mm are available For dual launches an internal carrying structure can be proposed that houses the lower passenger and carries the upper passenger The payload fairing protects the spacecraft from external environment during the flight as on the ground providing at the same time specific access to the spacecraft during ground operations The electrical interface provides communication with the launch vehicle and the ground Support equipment during all phases of spacecraft preparation launch and flight The adapters dispensers and fairings accommodate also the telemetry sensors that are used to monitor the spacecraft flight environment These elements could be subject of mission specific adaptatio
17. The dates are given in months relative to contract kick off meeting or relative to L where L is the first day of the latest agreed Launch period Slot or approved launch day as applicable A2 2 Arianespace issued documentation A QONGA 10 11 A2 2 Mission Integration Schedule Interface Control Document DCI Issue 0 Issue 1 Issue 2 Preliminary Mission Analysis Documents Final Mission Analysis Documents Interleaved Operations Plan POI Range Operations Document DL Combined Operations Plan POC Countdown sequence Safety Statements Phase 1 reply Phase 2 reply Phase 3 reply Injection Data Launch Evaluation Report DEL Contract kick off L 24 L 20 L 13 L 2 L 16 ESS L 3 L 3 L 7 weeks L 2 weeks L 17 3 months after each submission L 2 60 minutes after separation Approval Approval Approval Approval Review Review Review For information Approval Review Review Review Review For information For information After RAMP After RAMF 2 weeks before RAMP 2 weeks before RAMF At RAMF At RAMP 1 5 months after Launch or 1 month after receipt of the orbital tracking report from the Customer whichever is later Arianespace January 2006 Soyuz CSG User s Manual Review and documentation Issue Draft checklist A2 3 Customer issued documentation 1 Application to Use Soyuz L 24 Review At contract Safety Submission Phase 1
18. s Manual Mission integration and Issue Draft management 7 5 4 Launch campaign meetings and reviews 7 5 4 1 1 ntroduction The launch preparation is carried out in permanent interaction between the Customer and the LV team The planning of activity critical points and needs are discussed at daily briefings giving the Customer access to in time support and total transparency of the operations A few more formalized meetings and reviews takes place at major milestones of the operational process 7 5 4 2 Spacecraft preshipment review Arianespace wishes to be invited to the preshipment or equivalent review organized by the customer and held before shipment of the Spacecraft to the CSG Besides Spacecraft readiness this review may address the CSG and launch vehicle readiness status that will be presented by Arianespace 7 5 4 3 Satellite transport meeting Arianespace will hold a preparation meeting with the customer at the CSG before satellite transportation The readiness of the facilities at entrance port and at CSG for satellite arrival as well as status of formal issues and transportation needs will be verified 7 5 4 4 EPCU acceptance review The EPCU Acceptance Review is conducted at the CSG at the beginning of the launch campaign It addresses the following main points e The readiness of the CSG facilities to support all planned satellite autonomous activities and particularly the specific customer requests communicati
19. 1 0 0 3 max E 7 p perem slum ARS Ims 1 0 0 3 max o 7 rmm es and third stages 0 2 LI max 41 3 erem po ser a s flight max 40 3 mpm zr 5 max 41 5 e The factors apply on payload CoG e The minus signs indicate compression along the longitudinal axis and the plus Signs tension e Lateral loads may act in any direction simultaneously with longitudinal loads e The gravity load is included e For the structural design additional safety coefficients shall be applied as defined in paragraph 4 3 2 4 4 Arianespace January 2006 Soyuz CSG User s Manual Design And Verification Requirements Issue Draft 4 2 4 2 Line loads peaking The geometrical discontinuities and differences in the local stiffness of the LV stiffener holes stringers and the non uniform transmission of the LV s thrust at the spacecraft adapter interface may produce local variations of the uniform line loads distribution Line loads peaking induced by the Launch Vehicle The integral of these variations along the circumference is zero and the line loads derived from the QSL are not affected but for the correct dimensioning of the lower part of the spacecraft this excess shall be taken into account and has to be added uniformly at the S C adapter interface to the mechanical fluxes obtained for the various flight events Such local over line loads are specific of the adapter design For off the shell adapters a value of 15 over the line
20. 5 Final Thermal Analysis The final thermal analysis takes into account the final thermal model provided by the Customer For ground operations it provides a time history of the temperature at nodes selected by the Customer in function of the parameters of air ventilation around the Spacecraft During flight and after fairing jettisoning it provides a time history of the temperature at critical nodes taking into account the real attitudes of the LV during the entire launch phase The study allows Arianespace to adjust the ventilation parameters during operations with the upper composite and up to the launch in order to satisfy in so far as the system allows it the temperature limitations specified for the Spacecraft 7 4 3 Spacecraft Design Compatibility Verification 7 10 In close relationship with mission analysis Arianespace will Support the Customer in demonstrating that the Spacecraft design is able to withstand the LV environment For this purpose the following reports will be required for review and approval e A Spacecraft environment test plan correlated with requirements described in Chapter 4 Customer shall describe their approach to qualification and acceptance tests This plan is intended to outline the Customer s overall test philosophy along with an overview of the system level environmental testing that will be performed to demonstrate the adequacy of the Spacecraft for ground and flight loads e g static loads vibrat
21. Connector for screw head 10 keyway 10 7 37 pins 12 65 61 pins SEP PLANE 1194SF i Connector SEP PLANE 0 7 Adaptor connector in free position Two places 1194SF Figure A4 2 5 Adapter 1194 SF Umbilical connectors Arianespace January 2006 A4 14 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters TO BE ISSUED LATER Figure A4 2 6 Adapter 1194 SF Usable volume Arianespace January 2006 A4 15 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft A4 3 Adapter 1666 SF The adapter 1666 SF is an aluminium monolithic structure that takes the form of a truncated cone with a diameter of 1666 mm at the level of the spacecraft separation plane see TBD The adapter 1666 SF is equipped with an EADS CASA 1666 separation The spacecraft installed on top of the adapter is secured by a clamp band consisting of an iron strip that holds in place a series of clamps hooked onto the spacecraft and adapter interfacing frames see Figure TBD At separation the band is severed in two places by a bolt cutter mounted on the adapter with all pieces remaining captive to the adapter The Spacecraft is then forced away from the launcher by 8 spring actuators that are also part of the adapter and that bear on the spacecraft rear frame see TBD In this way the relative velocity between the spacecraft and the launcher can be adjusted to mission requirements Once the clamp band
22. Fregat burns are performed to transfer the payload to a wide variety of final orbits providing the required plane changes and orbit raising In this case the Fregat ACS thrusters are operated 5 seconds after separation from the third stage followed 55 seconds later with the ignition of the main Fregat engine Fregat burns are then performed to transfer the payload as described above Direct injection profile a single Fregat burn injects the payload to the final orbit Up to 20 burns may be provided by the Fregat to reach the final orbit or to deliver the payload to the different orbits Soyuz St Fregat 150 5 Dad mme 100 50 0 latitude degree longitude degree Figure 2 4 Example of Fregat upper stage mission profile SSO orbit 2 6 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 3 3 Fregat deorbitation or orbit disposal manoeuvre After spacecraft separation and following the time delay needed to provide a safe distance between the Fregat upper stage and the spacecraft the Fregat typically conducts a deorbitation or orbit disposal manoeuvre This manoeuvre is carried out by an additional burn of the Fregat s ACS thrusters or in some cases by the main engine Parameters of the safe orbit or entry into the earth s atmosphere will be chosen in accordance with international laws pertaining to space debris and will be coordinated with the user during mission analys
23. LV preparation Figure 1 4 shows the launch vehicle procurement organization To illustrate the industrial experience concentrated behind the Soyuz prime supplier the Figure 1 5 shows second level subcontractors and their responsibilities Qualification Authority ARSENI Tire SOFU Company ARIANE STARSEM Figure 1 4 The launch vehicle procurement organization Arianespace January 2006 1 13 Introduction Soyuz CSG User s Manual Issue Draft 1 6 4 Main suppliers 1 6 4 1 Russian Federal Space Agency The Agency FSA represents the Russian federal executive authority that defines the Russian Federation s national policy in the field of space research and exploration The agency also performs interdisciplinary coordination of national scientific and application space programs It was created in February 1992 by a decree issued by the President of the Russian Federation FSA s responsibilities include development and implementation of Russian national space policy acting as governmental customer in the development of scientific and application Space systems facilities and equipment establishing international cooperation and collaboration in space research and organization coordination of commercial space programs Operations under FSA responsibility include more than 400 aeronautic and space companies and organizations 1 6 4 2 The Samara Space Centre TsSKB Progress The Samara S
24. M Soyuz U Molniya M Soyuz FG Soyuz FG Soyuz U Molniya M Soyuz U Soyuz U Soyuz FG Soyuz FG Fregat Soyuz FG Molniya M Soyuz FG Soyuz U Soyuz U Soyuz U Soyuz FG Soyuz 2 1a Soyuz U Unmanned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Progress M1 7 Kosmos 2387 Progress M1 8 Kosmos 2388 Soyuz TM 34 Progress M 46 Progress M1 9 Photon M N1 Soyuz TMA 1 Kosmos 2393 Progress M47 Molnia 1T Soyuz TMA 2 Mars Express Progress M1 10 Molnia 3 Cosmos 2399 Progress M48 Soyuz TMA 3 AMOS 2 Progress M1 11 Molniya 1 93 Soyuz TMA 4 Progress M 49 Progress M 50 Cosmos 2410 Soyuz TMA 5 Test payload Oblick Progress M 51 X XIX X X x gt lt X X X KKK KK X X XX X X X X X X X X X 1665 1666 1667 1668 1669 1670 1671 1672 1673 1674 1675 1676 1677 1678 1679 1680 1681 1682 1683 1684 1685 1686 1687 1688 1689 1690 1691 1692 1693 829 830 831 832 833 834 835 836 837 838 839 840 841 842 843 844 845 846 847 848 849 850 851 852 A5 17 February 28 2005 Baikonur SoyuzU Unmanned Progress M 52 X 1694 8
25. Presentation QSP included in the agenda of the contractual Kick off Meeting This presentation explicitly reviews the Product Assurance provisions defined in the ARIANESPACE Quality Manual e A Quality System Meeting QSM suggested about 10 12 months before the Launch where the latest LV production Quality Statement is reviewed with special emphasis on major Quality and Reliability aspects relevant to Customer s LV or LV batch It can be accompanied by visits to main contractor facilities e A dedicated Quality Status Review QSR which can be organized about 3 4 months before launch to review the detailed quality log of Customer s Launch Vehicle hardware Arianespace January 2006 Soyuz CSG User s Manual Issue Draft APPLI CATI ON TO USE ARI ANESPACE S LAUNCH VEHICLE DUA Annex 1 The Customer will preferably provide the DUA as an electronic file according to the Arianespace template Arianespace January 2006 A1 1 Soyuz CSG User s Manual Issue Draft REVIEW AND DOCUMENTATION CHECKLIST Annex 2 Arianespace January 2006 A2 1 Review and documentation checklist A2 1 I ntroduction The presented annex contents of the typical documentation and meetings checklist that can be used as a base during contract preparation The delivery date can be modified according to the Customer s mission schedule availability of the input data and satellite s production planning Soyuz CSG User s Manual Issue Draft
26. REDUNDANT Command to put two 3 3 Wresistors in parallel to adapt the line resistance value Figure 5 6 Pyrotechnic order Electrical diagram Arianespace January 2006 5 17 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft 5 5 3 Electrical Continuity I nterface 5 5 3 1 Bonding The spacecraft is required to have an Earth reference point close to the separation plane on which a test socket can be mounted The resistance between any metallic element of the spacecraft and a closest reference point on the structure shall be less than 10 mQ for a current of 10 mA The spacecraft structure in contact with the LV separation plane of the spacecraft rear frame or mating surface of a Customer s adapter shall not have any treatment or protective process applied which creates a resistance greater than 10 mQ for a current of 10 mA between spacecraft earth reference point and that of the LV adapter or upper stage 5 5 3 2 Shielding The umbilical shield links are grounded at both ends of the lines the spacecraft on one side and EGSE on the other If the Customer desires it is also possible to connect to ground at the umbilical mast connector SHO1 and the last instant connectors R15 The Spacecraft umbilical grounding network diagram is shown in Figure 5 7 For each LV and ground harnesses connector two pins are reserved to ensure continuity of the shielding 5 5 4 RF communication link between spacecra
27. Separation 20 s v w v v YES Command Spacecraft YES Sequencer To L V orders NO waiver possible Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft 5 5 1 Spacecraft to EGSE umbilical lines 5 5 1 1 Lines definition Between the base of the payload adapter and the umbilical mast junction box 92 wires are available for the payload up to 2 min and 35 seconds before lift off and 14 wires up to lift off e he 92 umbilical lines pass through the umbilical connector SHO1 located on the inter stage section of the Fregat In case of launch abort after HO 2min 35 seconds these lines will be re connected in about 2 hours TBC e The 14 umbilical lines pass through a last instant connector R15 located at the base of the first stage and jettisoned at lift off These lines can be assigned to the function related to the spacecraft switch OFF ON power command and telemetry status which permits the safety configuration to be restored immediately in the event of a launch abort 5 5 1 2 Lines composition The spacecraft to launch pad rooms LP room wiring consists of permanent and customized sections The permanent sections have the same configuration for each launch and consist of the following segments e hose between the LP room connectors C1 C2 C3 and C4 and the umbilical connector SHO1 at the top of the mast This segment is 110 TBC meters long e Those betwe
28. T 0 10 0 39 2 1978 59 0 5 0 9 0 45 0 1979 62 2 8 0 7 0 47 2 1980 64 1 T 1 12 0 45 0 1981 62 1 6 0 14 0 42 1 1982 61 2 5 0 11 0 45 2 1983 58 1 4 0 11 0 43 1 1984 55 0 11 0 44 0 1985 57 0 1 0 16 0 40 0 1986 51 1 14 0 37 1 1987 48 1 4 0 44 1 1988 58 3 2 0 11 0 45 3 1989 44 0 6 0 38 0 1990 44 2 12 0 32 2 1991 30 0 1 0 5 0 24 0 1992 32 0 8 0 24 0 1993 29 0 8 0 17 0 1994 18 0 3 0 15 0 1995 16 0 4 0 12 0 1996 12 2 3 0 9 2 1997 13 0 3 0 10 0 1998 11 0 3 0 8 0 1999 14 0 2 0 12 0 2000 13 0 13 0 2001 11 0 2 0 9 0 2002 9 1 2 0 7 1 2003 10 0 2 0 8 0 2004 9 0 1 0 8 0 2005 5 1 1 1 4 0 Totals 1698 75 30 10 195 17 316 13 301 14 856 22 A5 14 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft A5 2 3 Detailed Launch Record 1996 2003 Since Soyuz entry to the commercial market in 1996 there has been TBD successful launches within TBDlaunch attempts Table A5 2 shows a detailed log of all launches since 1996 Table A5 2 Record of Soyuz R 7 Launch Vehicle Family 1996 2003 February 21 1996 Baikonur SoyuzU Manned Soyuz TM 23 X 1592 769 March 14 1996 Plesetsk SoyuzU Unmanned Kosmos 2331 X 1593 770 May 5 1996 Baikonur SoyuzU Unmanned Progress M 31 X 1594 771 May 14 1996 Baikonur SoyuzU Unmanned Kosmos 1595 172 June 20 1996 Plesetsk SoyuzU Unmanned Yantar 4K2 1596 113 July 31 1996 Baikonur SoyuzU Unmanned Progress M 32 X 1597 1714 August 15 1996 Plesetsk Molniya Unmanned Molniya 1T X 1598 August 17 1996 Baik
29. and an aluminium honeycomb core The upper and lover rings are made of aluminium alloys 5 8 Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft 5 5 Electrical and radio electrical interfaces The needs of communication with the spacecraft during the launch preparation and the flight require electrical and RF links between the spacecraft LV and the EGSE located at the launch pad and preparation facilities The electrical interface composition between spacecraft and the Soyuz LV is presented in the Table 5 2 The wiring diagram for the launch pad configuration is shown on Figure D All other data and communication network used for spacecraft preparation in the CSG facilities are described in Chapter 6 Table 5 2 Spacecraft to launch vehicle electrical and RF interfaces E a ue s S Standard Spacecraft TC TM Umbilical TE 14 lines see 5 5 1 Standard raed data transmission Standard and battery charge Additional lines Optional see 5 5 1 4 ETT GT 2 x 61 pin Separation see 5 5 2 1 Standard p monitoring DBAS 70 37 OSN Dry Dry loop commands commands see 5 5 2 2 Optional TBD os see 5 5 2 3 e DBAS 70 37 OSY LV commands p TBD electrical Spacecraft TM see 5 5 2 4 E retransmission Or spacecraft Bussi 39 9 2 9 Optional supply during flight Pyrotechnic see 5 5 2 only 2 x 12 pin commane Optional DBAS 70 12 OSN RF transparent RF l
30. and mated with the launch vehicle After mating of the payload on the launch vehicle the ventilation and electric umbilical are connected to the upper composite 7 5 5 5 3 Launch preparation activities Launch preparation activity is held usually during 4 days including launch day The respective procedures requirements and constraints are described in the Combined Operations Plan and associated documents Typical launch pad activities are described as following Four days before the launch e LV 3 stages transfer from Integration building to the launch pad and erection into the vertical position e LV 3 stages connection to the launch pad umbilical ventilation filling pipes etc e Upper Composite transfer from UCIF to the launch pad e Upper Composite mating on the 3 rd stage and umbilical connection and e Electrical line verification Three days before the launch e Three stage LV countdown rehearsal e Fregat preparation and verification e Activation of LV and Fregat TM systems for full RF compatibility verification e Spacecraft autonomous preparation and e Upper composite launch countdown rehearsal Second day before the launch e Other Spacecraft activities if needed e LV filling preparation Launch day countdown chronology e LV preparation for launch e LV propellant filling operations and e Final launch countdown Arianespace January 2006 7 25 Soyuz CSG User s Manual Issue Draft The
31. and recurrent manufacture of this type of structure Such experience would obviously be of benefit to other satellite constellation programs as most of the principles involved especially those related to the handling and separation system are valid for any application The Globalstar GLS dispenser was developed by EADS within the framework of the Globalstar launch services agreement and was successfully flown six times on the Soyuz Ikar launch vehicle in 1999 It is an aluminum structure capable of handling four 450 kg satellites and of providing these satellites with the required separation impulse once in orbit It consists of the following see Figure TBD A conical part that interfaces with the Ikar upper frame A cylindrical part that interfaces with three of the four spacecraft and e A top plate that interfaces with the fourth spacecraft Each spacecraft had four contact points with the dispenser These points are located at the corners of a 598 mm x 1650 mm rectangle The separation subsystem thus consisted of four assemblies each comprising four pyro bolts four spring actuators and two microswitches The release shock spectrum at the spacecraft adapter interface is indicated in Figure TBD The Globalstar dispenser was equipped with a set of sensors that are designed to monitor the spacecraft mechanical environment thereby enabling users to verify the compliance of acoustic pressure QSLs and sine and random vibration
32. and symbols with their definition A1 14 simulator etc Arianespace January 2006 Soyuz CSG Manual Application to use Issue Draft Arianespace s launch vehicle A1 8 Contents of Safety Submission Phases 1 and 2 The Customer prepares a file containing all the documents necessary to inform CSG of his plans with respect to hazardous systems This file contains a description of the hazardous systems It responds to all questions on the hazardous items check list given in the document CSG Safety Regulations and summarized here below O Documentation O General comments Miscellaneous Solid propellant rocket motor Igniter assembly S amp A device Initiation command and control circuits propellants cryogenics Transport handling devices structure Ionizing systems flight sources Ionizing systems ground sources Arianespace January 2006 A1 15 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft A1 9 Contents of Spacecraft Operations Plan POS The Customer defines the operations to be executed on the spacecraft from arrival at the CSG at the launch site and up to the launch A typical content is presented here below A1 16 1 General 1 1 Introduction 1 2 Applicable documents 2 Management 2 1 Time schedule with technical constraints 3 Personnel 3 1 Organizational chart for spacecraft operation team in campaign 3 2 Spacecraft organizational cha
33. block diagram showing line functions on the spacecraft side and the EGSE side e data link requirements on ground baseband and data network between spacecraft and EGSE e adescription of additional links used after spacecraft mating on the L V for the test or ground operation e the location of the spacecraft ground potential reference on the spacecraft interface frame e electrical link requirements data power etc during flight between the L V and spacecraft A1 10 Arianespace January 2006 Soyuz CSG Manual Issue Draft A1 3 8 Radioelectrical interfaces Application to use Arianespace s launch vehicle A1 3 8 1 Radio link requirements for ground operations Provide the radio link requirements and descriptions between spacecraft launch site spacecraft check out system and PPF and HPF including re rad Include transmit and receive points location of antenna e to be considered for radio links during launch preparation as well as antenna e pattern A1 3 8 2 Spacecraft transmit and receive systems Provide a description of spacecraft payload telecommunications systems for information only Provide a description of spacecraft telemetry and telecommand housekeeping systems For each TM and TC system used on the ground and during launch give the following Source unit description S1 Carrier Frequency Fo MHz Bandwidth centered 3 dB Around Fg 60 dB Carrier Type Modulation Index Max EIRP transmit
34. can provide specific items of protection for members of the spacecraft team During hazardous operations a specific safety organization is activated officers equipment fire brigade etc Any activity involving a potential source of danger is to be reported to CSG which in return takes all steps necessary to provide and operate adequate collective protection equipment and to activate the emergency facilities The spacecraft design and spacecraft operations compatibility with CSG safety rules is verified according with mission procedure described in the Chapter 7 6 4 4 Training Course In order to use the CSG facility in a safe way Arianespace will provide general training courses for Customer team In addition the training courses for program specific needs e g Safety propellant team crane and handling equipment operations and communication means will be given to appointed operators 6 4 5 Customer assistance 6 4 5 1 Visas and Access Authorization For entry to French Guyana the Customer will be required to obtain entry visas according to the French rules Arianespace may provide support to address special requests to the French administration as needed The access badges to the CSG facility will be provided by Arianespace according to the Customer request 6 4 5 2 Customs Clearance The satellites and associated equipment are imported into French Guiana on a temporary basis with exemption of duties By addressi
35. core The adapter 937 SF is equipped with a CASA 937B separation system a standard Ariane device The release shock spectrum at the spacecraft adapter interface is indicated in Figure TBD The spacecraft is separated from the launch vehicle by 4 to 8 spring actuators that are also part of the adapter and that bear on the spacecraft rear frame see Figure TBD In this way the relative velocity between the spacecraft and the launch vehicle can be adjusted to mission requirements Each actuator applies a force up to 1200 N on the spacecraft rear frame with a 24 N tolerance Note that the clamp band tension does not exceed 27 700 N at any time including dispersions due to temperature variations on ground and in flight This ensures no gapping or sliding between the spacecraft and adapter interfacing frames during all phases of the mission The angular positioning of the spacecraft with respect to the adapter is ensured by the alignment of engraved marks on the interfacing frames at a specified location to be agreed with the user The adapter 937 SF is equipped with a set of sensors that are designed to monitor the spacecraft environment The adapter 937 SF also holds the electrical harness that is necessary for umbilical links as well as for separation orders and telemetry data transmission This harness will be tailored to user needs with its design depending on the required links between the spacecraft and the launch vehicle see Section T
36. current of up to 10 A by wires The LV on board harnesses shall not carry permanent currents in excess of 4 A by wire The voltage shall be less than 125 Vdc The end to end resistance of these umbilical links is less than 1 2 between the satellite and its Check Out Terminal Equipment in LP room and insulation is more than 5 MQ under 500 Vdc No current shall circulate in the shielding It is supposed that the spacecraft wiring insulation is less than 10 MQ under 50 Vdc TBC To meet prelaunch electrical constraints 60 seconds prior to the jettisoning of the umbilical mast and last instant connectors all spacecraft EGSE electrical interface circuits Shall be designed to ensure no current flow greater 100 mA across the connector interfaces 5 5 1 4 Additional umbilical lines Optional 5 14 For mission specific needs another umbilical connector may be added to the Fregat interstage section This connector referred to as SHO5 offers the same service as connector SHO1 To establish this extension Arianespace will provide a new set of harnesses between the spacecraft and the LP room Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft 5 5 2 L V to spacecraft electrical functions The launch vehicle can provide electrical functions used by the spacecraft during flight Due to the spacecraft to launch vehicle interface the Customer is required to protect the circuit against any overload or vo
37. definition of spacecraft GSE dimensions and interfaces required dispatching list A1 4 5 Fluids and propellants needs A1 4 5 1 List of fluids Indicate type quality quantity and location for use of fluids to be supplied by Arianespace Arianespace January 2006 A1 13 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft A1 4 5 2 Chemical and physical analysis to be performed on the range Indicate for each analysis type and specification A1 4 5 3 Safety garments needed for propellants loading Indicate number A1 4 6 Technical support requirements Indicate need for workshop instrument calibration A1 4 7 Security requirements Provide specific security requirements access restriction supervision A1 5 Miscellaneous Provide any other specific requirements requested for the mission A1 6 Contents of the spacecraft development plan protected rooms The Customer prepares a file containing all the documents necessary to assess the spacecraft development plan with regard to the compatibility with the launch vehicle It at least shall include e spacecraft test plan define the qualification policy vibrations acoustics shocks protoflight or qualification model e requirements for test equipment adapters clamp band volume e tests on the Customer s premises e test at the range A1 7 Definitions acronyms symbols Provide a list of acronyms
38. equivalent dynamics Sinusoidal excitations affect the LV during its powered flight mainly the atmospheric flight as well as during some of the transient phases The envelope of the sinusoidal or sine equivalent vibration levels at the spacecraft base does not exceed the values given in Table 3 1 The sinusoidal excitation above 40 Hz is insignificant Table 3 1 Sine Excitation at Spacecraft Base Longitudinal Lateral Latrdl Sine Amplitude g 3 2 3 Random vibration Random vibrations at the spacecraft base are generated by propulsion system operation and by the adjacent structure s vibro acoustic response Maximum excitation levels are obtained during the first stage flight Acceleration power spectral density PSD and root mean square vibration levels Gems are given in Table 3 2 along each of three axes The random vibrations must be taken into account for equipment dimensioning in the 40 100 Hz frequency range considering that at higher frequency it is covered by acoustic loads Table 3 2 The maximum flight levels of random vibrations at Spacecraft Base Frequency Band Frequency Band Hz ee Li MN 50 100 100 200 200 500 500 1000 Game eee 1000 2000 g uu PSD Power PSD Power Spectral Density 1 g2 H7 Density 1 g2 Hz 1 stage flight LINE 0050 0 0100 0 0250 E 0100 2 4 stage and 0 0025 0 0050 0 0100 Bem 0050 3 stage flight amp 997 0 0050 0 0100 0 0100 9 00
39. final orbit and e Fregat deorbitation or orbit disposal maneuvers 2 3 1 Ascent of the first three stages The flight profile is optimized for each mission The upper composite Fregat with payload is separated on a sub orbital path Fregat being used in most cases to reach an intermediate parking orbit the so called intermediate orbit ascent profile in other cases after separation from the third stage a single Fregat boost may inject the upper composite into the targeted orbit the so called direct ascent profile The optimum mission profile will be selected depending upon specific mission requirements A typical Soyuz three stage ascent profile and the associated sequence of events are shown in Figure 2 1 A typical ground track for the lower three stages is presented in the Figure 2 2 GTO mission An example of the evolution of altitude and relative velocity during the ascent profile of the first three stages is presented in Figure 2 3 Jettisoning of the payload fairing can take place at different times depending on the aero thermal flux requirements on the payload Typically fairing separation takes place depending on the trajectory between 155 and 200 seconds from liftoff owing to aero thermal flux limitations 290 E 2 Ascent profile i L Lift off Os 100 First second stage separation 1185 3 Fairing jettisoning 226s 4 Second third stage separation 288 s 5 Third stage lower skirt jettisoning 295
40. gas generator hydrogen nitrogen Nb vaporization 118 s No two level thrust throttling Two 35 kN vernier thrusters and one aerofin Input Output units TM power Burn time Restart Attitude Control Avionics Stage separation Pyronuts pushers reaction nozzle 1 7 286 s No one level thrust throttling Four 35 kN vernier thrusters Input Output units TM power Pyronuts and 3 stage engine ignition 3 35 m diameter x 1 50 m height 950 kg 5350 kg N204 UDMH Structurally stable aluminum alloy 6 spherical tanks 8 cross rods 5 92 Two mode thrust 19 85 14 00 kN Vac Two mode thrust 331 316 s Vac Pump fed open cycle gas generator Ghe vaporization Up to 900 s up to 20 controled or depletion burn Main engine translation or eight 50 N hydrazine thrusters Four 50 N hydrazine thrusters Inertial 3 axis platform on board computer TM amp RF systems Power gas pressure locks pushers 3 STAGE 2 66 m diameter x 6 70 m length 27 755 kg 2 355 kg 17 800 kg LOX 7 600 kg Kerosene Pressure stabilized aluminum alloy tanks with intertanks and rear skin structure RD 0124 4 chamber engine Soyuz 2 1b 297 9 kN Vac RD 0110 4 chamber engine Soyuz 2 1a 297 9 kN Vac 325 s Vac 359 s Vac Pump fed gas Multi stage pump fed generator generator s close cycle gas gas blow down through generator verniers Oxygen Helium vaporization vaporization generator gases 250 s No 27
41. give readers sufficient information to assess the suitability of the Soyuz LV and its associated launch services to perform its mission and to assess the compatibility with the proposed launch vehicle On completion of the feasibility phase formal documentation will be established in accordance with the procedures outlined in Chapter 7 For more detailed information the reader is encouraged to contact Arianespace Arianespace January 2006 1 1 Soyuz CSG User s Manual Issue Draft PERFORMANCE AND LAUNCH MISSION Chapter 2 2 1 1 ntroduction This section provides the information necessary to make preliminary performance assessments for the Soyuz LV The paragraphs that follow present the vehicle reference performance typical accuracy attitude orientation and mission duration The provided data covers a wide range of missions from spacecraft delivery to geostationary transfer orbit GTO to injection into sun synchronous and polar orbit as well as low and high circular or elliptical orbit and escape trajectories Performance data presented in this manual are not fully optimized as they do not take into account the specificity of the Customer s mission Arianespace January 2006 2 1 Performance and launch mission Soyuz CSG User s Manual Issue Draft 2 2 Performance definition 2 2 The performance figures given in this chapter are expressed in term of payload mass including the spacecraft separated mass the d
42. has been installed and the springs have been released each actuator applies a maximum force of 1200 N TBC on the spacecraft rear frame with a 24 N TBC tolerance Note that the clamp band tension does not exceed 33 100 N TBC at any time including dispersions due to temperature variations on ground and in flight This ensures no gapping or sliding between the spacecraft and adapter interfacing frames during all phases of the mission The angular positioning of the spacecraft with respect to the adapter is ensured by the alignment of engraved marks on the interfacing frames at a specified location to be agreed on with the user Adapter 1666 SF is equipped with a set of sensors that are designed to monitor the Spacecraft environment Adapter 1666 SF also holds the electrical harness that is necessary for umbilical links as well as for separation orders and telemetry data transmission from and to the Fregat This harness will be tailored to user needs with its design depending on the required links between the spacecraft and the launcher see Section TBD Adapter 1666 SF can be used with spacecraft whose mass and CoG are below the curve provided in Figure TBD A4 16 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters TO BE ISSUED LATER Figure A4 4 1 Adapter 1666 SF Load capability Arianespace January 2006 A4 17 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft X
43. increased according to mission duration The thermal control system of the two equipment bays consists of two dedicated fans for nitrogen circulation Thermal insulation and heaters protect the external equipment and the propellant tanks The Fregat is presented in Figure A5 4 The Fregat is a restartable upper stage main engine with multiple ignition capability up to 20 times with six demonstrated during flight fully independent from the lower composite I MU telemetry power etc which allows a wide range of missions and even to be potentially compatible with other launch vehicles NPO Lavotchkine located near Moscow is responsible for the production of Fregat Its facilities can accommodate the production of up to eight upper stages per year with a production time of 10 to 15 months Arianespace January 2006 A5 7 Hydrazine bottle Helium bottle Fuel tanks Deployable TM 2 opposite ACS thrusters 3 4 PROS antenna Deployable TM antenna Chemical battery Control system on its support cover radiator Oxidizer tanks 2 opposite Open Equipment bay TM RF Power systems E N Engine management I tem Tracking antenna system Tank extentions Chemical battery Filling control GPS Glonass 55 92 main engine panel antenna Figure A5 5 Fregat Overview TMC M4 4X TMC M4 Antenna A Antenna TMC M4 Antenna ANTENNA AND REF
44. should be indicated solar aspect angle constraints or others A1 2 3 2 Separation conditions A1 2 3 2 1 Separation mode and conditions Indicate spinning axial or transverse or three axis stabilization tip off rates depointing etc including limits A1 2 3 2 2 Separation attitude The desired orientation at separation should be specified by the Customer with respect to the inertial perifocal reference frame U V W related to the orbit at injection time as defined below U radius vector with its origin at the center of the Earth and passing through the intended orbit perigee V vector perpendicular to U in the intended orbit plane having the same direction as the perigee velocity W vector perpendicular to U and V to form a direct trihedron right handed system U V W For circular orbits the U V W frame is related to the orbit at a reference time specified by Arianespace in relation with the mission characteristics with U defined as radius vector with origin at the Earth center and passing through the launcher CoG and V W as defined above In case of 3 axis stabilized mode two of the three S C axes U V W coordinates should be specified In case of spin stabilized mode the S C spin axes U V W coordinates should be specified Maximum acceptable angular rate and relative velocity at separation shall be indicated A1 2 3 3 Separation conditions and actual launch time Need of adjustmen
45. the ground a telecommand to shut down the engines in case of major anomaly during the flight in addition to the automatic one presently used on Soyuz Arianespace January 2006 A5 1 A5 1 2 Boosters First Stage Support cone Oxidizer tank Intertank section Fuel tank Hydrogen Liquid nitrogen peroxide tank tank Aerofin Vernier RD 107A engine chambers Figure A5 1 Booster Layout and Location A5 2 The four boosters are arranged around the central core and are tapered cylinders with the oxidizer tank in the tapered portion and the kerosene tank in the cylindrical portion see Figure A5 1 As in the entire Soyuz lower composite the RD 107A engines of the boosters are powered by nontoxic liquid oxygen kerosene propellants These spark ignition engines are fed by a turbopump running off gases generated by the catalytic decomposition of H202 in a gas generator Each RD 107A has four combustion chambers and nozzles Liquid nitrogen IS used for pressurization of the propellant tanks Attitude control is carried out through two movable vernier thrusters and one aerofin Three axis flight control is made possible through these eight engines two per booster and four aerofins one per booster The boosters burn for 118 seconds and are then discarded Thrust IS transferred through a ball joint located at the top of the cone shaped structure of the booster which is attached to the central core by
46. two rear struts Arianespace January 2006 Soyuz CSG User s Manual Issue Draft A5 1 3 Core Second Stage Truss Equipment Bay Oxidizer Tank Load carrying ring Intertank section Fuel tank Kerosene Hydrogen peroxide tank Liquid nitrogen tank Tail section Vernier chambers a SNEME Figure A5 2 Core Stage Layout and Location Arianespace January 2006 The second stage is similar in construction to the booster stages using the RD 108A engine and four vernier thrusters for three axis flight control see Figure A5 2 The core stage nominally burns for 290 seconds The stage is shaped to accommodate the boosters and a stiffening ring is located at the upper interface between the boosters and central core This structure is strengthened with use of larger fairing The boosters and the central core are ignited on the ground They burn at intermediate thrust levels for approximately 20 seconds before actual liftoff in order to verify their health and nominal level of operation The core stage continues to function after booster shutdown and separation A5 3 A5 1 4 Third Stage Figure A5 3 Third Stage with Ignition of the third stage s single main engine occurs approximately 2 seconds before shutdown of the central core The separation of the stages takes place at a predetermined velocity After separation the lower skirt of the third stage is jettisoned in three s
47. 0 s No Four 6 kN vernier Each chambers thrusters gimbaling in one axis Centralized control system inertial 3 axis platform on board computer TM amp RF system power Introduction Soyuz CSG User s Manual Issue Draft 1 5 2 European spaceport and CSG Facilities 1 8 The launch preparation and launch are carried out from the Guiana Space Centre CSG European spaceport operational since 1968 in French Guiana The spaceport accommodates Soyuz Ariane 5 and Vega separated launch facilities ELS ELA and ELV respectively with common Payload Preparation Complex EPCU and launch support services The CSG is governed under an agreement between France and the European Space Agency that was recently extended to cover Soyuz and Vega installations The day to day life of CSG is managed by French National Agency Centre National d Etude Spatiales CNES on behalf of the European Space Agency CNES provides all needed range support requested by Arianespace for satellite and launch vehicle preparation and launch The CSG provides state of the art Payload Preparation Facilities Ensemble de Preparation Charge Utile EPCU recognized as a high quality standard in space industry The facilities are capable to process several satellites of different customers in the same time thanks to large cleanrooms and supporting infrastructures Designed for Ariane 5 dual launch capability and high launch rate the EPCU capacity is sufficient to be sh
48. 17 Mission Control centre Jupiter IT 6 18 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 3 CSG GENERAL CHARACTERISTICS 6 3 1 Environmental Conditions 6 3 1 1 Climatic conditions The climatic conditions at the Guyana Space Centre are defined as follows e The ambient air temperature varies between 18 C x T lt 35 C e The relative humidity varies between 60 x r lt 100 6 3 1 2 Temperature Humidity and Cleanliness in the facilities Data related to the environment and cleanliness of the various working areas are given in Table 6 1 Table 6 1 The temperature humidity and cleanliness in the facilities Designation Particle Organic Temperature Relative Humidity Cleanliness Cleanliness PPF HPF and Class 8 ESA 23 C 22 C 55 5 XX UCIF S3 100 000 standard clean halls HPF S2 S4 33 C 20 C halls Class 8 ESA ae ee CCU container standard lt 55 5 100 000 CCU3 23 C 2 C LP tower lt 27 C room TBD room Note x A According to the US Federal Standard 209D x According to the AE GRCO 36 Issue 0 Rev 0 December 2000 pollution lt 2 107 g cm week Atmospheric pressure in the EPCU buildings is 998 mbar lt Pam lt 1023 mbar Arianespace January 2006 6 19 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 3 1 3 Mechanical Environment No specific mechanical requirements are applicable during the activity at th
49. 2359 X 1623 193 July 1 1998 Plesetsk Molniya Unmanned Moiniya 3 X 1624 August 13 1998 Baikonur SoyuzU Manned Soyuz TM 28 X 1625 794 alate Plesetsk Molniya Unmanned Molniya 1T X 1626 October 25 1998 Baikonur SoyuzU Unmanned Progress M 40 X 1627 195 February 9 1999 Baikonur SoyuzU Unmanned Globalstar FM36 X 1628 796 Ikar 23 38 40 February 20 1999 Baikonur SoyuzU Manned Soyuz TM 29 X 1629 197 Arianespace January 2006 A5 15 March 15 1999 April 2 1999 April 15 1999 July 8 1999 July 16 1999 August 18 1999 September 9 1999 September 22 1999 September 28 1999 October 18 1999 November 22 1999 December 27 1999 January 2 2000 February 9 2000 March 20 2000 April 4 2000 April 25 2000 May 3 2000 July 16 2000 August 6 2000 August 9 2000 September 29 2000 October 15 2000 October 31 2000 November 16 2000 January 24 2001 February 26 2001 April 28 2001 May 21 2001 May 29 2001 July 20 2001 August 21 2001 September 14 2001 October 21 2001 October 25 2001 A5 16 Baikonur Baikonur Baikonur Plesetsk Baikonur Plesetsk Plesetsk Baikonur Plesetsk Baikonur Baikonur Plesetsk Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Baikonur Plesetsk Plesetsk Baikonur Baikonur Baikonur Plesetsk Soyuz U Ikar
50. 2nd stage engines will be progressively replaced by FG configuration For simplification in this User s Manual the name Soyuz refers to Soyuz with the Fregat upper stage the configuration that is presently offered commercially A5 10 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Arianespace January 2006 R 7A Sputnik 1957 1960 Used to launch the world s first artificial satellite in 1957 the Sputnik LV was a modified version of the R 7A ICBM and was designed for injection of a payload of up to 1 5 tons The vehicle consists of just four strap on boosters and a central core and is considered as two stage LV This vehicle launched the first three Sputnik satellites in 1957 and 1958 Soon after these missions this two stage LV was no longer used owing to the desire to launch larger payloads Vostok 1958 1991 In order to launch heavier payloads and more complex missions the Vostok LV added a third stage to the R 7A Sputnik LV alone The Vostok LV essentially uses the same four strap on boosters as the R 7A Sputnik launch vehicle and adds a LOX Kerosene fueled third stage Block E designed by the OKB 1 design bureau In 1959 the Vostok successfully launched the first unmanned spacecraft Lunnik to the moon and to achieve earth escape velocity In 1961 the Vostok LV was also used to launch the first man Yuri Gagarin Owing to its limited payload capacity the Vostok was not used fo
51. 433 m 7 700 m Mass 1700 kg 1045 kg Structure Two half shell carbon Two half shell aluminum fiber reinforced plastic skin stringer Separation Mechanical locks Mechanical locks Spring pneumatic jack pushers jack pushers I nterstage Mass 400 kg 350 kg Structure aluminum skin stringer Aluminum skin stringer PAYLOAD ADAPTERS Off the shelf devices 1194SF 838750 1666SF 110 kg 45 kg 100 kg 1 STAGE FOUR BOOSTERS Size 2 68 m diameter x 19 60 m length 44 413 kg 3 784 kg 27 900 kg LOX 11 260 kg Kerosene Gross Dry mass Propellant Subsystems Structure Pressure stabilized aluminium alloy tanks with intertanks skin structure Propulsion RD 107A 4 chambers engine Thrust 838 5 kN SL 1021 3 kN Vac Isp 262 s SL 319 s Vac Feed system pump fed by hydrogen peroxide H205 gas generator Pressurization Liquid nitrogen N5 vaporization Liquid FREGAT UPPER STAGE Size Inert mass Propellant Subsystems Structure Propulsion Thrust Isp Feed system Pressurization Burn time Restart Attitude Control pitch yaw roll Avionics Stage separation 2 STAGE CORE 2 95 m diameter x 27 10 m length 99 765 kg 6 545 kg 63 800 kg LOX 26 300 kg Kerosene Pressure stabilized aluminum alloy tanks with intertanks skin structure RD 108A 4 chambers engine 792 5 kN SL 990 2 kN Vac 255 s SL 319 s Vac pump fed by peroxide H202
52. 50 0 0025 FREGAT flight 00020 0020 00020 0020 0 0020 b 0040 0 0010 163 875 Note 1 co of the Power LUNG Density in frequency sub ranges is linear when a logarithmic scale is used for both frequency and Power Spectral Density Arianespace January 2006 3 2 Environmental conditions Soyuz CSG User s Manual Issue Draft 3 2 4 Acoustic vibration 3 2 4 1 On Ground The noise level generated by the venting system does not exceed 94 dB 3 2 4 2 In Flight 3 4 Acoustic pressure fluctuations under the fairing are generated by engine operation plume impingement on the pad during liftoff and by unsteady aerodynamic phenomena during atmospheric flight i e shock waves and turbulence inside the boundary layer which are transmitted through the upper composite structures Apart from liftoff and transonic flight acoustic levels are substantially lower than the values indicated hereafter The envelope spectrum of the noise induced inside the fairing during flight is shown in Table 3 3 It corresponds to a space averaged level within the volume allocated to the spacecraft stack as defined in Chapter 5 The acoustic spectrum defined below covers excitations produced by random vibration at the spacecraft base for frequency band above 100 Hz It is assessed that the sound field under the fairing is diffuse Table 3 3 Acoustic Noise Spectrum under the Fairing Flight Limit Level dB Octave Center reference 0 dB
53. 53 April 15 2005 Baikonur Soyuz Manned Soyuz TMA 6 X 1695 854 FG May 31 2005 Baikonur SoyuzU Unmanned Foton M2 X 1696 899 June 17 2005 Baikonur SoyuzU Unmanned Progress M 53 X 1697 856 June 21 2005 Plesetsk Moiniya Unmanned Molnia 3K 1698 M August 14 2005 Baikonur Soyuz Unmanned Galaxy 14 X 1699 857 FG Fregat September 2 Baikonur Soyuz Unmanned X 1700 858 2005 September 8 Baikonur SoyuzU Unmanned Progress M 54 X 1701 859 2005 October 1 2005 Baikonur Soyuz Manned Soyuz TMA 7 X 1702 860 FG November 9 2005 Baikonur Soyuz Unmanned Venus Express X 1703 861 FG Fregat December 21 Baikonur SoyuzU Unmanned Progress M 55 X 1704 862 2005 December 28 Baikonur Soyuz Unmanned GIOVE A X 1705 863 2005 FG Fregat The two failures listed in 1996 May 14 and June 20 were due to a manufacturing defect of the fairing release mechanism Since the fairings for the two flights were manufactured in a batch the same defect was repeated on both fairings The cause was identified other fairings in the batch were repaired and corrective actions were taken to ensure that this defect was not repeated The failure on October 15 2002 was due to a particle in the hydrogen peroxide circuit running the turbopump of the 1 st stage booster This anomaly was detected after 37 successful launches of the same production batch Nevertheless comprehensive corrective actions were taken in the design of the questionable element production operation and prepara
54. Accommodation Arianespace may assign some places for Customer s VIP in the Mission Control Center Jupiter 2 for witnessing of the final chronology and launch The details of this VIP accomodation shall be agreed with advance notice 6 4 5 6 Other assistance For the team accommodation flight reservations banking off duty amp leisure activities the Customer can use the public services in Kourou and Cayenne or can benefit from the support of Arianespace s affiliated company Free Lance Arianespace January 2006 6 29 Soyuz CSG User s Manual Mission integration and Issue Draft management MI SSI ON INTEGRATI ON AND MANAGEMENT Chapter 7 7 1 Introduction To provide the Customer with smooth launch preparation and on time reliable launch a customer oriented mission integration and management process is implemented This process has been perfected through more than 200 commercial missions and complies with the rigorous requirements settled by Arianespace and with the international quality standards ISO 9000 V 2000 specifications The mission integration and management process covers Mission management and Mission integration schedule LV procurement and hardware software adaptation as needed Systems engineering support Launch campaign management Safety assurance Quality assurance The mission integration and management process is consolidated through the mission documentation and accessed and verified during formal meet
55. Arianespace January 2006 Soyuz CSG Manual Application to use Issue Draft Arianespace s launch vehicle A1 4 Operational requirements A1 4 1 Provisional range operations schedule Provide a main operations list and description including launch pad activities and estimated timing with hazardous operation identification A1 4 2 Facility requirements For each facility used for spacecraft preparation PPF HPF Launch pad provide main operations list and description space needed for spacecraft GSE and Customer offices environmental requirements Temperature relative humidity cleanliness power requirements Voltage Amps phases frequency category RF and hardline requirements support equipment requirements GSE and hazardous items storage requirements A1 4 3 Communication needs For each facility used for spacecraft preparation PPF HPF Launch pad provide need in telephone facsimile data lines time code A1 4 4 Handling dispatching and transportation needs Provide estimated packing list including heavy large and non standard container characteristics with indication of designation number size L x W x H in m and mass kg propellant transportation plan including associated paperworks a definition of the spacecraft container and associated handling device constraints a definition of the spacecraft lifting device including the definition of ACU interface if provided by the Customer a
56. BD Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters TO BE ISSUED LATER Figure A4 1 1 Adapter 937 SF Load capability Arianespace January 2006 A4 3 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft X t OE 7 0 3 0 03 10 0 5 A 750 0 5 2046 OVERHEAD VIEW Zh 4 SEPARATION SPRINGS 90 APART ON 825 5 2 UMBILICAL CONNECTORS 180 APART ON 1219 Figure A4 1 2 Adapter 937 SF General view A4 4 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters KEYWAY ON SPACECRAFT REAR FRAME UNDERSIDE VIEW engraved mark is also acceptable DETAIL A ACU 937 SF Ec Upper fr frame ams Rear x frame COATING For surfaces in contact a and ACU frames Chromic acid anodizing STIFFNESS Applicable length ae 25 section area zs 1420 230 460 Inertia bx mm 11700 lt lt 69000 lyy 7480 lt lt 12650 TWO ENGRAVED REFERENCE MARKS ON ADAPTOR UPPER FRAME OVERHEAD VIEW x t 29452605 P12 876 3 2025 lm 16 bea B m P PLANE Fu T d 6 0 05 d 7 a EE En V R2 32025 w ZZ TS 24 6 64 1402 908 8 926 2 202 gt 945 26 I A SETAE 939 97 6 2 DISMANTLING INTERFACE DETAIL B SEP PLANE Figure A4 1 3 Adapter 937 SF Interface frames Arianespace
57. CO Operations Coordination Office BNBD Low level bipolar unbalanced BT POC Combined operations readiness review Bilan Technique POC CAD Computer Aided Design CCTV Closed Circuit Television Network CCU Payload Container Container Charge Utile CDL Launch Control Building Centre de Lancement CDR Critical Design Review CFRP Carbon Fiber Reinforced Plastic CG CoG Center of Gravity Centre de Gravit CLA Coupled Loads Analysis CM Mission Director Chef de Mission CNES French National Space Agency Centre National d Etude Spatiales COEL Launch Site Operations Manager Chef des Op rations Ensemble de Lancement COTE Check Out Terminal Equipment CP Program director Chef de Programme CPAP Ariane production project manager CPS Spacecraft project manager Chef de Projet Satellite CRAL Post Flight Debriefing Compte Rendu Apres Lancement CRE Operational Reporting Network Compte Rendu d Etat Arianespace XI l1 XII CSEL CSG CVCM CVI CU DAM DAMF DAMP DCI DDO DEL DL DMS DUA DV EADS EDP EDS EGSE ELA ELS ELV EMC EPCU ESA ESMC FAR FM FM FMA FMAD FMAR FAR GEO Soyuz CSG User s Manual Issue Draft Launch Complex Safety Officer Guiana Space Centre Technical Centre Collected Volatile Condensable Material Centre Spatial Guyanais Centre Technique Contr le Visuel Imm diat Payload Charge Utile Mission analysis document Document d Analyse de Mission
58. Document d Analyse de Mission Finale Document d Analyse de Mission Pr liminaire Document de Contr le des Interfaces Final mission analysis document Preliminary mission analysis document Interface control file Range operations manager Flight Synthesis Report FSR Document d Evaluation du Lancement Demande de Lancement Directeur de Mission Satellite Demande d Utilisation Arianespace Directeur Vol Launch requirements document Spacecraft mission director Application to use Arianespace launch vehicles Flight director European Aeronautic Defense and Space Company Hazardous primary circuits Hazardous secondary circuits Electrical Ground Support Equipment Ariane launch site Ensemble de Lancement Ariane Ensemble de Soyuz Soyuz Launch Site Lancement ELV S p A European Launch Vehicle Electromagnetic Compatibility Payload preparation complex Ensemble de Pr paration des Charges Utiles European Space Agency Eastern Space Missile Center Fueling Authorization Review Frequency modulation Flight Model Final Mission Analysis Final Mission Analysis Document Final Mission Analysis Review RAMF Revue d Analyse de Mission Finale Final Qualification Review Geosynchronous Equatorial Orbit Arianespace Soyuz CSG User s Manual Issue Draft GRS General Range Support GSE Ground Support Equipment GTO Geostationary Transfer Orbit GTO Geosynchronous Transfer Orbit HEO Highly Elliptical Orbit H
59. ENGINEERING SUPPORT 7 4 1 Interface Management 7 4 2 Mission Analysis 7 4 3 Spacecraft Design Compatibility Verification 7 4 4 Post launch Analysis 7 5 LAUNCH CAMPAIGN 7 5 1 Introduction 7 5 2 Spacecraft Launch campaign preparation phase 7 5 3 Launch Campaign Organization 7 5 4 Launch campaign meetings and reviews 7 5 5 Summary of a typical launch campaign 7 6 SAFETY ASSURANCE 7 6 1 General 7 6 2 Safety Submission 7 6 3 Safety training 7 6 4 safety measures during hazardous operations 7 7 QUALITY ASSURANCE 7 7 1 Arianespace s quality assurance system 7 7 2 Customized quality reporting optional Annex 1 APPLICATION TO USE ARIANESPACE S LAUNCH VEHICLE DUA Annex 2 REVIEW AND DOCUMENTATION CHECKLIST Annex 3 ITEMS AND SERVICES FOR AN ARIANESPACE LAUNCH Annex 4 STANDARD PAYLOAD ADAPTERS Annex 5 LAUNCH VEHICLE DESCRIPTION Arianespace Soyuz CSG User s Manual Issue Draft Acronyms abbreviations and definition D D s NN 0 9 X SS Argument of perigee Ascending node Descending node Semi major axis Eccentricity Apogee altitude Perigee altitude Inclination ABM Apogee Boost Motor ACS Attitude Control System ACU Payload adapter Adapteur Charge Utile ACY Raising Cylinder AE Arianespace ARS Satellite ground stations network Assistant Adjoint R seau Sol AULV Application to Use Arianespace Launch Vehicle AZ Azimuth Azimut BCL Launch Vehicle Checkout System B
60. Fibres Optiques SYst me de Lancement Double SOyuz Temps D compt T l phone Sp cialis XV V VEB W w r t Z ZL ZSP Vehicle Equipment Bay With Reference to With Respect to Launch Pad Pyrotechnics Storage facility Soyuz CSG User s Manual Issue Draft Zone de Lancement Zone de Stockage de Pyrotechnique Upper Composite defined as the spacecraft adapter and upper stage if located under the fairing encapsulated under the fairing with its interstage bay 1 XVI Arianespace Soyuz CSG User s Manual Issue Draft INTRODUCTION Chapter 1 1 1 Purpose of the User s Manual This User s Manual is intended to provide basic information on the Arianespace s launch services solution using the Soyuz launch system operated from the Guiana Space Centre along with Ariane 5 and Vega launch systems The content encompasses the Soyuz launch vehicle LV description performance and launch vehicle mission environmental conditions imposed by the LV and corresponding requirements for Spacecraft design and verification description of interfaces between spacecraft and launch vehicle payload processing and ground operations performed at the launch site mission integration and management including Customer s support carried out throughout the duration of the launch contract Together with the Payload Preparation Complex Manual EPCU User s Manual and the CSG Safety Regulations it will
61. L 20 Approval IE 2 S C Dynamic model Preliminary L 19 Review Final L 6 Review 3 S C thermal model Preliminary L 20 Review Final L 6 Review 6 Safety Submission Phase 2 L 17 to Approval L 9 S C mechanical environmental Test Plan L 20 Review Updated S C data for final mission analysis L 6 Review S C Launch operations Plan POS 7 Review S C operations procedures applicable at CSG including Safety Submission Phase 3 oo fpes 7 Environmental Testing Instrumentation L 5 Approval plan notching plan test prediction for Sine test amp test plan for Acoustic test according to A4 SG 0 P 01 S C mechanical environment tests results L 2 5 maven according to A4 SG 0 P 01 S C final launch window L 2 5 Review amp Final S C mass properties L 7 days Approval After S C filling 9 Orbital Tracking report orbit parameters 2 weeks after For information after separation Launch Arianespace January 2006 A2 3 Review and documentation Soyuz CSG User s Manual checklist Issue Draft A2 4 Meetings and reviews 1 Contractual Kick Off Meeting L 24 M E C DUA Review L 22 M E O S 3 Preliminary Mission Analysis Kick Off L 20 M E S X First DCI Review and Ed 0 signature 1 month after Review of Safety Submission Phase 1 4 DCI Signature L 18 M E O E 5 Prelim Mission Analysis Review RAMP L 16 M E S E DCI Review Safety Submission Status 6 Preparation of S C Operations Plan POS L 12 M O S K
62. LANET Payload Local Area NETwork PLANET provides Customer with dedicated Ethernet VLAN type 10 Mb s network This network is set up and managed by CSG 3 VLAN networks are available per Customer and can be accomodated according to Customer s request for operational data tranfer between EGSE and satellite and or for inter offices connections between personal computers Encrypted data transfer is also possible Dedicated stripped ends optical fibers are also available in PPF low bays for EGSE connectors at one side in HPF and in the launch pad Customer room for COTE connection at the other end For confidentiality purpose Customers can connect their equipment at each part of these direct and point to point dedicated optical fibers Arianespace January 2006 6 21 Guiana Space Centre Soyuz CSG User s Manual Issue Draft TO BE ISSUED LATER Figure 6 18 Typical operational data network configuration 6 22 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 3 3 2 Range communication network The multifunctional range communication network provides Customer with different ways to communicate internally at CSG and externally by voice and data and delivers information in support of satellite preparation and launch The following services are proposed in its standard configuration or adapted to the Customer needs CSG Telephone PABX System CTS Arianespace provides specified numbers
63. LECTOR Figure A5 6 Antennas location on the Fregat A5 8 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft A5 2 LAUNCH VEHICLE HISTORY RECORD A5 2 1 Soyuz Family of Launch Vehicles The two stage R 7A intercontinental ballistic missile ICBM laid the groundwork for an evolutionary series of launch vehicles that would eventually launch the world s first satellite Sputnik 1957 and man Yuri Gagarin 1961 into space Originally developed by Sergei Korolev s OKB 1 design bureau now RSC Energia in Kaliningrad the R 7A was the first in a series of vehicles that in addition to the Soyuz includes Sputnik Vostok Molniya and Voskhod Since the R 7A was developed between 1953 and 1957 some ten different versions have been built in this family Production of the R 7A was moved to the Progress Aviation Factory in Samara Russia now the production facility of TSSKB Progress beginning in 1959 Over time complete responsibility for the family would pass from Kaliningrad to Samara with the design facilities at Samara transforming from a subsidiary of OKB 1 to an independent entity TSSKB in 1974 Since then TSSKB and the Progress factory have been in charge of design development and production of vehicles in this family and their future derivatives They were combined into one entity Samara Space Center TSSKB Progress in 1996 Vehicles in this family ha
64. PF Hazardous Processing Facility HSF Hazardous Storage Facility HV High Voltage I S nterstage ICD Interface Control Document IMU I nertial Measurement Unit lO Operational Intersite Intercom system Intercom Operationelle ISCU Payload safety officer Ing nieur Sauvegarde CU ISLA Launch area safety officer I ng nieur Sauvegarde Lanceur Ariane ITAR I nternational Traffic in Arms Regulations KM Kick motor KRU Kourou LAM Measuring instrument laboratory Laboratoire Mesures LBC Check out equipment room Laboratoire Banc de Contr le LEO Low Earth Orbit LL Leased Lines LOX Liquid Oxygen LP Launch Pad LRR Launch Readiness Review Revue d aptitude au lancement LSA Launch Service Agreement LTD Data transmission links Ligne de Transmission de Donn es LV Launch Vehicle LW Launch Window MCC Mission Control Centre Centre de Contr le MCI Masses balances and inertias Masse Centre de gravit Inerties MCU Payload mass Masse Charge Utile MEO Medium Earth Orbit MEOP Maximum Expected Operating Pressure MGSE Mechanical Ground Support Equipment MIK Assembly and Integration Building Russian acronym MMH Monomethyl Hydrazine Arianespace XIII MPS MUSG N A NCR NTO OASPL OBC OCOE PABX PCM PCU PDE PDR PFCU PFM PFT PIP PLANET PMA PMAD PMAR POC POE POI POP POS PPF PPLS PSCU PSD QA QR QSL QSM QSP QSR Soyuz CSG User s Manual Issue Draft Master Program Sched
65. SG User s Manual Issue Draft 4 3 3 3 Random vibration tests The verification of the spacecraft structure compliance with the random vibration environment in the 40 Hz 100 Hz frequency range shall be performed Three methodologies can be followed Method Number One Perform a dedicated random vibration qualification test Frequency band Spectral density 10 g Hz Qualification 20 50 11 25 50 100 11 25 22 5 100 200 22 5 56 25 200 500 56 25 500 1000 56 25 22 5 1000 2000 22 5 11 25 Overall g Method Number Two Conduct the sine vibration qualification test up to 100 Hz and apply input levels high enough to cover the random vibration environment equivalency obtained with the Miles formula TT Grus mn O input where Gems root mean square acceleration g f Natural frequency Hz RR l Q Amplification factor at frequency fna Q Dee where is the critical damping ratio PSDinput Input Power Spectral Density at fa g Hz Method Number Three Conduct the sine vibration qualification test up to 100 Hz so as to restitute the structural transfer functions and then demonstrate the compliance of the spacecraft secondary structure with the random vibration environment by analysis Above 100 Hz spacecraft qualification with respect to the random vibration environment is obtained through the acoustic vibration test 4 10 Arianespace January 2006 Soyuz CSG User s Ma
66. SG User s Manual Guiana Space Centre Issue Draft E NY Soyuzlaunching area 59 18 18 North 529 50 04 West Technical Centre Figure 6 2 The Guiana Space Centre Arianespace January 2006 6 3 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 2 CSG GENERAL PRESENTATION 6 2 1 Arrival areas The spacecraft Customer s ground support equipment and propellant can be delivered to the CSG by aircraft landing at Rochambeau international airport and by ship at the Cayenne Pariacabo for commercial ships and Pariacabo harbor for Arianespace s ships that can be used also for spacecraft delivery Arianespace provides all needed support for the equipment handling and transportation as well as formality procedures 6 2 1 1 Rochambeau international airport 6 2 1 2 Cayenne harbour 6 2 1 3 The Pariacabo docking area 6 4 Rochambeau international airport is located near Cayenne with a 3200 meters runway adapted to aircraft of all classes and particularly to the Jumbo jets e B 747 e C130 e Antonov 124 A wide range of horizontal and vertical handling equipment is used to unload and transfer standard type pallets containers Small freight can be shipped by the regular Air France B747 cargo weekly flight A dedicated Arianespace office is located in the airport to welcome all participants arriving for the launch campaign and to coordinate the shipment procedures The airport is co
67. SION DURATION LAUNCH WINDOW SPACECRAFT ORIENTATION DURING THE FLIGHT VII Arianespace Soyuz CSG User s Manual Issue Draft 2 9 SEPARATION CONDITIONS 2 9 1 Orientation performance 2 9 2 Separation mode and pointing accuracy CHAPTER 3 ENVIRONMENTAL CONDITIONS 3 1 GENERAL 3 2 MECHANICAL ENVIRONMENT 3 2 1 Steady state accelerations 3 2 2 Sine equivalent dynamics 3 2 3 Random vibrations 3 2 4 Acoustic vibrations 3 2 5 Shocks 3 2 6 Static pressure under the fairing 3 3 THERMAL ENVIRONMENT 3 3 1 Introduction 3 3 2 Ground operations 3 3 3 Flight environment 3 4 CLEANLINESS AND CONTAMINATION 3 4 1 Cleanliness 3 4 2 Contamination 3 5 ELECTROMAGNETIC ENVIRONMENT 3 5 1 LV and range RF systems 3 5 2 The electromagnetic field 3 6 ENVIRONMENT VERIFICATION CHAPTER 4 SPACECRAFT DESIGN AND VERIFICATION REQUIREMENTS 4 1 INTRODUCTION 4 2 DESIGN REQUIREMENTS 4 2 1 Safety requirements 4 2 2 Selection of spacecraft materials 4 2 3 Spacecraft properties 4 2 4 Dimensioning loads 4 2 5 Spacecraft RF emission 4 3 SPACECRAFT COMPATIBILITY VERIFICATION REQUIREMENTS 4 3 1 Verification logic 4 3 2 Safety factors 4 3 3 Spacecraft compatibility tests 1 VIII Arianespace Soyuz CSG User s Manual Issue Draft CHAPTER 5 SPACECRAFT INTERFACES 5 1 INTRODUCTION 5 2 THE REFERENCE AXES 5 3 ENCAPSULATED SPACECRAFT INTERFACES 5 3 1 Payload usable volume definition 5 3 2 Spacecraft acces
68. Soyuz U Soyuz U Ikar Molniya Soyuz U Soyuz U Soyuz U Soyuz U Ikar Soyuz U Soyuz U Ikar Soyuz U Ikar Molniya Soyuz U Soyuz U Fregat Soyuz U Fregat Soyuz U Soyuz U Soyuz U Soyuz U Fregat Soyuz U Soyuz U Fregat Soyuz U Soyuz U Soyuz U Soyuz U Soyuz U Soyuz U Soyuz U Soyuz FG Soyuz U Molniya M Soyuz U Soyuz U Soyuz U Molniya Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Manned Unmanned Unmanned Unmanned Unmanned Unmanned Manned Unmanned Globalstar FM22 41 46 37 Progress M 41 Globalstar FM19 42 44 45 Molniya 3 Progress M 42 Kosmos 2365 Foton 12 Globalstar FM33 50 55 58 Resurs F1M Globalstar FM31 56 57 59 Globalstar FM29 34 39 61 Kosmos 2368 Progress M1 1 IRDT DUMSAT Soyuz TM 30 Progress M1 2 Kosmos 2370 Cluster Il FM6 7 Samba Salsa Progress M1 3 Cluster Il FM5 8 Rumba Tango Kosmos 2373 Progress M 43 Soyuz TM 31 Progress M1 4 Progress M1 5 Progress M 44 Soyuz TM 32 Progress M1 6 Kosmos 2377 Molnia 3K Progress M 45 Progress M SO1 w Stikovochniy Otsek 1 Soyuz TM 33 Molniya 3 A X KK XX X KKK KOK OK KOK KKK X XXI X X X X X XX XX XX X X X 1630
69. Upper Composite launch countdown rehearsal implies the activation of major part of the electrical and mechanical on board and ground sub systems involved in launch together with Spacecraft systems and ground network The major objective of this nterfaces and the training of the Spacecraft and rehearsal is the verification of the launch vehicle teams 7 5 5 5 4 Launch countdown The major countdown activity starts Mission integration and management approximately 8 hours before lift off During this time the Customer performs the final Spacecraft preparation and verification The Spacecraft s final RF flight configuration set up must be completed before 1h30m and remains unchanged until 20 s after separation The Customer can require a hold or abort of the countdown up to the 20s before lift off It can be done automatically according to established countdown procedures Figure 7 5 shows major events in the countdown chronology on launch day Hours Man BERTI SIC preparation S C readiness to LV fueling LA An den rhdom helen Fregat amp GSE verifications Shin Fregat TM verification D sons Fregat launch readiness setting eS Fregat readiness to LV fueling Ariam th m Apu Readiness b fueling fal Electrical systems verification LV TM verification Preparation 14m Th30m 5h Shin het IP Alinement M ih35m Start of the automatic sequence V Communication ie Network Verifi
70. V is essentially the first 3 stages of the Molniya vehicle It was able to launch heavier payloads to LEO than the Vostok and became the Soviet Union s workhorse launch vehicle of the late 1960 s and early 1970 s This vehicle was first launched in 1963 to launch the Zenit series of observation satellites From 1964 to 1966 it was also used to launch the Voskhod series of three crew member manned spacecraft Arianespace January 2006 Soyuz CSG User s Manual Issue Draft ayas mt 1 1 I I PiS i i ii Arianespace January 2006 Soyuz 1966 Present The Soyuz LV was developed from Voskhod for launching the manned Soyuz spacecraft Initially modifications were made to the intermediate bay of Voskhod and a new fairing was designed with an emergency crew escape System Several improvements were made on the vehicle s design during the 1960 s and early 1970 s cumulating in 1973 with the introduction of the Soyuz U 11A511U which unified and standardized the improvements that had been made over the previous eight years This version is by far the most frequently flown and makes up the first three stages of the Soyuz vehicle that markets for commercial use with the Fregat upper stage The Soyuz U2 11A511U2 was introduced in 1982 and used synthetic kerosene Sintin in the core stage to provide higher performance The Soyuz U2 was flown 70 times and was then discontinued In 1999 a restartable up
71. a and surface frame only and grounding A1 3 6 2 Customer providing its own adapter Define adaptor and its interface with the launch vehicle according to Arianespace s specifications Define the characteristics of the separation system including separation spring locations type diameter free length compressed length spring constraint energy tolerances on the above dispersion on spring energy vectors dispersion of separation system clampband tension dispersion on pyro device actuation times the energy of separation and the energy released in the umbilical connectors A1 3 6 3 Spacecraft accessibility requirements after encapsulation Indicate items on the spacecraft to which access is required after encapsulation and give their exact locations in spacecraft coordinates Arianespace January 2006 A1 9 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft A1 3 7 Electrical interfaces Provide the following e a spacecraft to EGSE links description and diagram as well as a definition of umbilical connectors and links indicate voltage and current during launch preparation as well as at plug extraction The umbilical links at launch preparation S C connector Function Max Max Max voltage Expected pin allocation voltage current drop one way resistance The umbilical links at umbilical connector extraction lift off Function Max voltage Max current V mA e a
72. accurate data please contact Arianespace 2 16 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 5 Injection accuracy The accuracy of the four stage Soyuz is determined mainly by the performance of the Fregat upper stage Conservative accuracy data depending on type of the mission are presented in Table 2 1 Mission specific injection accuracy will be calculated as part of the mission analysis Table 2 1 Injection Accuracy 10 Mission Super Sub Altitude km Circular Orbit GTO GTO Orbital Aude ofapogee my a meere J s w TBD Argument of perigee deg RAAN deg 0 083 0 083 Note Though the accuracy of some injection parameters for Super GTO is less than that for GTO the required S C fuel amount for final orbit correction is approximately the same in both cases 2 6 Mission duration Mission duration from lift off until separation of the spacecraft on the final orbit depends on the selected mission profile specified orbital parameters injection accuracy and the ground station visibility conditions at spacecraft separation Typically critical mission events such as payload separation are carried out within the visibility of LV ground stations This allows for the receipt of near real time information on relevant flight events orbital parameters on board estimation and separation conditions The typical durations of various missions wit
73. aft s heat dissipation 3 10 Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft TO BE ISSUED LATER Figure 3 5 Configuration of the air conditioning systems Arianespace January 2006 3 11 Environmental conditions Soyuz CSG User s Manual Issue Draft 3 3 3 Flight environment 3 3 3 1 Thermal conditions before fairing jettisoning The thermal flux density radiated by the fairing does not exceed 800 W m at any point This figure does not take into account any effect induced by the spacecraft dissipated power 3 3 3 2 Aerothermal flux and thermal conditions after fairing jettisoning 3 12 The nominal time for jettisoning the fairing is determined in order not to exceed the aerothermal flux of 1135 W m This flux is calculated as a free molecular flow acting on a plane surface perpendicular to the velocity direction and based on the atmospheric model US 66 latitude 159 North Typically the aerothermal flux varies from 1135 W m to less than 200 W m within 20 seconds after the fairing jettisoning as presented in Figure 3 6 For dedicated launches lower or higher flux exposures can be accommodated on request as long as the necessary performance is maintained Solar radiation albedo and terrestrial infrared radiation and conductive exchange with LV must be added to this aerothermal flux While calculating the incident flux on spacecraft account must be taken of the al
74. ance notice negociations and agreement with local authorities It includes e coordination of loading unloading activities e transportation from Rochambeau airport and or Degrad des Cannes harbor to CSG and return to airport harbor of spacecraft and associated equipment of various freight categories standard hazardous fragile oversized loads low speed drive etc compliant with transportation rules and schedule for oversized loads The freight is limited to 12 x 10 ft pallets or equivalent in 2 batches plane or vessel e depalletisation of spacecraft support equipment on arrival to CSG and dispatching to the various working areas e palletisation of spacecraft support equipment prior to departure from CSG to airport harbor e all formality associated with the delivery of freight by the carrier at airport harbor e CSG support for the installation and removal of the spacecraft check out equipment It does not include e the octroi de mer tax on equipment permanently imported to Guiana if any e insurance for spacecraft and its associated equipment A3 7 1 3 Logistics support Support for shipment and customs procedures for the spacecraft and its associated equipment and for personal luggage and equipment transported as accompanied luggage A3 7 1 4 Spacecraft and GSE Inter Site Transportation All spacecraft transportation either inside the S C container or in the payload container CCU and spacecraft GSE trans
75. and Gases Arianespace provides the following standard fluids and gases to support the Customer launch campaign operations industrial quality gases e compressed air supplied through distribution network e nitrogen GN of grade N50 supplied through distribution network from tanks or in 50 bottles e nitrogen GN of grade N30 supplied through distribution network only in S3 area e helium GHe of grade N55 supplied through distribution network from tanks limited capacity or in 50 bottles industrial quality liquids e nitrogen LN2 N30 supplied in 35 or 60 Dewar flasks e isopropylic alcohol IPA MOS SELECTIPUR e demineralized water Additionally breathable air and distilled water networks are available in the HPF for hazardous operations Any gases and liquids different from the standard fluid delivery different fluid specification or specific use GN N60 deionized water can be procured The Customer is invited to contact Arianespace for their availability The CSG is equipped with laboratories for chemical analysis of fluids and gases This service shall be requested by the Customer as option Arianespace does not supply propellants Propellant analyses except Xenon can be performed on request Disposal of chemical products and propellants are not authorized at CSG and wastes must be brought back by the Customer 6 26 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Ce
76. angular positioning of the spacecraft with respect to the adapter is ensured by the alignment of engraved marks on the interfacing frames at a specified location to be agreed on with the user Adapter 1194 SF is equipped with a set of sensors that are designed to monitor the spacecraft environment Adapter 1194 SF also holds the electrical harness that is necessary for umbilical links as well as for separation orders and telemetry data transmission from and to the Fregat This harness will be tailored to user needs with its design depending on the required links between the spacecraft and the launcher see Section TBD Adapter 1194 SF can be used with spacecraft whose mass and CoG are below the curve provided in Figure TBD Arianespace January 2006 A4 9 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft TO BE ISSUED LATER Figure A4 2 1 Adapter 1194 SF Load capability A4 10 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters F 1215 0 15 S C SEPARATION PLANE o T BOLTED INTERFACE 2000 8 holes 18 I 2044 Max FREGAT INTERFACE PLANE 12 ACTUATORS LOCATION 30 APART ON 11161 OVERHEAD VIEW 7 t 2 UMBILICAL CONNECTORS 180 APART ON 1578 25 Figure A4 2 2 Adapter 1194 SF General view A4 11 Arianespace January 2006 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft 1 engra
77. ared by the Customers of all three launch vehicles The satellite launch vehicle integration and launch are carried out from launch sites dedicated for Ariane Soyuz or Vega The Soyuz Launch Site Ensemble de Lancement Soyuz ELS is located some 10 km North of the existing Ariane 5 launch facilities and provides the same quality of services for payload The moderate climate the regular air and sea connection accessible local transportation and excellent accommodation facilities as for business and for recreation all that devoted to User s team and invest to the success of the launch mission Arianespace January2006 Soyuz CSG User s Manual Introduction Issue Draft LU KM Soyuz launch area 5 MN I kS N M Ariane launch area Figure 1 2 CSG overview Arianespace January 2006 1 9 Introduction Soyuz CSG User s Manual Issue Draft 1 5 3 Launch service organization Arianespace is organized to offer a Launch Service based on a continuous interchange of information between a Spacecraft Interface Manager Customer and the Arianespace Program Director Arianespace who are appointed at the time of the launch contract signature As from that date the Ariane Program Director is responsible for the execution of the Launch Service Contract For a given launch therefore there can be one or two Spacecraft Interface Manager s and one or two Arianespace Program Directors depending on whether the launch i
78. atellite dimensional and mating parameters meet all relevant requirements as well as to verify operational accessibility to the interface and cable routing It can be followed by a release test This test is usually performed at the Customer s facilities with the adapter equipped with its separation system and electrical connectors provided by Arianespace For a recurrent mission the mechanical fit check can be performed at the beginning of the launch campaign in the payload preparation facilities 2 Electrical fit check Functional interfaces between the spacecraft and the Fregat upper stage power supply TM monitoring commands etc if any shall be checked prior to the beginning of the launch campaign The customer shall provide an adequate spacecraft electrical interface simulator to be used in the launcher authority s facilities to perform these tests 5 6 2 Pre launch validation of the electrical 1 F 5 6 2 5 20 1 Definition The electrical interface between satellite and launch vehicle is validated on each phase of the launch preparation where its configuration is changed or the harnesses are reconnected These successive tests ensure the correct integration of the satellite with the launcher and help to pass the non reversible operations There are three major configurations e Spacecraft mated to the adapter e Spacecraft with adapter mated to Fregat e Upper composite mated to launch vehicle 3 stage Depending on th
79. ath Data are transmitted from ground stations to a Mission Control Center where they are analyzed and recorded some in real time A5 1 5 3 Tracking The launch vehicle position determined by the IMU and is downlinked to the ground through the telemetry system In addition one independent GPS GLONASS receiver elaborates the position of the launcher and transfers it to the ground every second through the same telemetry system The redundant tracking system based on transponder compatible with CSG ground station is used independently A5 1 5 4 Range Safety A5 6 The Soyuz launched from the CSG uses proven logic of automatic on board safety system The anomalies such as exceeded limits on selected parameters or unexpected stage separation are detected by the on board control system that triggers the shut down of all engines and ballistic fall of the vehicle back to earth An additional flight abort system of Ariane type has been added to allow to shut down the launch vehicle engines by a remote command sent from the ground 1 RTSTs antenna 3 pieces 2 SSN antenna 2 pieces Figure A5 4 Antennas location on the 3 stage Arianespace January 2006 Soyuz CSG User s Manual Issue Draft A5 1 6 Fregat Upper Stage The Fregat upper stage is an autonomous and flexible stage designed to operate as an orbital vehicle It extends the capability of the lower three stages
80. aunch windows of each co passenger to define combined launch window In order to allow the possibility of several launch attempts and account for any weather or technical concern resolution a minimum launch window of 45 minutes is recommended The actual launch window of each mission and its impact on performance will be calculated as part of mission analysis activities 2 18 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 8 Spacecraft orientation during the flight During coast phases of the flight the Attitude Control Systems allow the launch vehicle to satisfy a variety of spacecraft orbital requirements including thermal control maneuvers sun angle pointing constraints and telemetry transmission maneuvers On the contrary the active parts of the mission like ascent boost phases and upper stage orbital burns and TM maneuvers will determine the attitude position of spacecraft The best strategy to meet satellite and launch vehicle constraints will be defined with the Customer during the Mission Analysis process 2 9 Separation conditions After injection into orbit the launch vehicle Attitude Control System is able to orient the upper composite to any desired attitude s and to perform separation s in various modes e 3 axis stabilization e longitudinal spin After completion of the separation s the launch vehicle carries out a last manoeuvre to avoid subsequent collis
81. cation Decision to fueling Figure 7 5 The 7 26 SIC swibching to the on board power supply Y Am Fregat TM ON v ule 50 3 2 Seconds 50 AQ a0 20 t s tints SIC status READY MISE SIC umbilical disconnect T LIFT OFF H ins Fregat status READY 5mi s Fregat transfer to onboard power oe Fregat umbilical disconnect v Fregat IP release Y 14Smiits LV TM ON LV status READY Key to start B Full thrust level Y Intermediate thrust level V D TE Preliminary thrust level Y N purge of propellant feedlines W mas Drainage filling of feedlines Key to drainage Y m Tank pressurizatian v P Flight program upload LV transfor to on board power W Engine ignition 1 1 Launch command V Ten ots Range status READY e i countdown chronology Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 5 5 5 Launch postponement Three different situations must be considered for launch postponement depending on the decision time e Decision before LV fueling 4h18mm The new launch date can be scheduled within ten days following LV installation on the pad Beyond those ten days the launch vehicle would require additional verification in the LV integration building after demating of the Upper Composite e Decision after the beginning of the fueling sequence after 4h18mm and bef
82. chanical fluxes into the main structure derived from the table of maximum QSLs and taken into account the additional line loads peaking The qualification factors given previously shall be considered 4 3 3 2 Sinusoidal vibration tests The objective of the sine vibration tests is to verify the spacecraft secondary structure dimensioning under the flight limit loads multiplied by the appropriate safety factors The spacecraft qualification test consists of one sweep through the specified frequency range and along each axis Flight limit amplitudes are specified in Chapter 3 and are applied successively on each axis The tolerance on sine amplitude applied during the test is 10 A notching procedure may be agreed on the basis of the latest coupled loads analysis CLA available at the time of the tests to prevent excessive loading of the spacecraft structure However it must not jeopardize the tests objective to demonstrate positive margins of safety with respect to the flight loads Sweep rates may be increased on a case by case basis depending on the actual damping of the spacecraft structure This is done while maintaining the objective of the sine vibration tests Table 4 4 Sinusoidal vibration tests levels Frequency Qualification Acceptance range Hz levels 0 peak g levels 0 peak g 0 65 i Longitudinal Sweep rate rate 0 5 oct min Arianespace November 2005 4 9 Design And Verification Requirements Soyuz C
83. chment point Slosh model under 0 g Fixed mass attachment point if any Natural frequency of fundamental sloshing mode Hz Pendulum attachment point Slosh model under 1 g Fixed mass attachment point if any Natural frequency of fundamental sloshing mode Hz Arianespace January 2006 pendulum mass ko pendulum length Gen pendulum mass ks pendulum tength m PF A1 7 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft Pressurant helium Tanks 1 2 3 Indicate Mass of total pressurant gas TBD kg Number of pressurant tanks TBD A1 8 Arianespace January 2006 Soyuz CSG Manual Application to use Issue Draft Arianespace s launch vehicle A1 3 6 Mechanical I nterfaces A1 3 6 1 Customer using Arianespace standard adapters A1 3 6 1 1 Interface geometry Provide a drawing with detailed dimensions and nominal tolerances showing the spacecraft interface ring the area allocated for spring actuators and pushers umbilical connector locations and supports the area allocated for separation sensors if any equipment in close proximity to the separation clampband superinsulation plume shields thrusters A1 3 6 1 2 Interface material description For each spacecraft mating surface in contact with the launcher adapter and the clampband indicate material roughness flatness surface coating rigidity frame only inerti
84. cs outside these domains please contact Arianespace 4 2 3 2 Static unbalance The centre of gravity of the spacecraft must stay within a distance d x 15 mm from the launcher longitudinal axis Higher offsets can be accommodated but must be compensated on the LV side and must therefore be specifically analysed 4 2 3 3 Dynamic unbalance There is no predefined requirement for spacecraft dynamic balancing with respect to ensuring proper operation of the LV However these data have a direct effect on spacecraft separation To ensure the separation conditions in spin up mode described in the Chapter 2 the maximum spacecraft dynamic unbalance corresponding to the angle between the spacecraft longitudinal geometrical axis and the principal roll inertia axis shall be 1 degree 4 2 Arianespace January 2006 Soyuz CSG User s Manual Design And Verification Requirements Issue Draft 4 2 3 4 Frequency Requirements To prevent dynamic coupling with fundamental modes of the LV the spacecraft should be designed with a structural stiffness which ensures that the following requirements are fulfilled In that case the design limit load factors given in next paragraph are applicable Lateral frequencies The fundamental frequency in the lateral axis of a spacecraft hard mounted at the interface must be as follows with an off the shelf adapter gt 15 Hz for spacecraft mass lt 5000 kg No local mode should be lower than th
85. cy and the day to day life of the CSG is managed by the French National Space Agency Centre National d Etude Spatiales CNES on behalf of the European Space Agency The CSG mainly comprises e CSG arrival area through the sea and air ports managed by local administration e The Payload Preparation Complex Ensemble de Preparation Charge Utile EPCU shared between three launch vehicles e Upper Composite Integration Facility UCIF dedicated to each launch vehicle e The dedicated Launch Sites for Ariane Soyuz and Vega each including Launch Pad LV integration buildings Launch Centre CDL Centre de Lancement and support buildings e The Mission Control Centre MCC or CDC Centre de Controle The Soyuz Launch Site Ensemble de Lancement Soyuz ELS is located some 10 km North West of the existing Ariane 5 launch facilities ELA3 and of the future Vega launch facilities installed in place of the previous ELA1 The respective location is shown in Figure 6 2 General information concerning French Guiana European Spaceport Guiana Space Center CSG and General Organization are presented in the presentation of Satellite Campaign Organisation Operations and Processing CD ROM SCOOP 2003 Buildings and associated facilities available for spacecraft autonomous preparation are described in the Payload Preparation Complex EPCU User s Manual Issue 8 0 2003 available also on CD ROM Arianespace January 2006 Soyuz C
86. d equipment and propellant e additional shipment of S C support equipment from Cayenne to CSG and return e extra working shift e campaign extension above contractual duration e access to offices and LBC outside working hours without AE CSG support during the Campaign duration e chemical analysis gas fluids and propellants except Xenon e S C weighing e bilingual secretary e technical photos e film processing e transmission of TV launch coverage to Paris e transmission of TV launch coverage to the point of reception requested by the Customer internet video corner during the spacecraft campaign e onboard camera Arianespace January 2006 A3 7 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters STANDARD PAYLOAD ADAPTERS Annex 4 Arianespace January 2006 A4 1 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft A4 1 Adapter 937 SF A4 2 The adapter 937 SF was developed by EADS CASA within the framework of the Mars Express launch services program and is qualified for ground and flight operations on the Soyuz LV It is a composite structure in the form of a truncated cone with a diameter of 937 mm at the level of the spacecraft separation plane see Figure TBD The upper ring that interfaces with the spacecraft and the eight lower brackets which interface with the Fregat are made of aluminum alloys whereas the conical part is a classical sandwich with CFRP skins and an aluminum honeycomb
87. d for the new industrial partners Soyuz s major subcontractors and suppliers are certified in accordance with government and industry regulations that comply with the international requirements of the ISO 9001 9002 2000 standard Their quality system is proven by the number of flights accomplished and by the high level of reliability achieved It should be noted that the similar quality rules are applied to the three stage Soyuz as for manned flights to the nternational Space Station The system is based on the following principles and procedures A Appropriate management system The Arianespace organization presents a well defined decisional and authorization tree including an independent Quality Directorate responsible for establishing and maintaining the quality management tools and systems and setting methods training and evaluation activities audits The Quality directorate representatives provide un interrupted monitoring and control at each phase of mission hardware production satellite LV compliance verification and launch operations B Configuration management traceability and proper documentation system Arianespace analyses and registers the modifications or evolutions of the system and procedures not to affect the hardware reliability and or interfaces compatibility with Spacecraft The reference documentation and the rigorous management of the modifications are established under the supervision of the quality depar
88. dBm Field strength at antenna receive dBu V M Type Location Gain Pattern Arianespace January 2006 A1 11 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft The spacecraft transmission plan shall also be supplied as shown in table below Source Function During After fairing In transfer On station preparation jettisoning orbit on until 20s launch pad after separation soo sz o ob seo o o d dl Provide the spacecraft emission spectrum A1 3 8 3 Spacecraft ground station network For each satellite ground station to be used for spacecraft acquisition after separation nominal and back up stations indicate the geographical location latitude longitude and altitude and the radio electrical horizon for TM and telecommand and associated spacecraft visibility requirements A1 3 9 Environmental characteristics Provide the following e thermal and humidity requirements including limits of environment during launch preparation and flight phase dissipated power under the fairing during ground operations and flight phase maximum ascent depressurization rate and differential pressure contamination constraints and contamination sensible surfaces purging requirements if any Indicate the following e Specific EMC concerns e g lightning RF protection e spacecraft electrical field susceptibility levels e spacecraft sensitivity to magnetic fields if any A1 12
89. e CSG except during transportation and handling During transport mainly by cars and handling of the non flight hardware and support equipment as well as spacecraft in its container the following dimensioning loads at the interface with platform shall be taken into account e Longitudinal QSL direction of motion 1g e Vertical QSL with respect to the Earth 1g ig e Transverse 0 4g Details on the mechanical environment of the spacecraft when it is removed from its container are given in Chapter 3 6 3 2 Power Supply All facilities used by the Customer for spacecraft activity during autonomous and combined operations are equipped with an uninterrupted power supply category III For non critical equipment like general lighting power outlets site services etc a public network 220 V 50 Hz Category I is used Category II is used for the equipment which must be independent from the main power supply but which can nevertheless accept the fluctuation a few milliseconds or interruptions of up to 1 minute gantries air conditioning lighting in hazardous and critical areas inverter battery charger etc The category III is used for critical equipment like S C EGSE communication and safety circuits etc The CSG equipment can supply current of European standard 230V 380V 50 Hz or US Standard 120V 208V 60 Hz More detailed characteristics of the power network are presented in the EPCU User s Manual 6 20 Arian
90. e first fundamental frequencies Longitudinal frequencies The fundamental frequency in the longitudinal axis of a spacecraft hard mounted at the interface must be as follows with an off the shelf adapter gt 35 Hz for spacecraft mass lt 5000 kg No local mode should be lower than the first fundamental frequencies 4 2 4 Dimensioning Loads 4 2 4 1 The design load factors The design and dimensioning of the spacecraft primary structure and or evaluation of compatibility of existing spacecraft with Soyuz launch vehicle shall be based on the design load factors The design load factors are represented by the Quasi Static Loads QSL that are the more severe combinations of dynamic and steady state accelerations that can be encountered at any instant of the mission ground and flight operations The QSL reflects the line load at the interface between the spacecraft and the adapter or dispenser The flight limit levels of QSL for a spacecraft launched on Soyuz and complying with the previously described frequency requirements and with the static moment limitation are given in the Table 4 1 Arianespace November 2005 4 3 Design And Verification Requirements Soyuz CSG User s Manual Issue Draft Table 4 1 Design limit load factors QSL g tension compression max 0 4 eR ee EUR EE dynamic pressure Qmax max 1 8 8 IRIS 3 maximal acceleration max 3 6 emeen p CDS mme and second stages
91. e responsibility After delivery all these parts to UCIF and their verification and acceptance the combined operations readiness review BT POC authorizes the combined operations The combined operations include the following activities Final preparation of the Spacecraft Mating of the Spacecraft onto the adapter dispenser Spacecraft stack and associated verification Integration of the Spacecraft stack on the already filled Fregat and associated verification Constitution of the Upper Composite with encapsulation of the Spacecraft stack in the vertical position Umbilical lines verification 75 5 4 2 Transfer to launch pad After the Transfer Readiness Review the Upper Composite is transferred by road to the Launch Pad The duration of this transfer is approximately TBD hours 7 24 Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 5 5 Launch pad operations 7 5 5 5 1 Launch Pad Preparation Activities The setup of Spacecraft COTE and the verification of the launch pad ground segment are performed as early as possible in the campaign A countdown chronology rehearsal based on the launch countdown procedures is conducted to allow teams to get familiar with nominal and abort procedures 7 5 5 5 2 Final integration on the launch pad After its arrival on the launch pad the upper composite is placed on the top of the third stage by the launch pad traveling crane
92. e test configuration the flight hardware the dedicated harness and or the functional simulator will be used Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft 5 6 2 2 Spacecraft simulator The spacecraft simulator used to simulate spacecraft functions during pre integration tests and ground patch panel cables will be provided by the Customer The electrical interface of the functional satellite simulator shall simulate the spacecraft output input circuit that communicates with the adapter umbilical lines during validation tests It shall be integrated in a portable unit with a weight not higher than 25 kg and dimensions less than 400 x 600 x 400 mm The simulator can be powered from external source 5 6 2 3 Spacecraft EGSE The following Customer s EGSE will be used for the interface validation tests e OCOE spacecraft test and monitoring equipment permanently located in PPF Control rooms and linked with the spacecraft during preparation phases and launch even at other preparation facilities and launch pad e COTE Specific front end Check out Equipment providing spacecraft monitoring and control ground power supply and hazardous circuit s activation SPM The COTE follows the spacecraft during preparation activity in PPF HPF and UCIF During launch pad operation the COTE is installed in the launch pad rooms under the launch table The spacecraft COTE is linked to the OCOE by data lines
93. ections The third stage of the Soyuz is powered by the RD 0110 engine see Figure A5 3 The LOX and kerosene tanks will be modified to accommodate the more powerful RD 0124 engine In fact since the RD 0110 and RD 0124 engines have the same thrust the same stage structure can accommodate both The RD 0110 engine is powered by a single turbopump spun by gas from combustion of the main propellants in a gas generator These combustion gases are recovered to feed four vernier thrusters that handle attitude control of the vehicle The LOX tank is pressurized by the heating and evaporation of the oxygen while the kerosene tank is pressurized by combustion products from the gas generator The RD 0124 engine is a staged combustion engine powered by a multi stage turbopump spun by gas from combustion of the main propellants in a gas generator These oxygen rich combustion gases are recovered to feed the four main combustion chambers where kerosene coming from the regenerative cooling circuit is injected Attitude control is provided by main engine activation along one axis in two planes LOX and kerosene tanks are pressurized by the heating and evaporation of helium coming from storage vessels located in the LOX tank An interstage truss structure connects the core stage with the third stage thereby allowing for the ignition of the third stage before separation of the second In fact this ignition assists the separation of the second stage
94. ed cleanliness in the fairing is ensured through the overpressure generated by the fairing ventilation Specific means can be provided TBC to ensure access from a protected area The same procedures is applicable to the optional radio transparent windows The radio transparent window may be replaced by RF repeater antenna The access and RF transparent window areas are presented in Figure 5 3 5 3 3 Special on fairing insignia A special mission insignia based on Customer supplied artwork can be placed by Arianespace on the cylindrical section of the fairing The dimensions colors and location of each such insignia are the subject to mutual agreement The artwork shall be supplied not later then 6 months before launch Arianespace January 2006 5 3 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft 5 3 4 Payload compartment description 5 4 Nose fairing description The ST fairing consists of a two half shell carbon fiber reinforced plastic CFRP sandwich structure with aluminum honeycomb core The total thickness is approximately 25 mm A 20 mm thick thermal cover made of polyurethane foam with a protective liner is applied to the internal surface of the cylindrical part of the fairing The separation system consists of longitudinal and lateral mechanical locks linked together by pushing rods and connected to pyro pushers 4 vertical jacks powered by a pyrotechnic gas generator are used for opening and rotation
95. ed shut down profile is implemented to reduce the transient loads at the end of the third stage flight Arianespace January 2006 3 1 Environmental conditions Soyuz CSG User s Manual Issue Draft 3 2 Mechanical environment 3 2 1 Steady state acceleration 3 2 1 1 On ground The flight steady state accelerations described hereafter cover the load to which the spacecraft is exposed during ground preparation 3 2 1 2 In flight During flight the spacecraft is subjected to static and dynamic loads Such excitations may be of aerodynamic origin e g wind gusts or buffeting at transonic velocity or due to the propulsion systems e g longitudinal acceleration thrust buildup or tail off transients or structure propulsion coupling etc Figure 3 1 shows a typical longitudinal static acceleration time history for the LV during its ascent flight The highest longitudinal acceleration occurs just before the first stage cutoff and does not exceed 4 3 g The highest lateral static acceleration may be up to 0 4 g at maximum dynamic pressure and takes into account the effect of wind and gust encountered in this phase The accelerations produced during Fregat flight are negligible and enveloped by the precedent events Figure 3 1 Typical Longitudinal Steady state Static Acceleration first three stages flight 3 2 Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft 3 2 2 Sine
96. efer as well to Chap 2 4 1 4 The Soyuz mission profile can be adapted to satellites which total mass exceeds or is lower than the standard GTO LV s performance It is applicable to satellites with liquid propulsion systems giving the possibility of several transfer burns to the GEO and which tank capacity allows the optimal use of the performance gain Satellite mass lower than standard GTO LV performance In that case the LV injects the satellite on an orbit with a higher apogee or a lower inclination requiring a lower velocity increment AV to reach the GEO The satellite propellant gain can be used for lifetime extension or for an increase of the satellite dry mass Satellite mass higher than standard GTO LV performance In that case the LV injects the satellite on an orbit with a lower apogee The satellite realizes then a Perigee Velocity Augmentation maneuver using proper extra propellant The overall propulsion budget of the mission translates in a benefit for the spacecraft in terms of lifetime for a given dry mass or in terms of dry mass for a given lifetime compared to the standard GTO injection profile TO BE ISSUED LATER Figure 2 6 Typical Super Sub GTO performance as function of altitude of apogee Arianespace January 2006 2 9 Performance and launch mission Soyuz CSG User s Manual Issue Draft 2 4 1 3 Direct GeoSynchronous equatorial Orbit Refer as well to Chap 2 4 1 4 The Soyuz launch vehicle can in
97. ellite DG Ensures the Arianespace s CM Responsible for preparation Chief Operating Officer commitments fulfillment Mission Director and execution of the launch Flight Director during final Chef de Mission campaign and final Directeur G n ral countdown countdown supported by DTC COEL Responsible for the ACU COEL s deputy in charge of all Launch Site Operations preparation activation and Payload Deputy interface operations between Manager checkout of the launch Adjoint Charge Utile S C and L V Chef des Op rations vehicle and associated Ensemble de facilities Coordinates all Lancement operations on the launch pad during final countdown CPAP Launch vehicle authority RCUA Responsible for the Arianespace coordinates all technical Arianespace contractual aspects of the Production Project activities allowing to state Payload Manager launch Manager Chef de the L V flight readiness Responsable Charge Projet Arianespace Utile Arianespace Production DTC Chairman of RAV and RAL Directeur Technique Central CG D Ensures the CSG s DDO Responsible for the Range Director commitments fulfillment Range Operations preparation activation and Manager Directeur use of the CSG facilities and Des Op rations down range stations and their readiness during launch campaign and countdown RMCU Responsible for EPCU RSG Responsible for the Payload facilities maintenance and technical Ground Safety applicatio
98. en the LP room connector C20 and the Fregat interstage section connectors X347 and X348 This segment is 180 TBC meters long The customized section is configured for each mission It consists of the following segments e The one between the spacecraft interface J1 and J2 and the connectors SHO1 X347 and X348 e he one between the LP room connectors C1 C2 C3 C4 and C20 and the Customer COTE in the LP room The Customer will provide the harness for this segment The LV to Launch Pad harness layout is shown in Figure 5 A description of these lines and their interfaces is given in Table 5 3 Arianespace January 2006 5 11 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft LEGEND Permanent Lines mi LV customized lines Adapter 4 48 Zi x o vM Customized Lines provided by the Customer FREGAT des KT100 Interstage ee Section e no X 347 X 348 LT ne y IT STAGE Sues i iei o amp II STAGES LAUNCH TABLE MEN R15 Figure 5 5 The LV to Launch Pad harness layout 5 12 Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft Table 5 3 Umbilical lines description TBC Spacecraft electrical Type of Wire Available Signals Harness designation Nominal umbilical lines KTO11 Spacecraft 14 TBC twisted
99. ent COTE racks compatible with the launch pad installation access door s and passive repeater or RF window are available as options A3 4 Launch operations Arianespace shall provide e all needed launch vehicle autonomous preparation integration verification and installation e launch vehicle spacecraft combined operations e launch pad operations including countdown and launch e flight monitoring tracking and reporting A3 5 Safety assurance As defined in chapter 7 A3 6 Quality assurance A3 2 As defined in chapter 7 Arianespace January 2006 Soyuz CSG User s Manual Items and services for an Issue Draft Arianespace launch A3 7 General Range Support GRS The General Range Support provides the Customer on a lump sum basis with a number of standard services and standard quantities of fluids see list hereafter Request s for additional services and or supply of additional items exceeding the scope of the GRS can be accommodated subject to negotiation between Arianespace and the Customer A3 7 1 Transport Services A3 7 1 1 Personnel transportation Transport from and to Rochambeau Airport and Kourou at arrival and departure as necessary A3 7 1 2 Spacecraft and GSE transport between airport or harbor and PPF Subject to advanced notice and performed nominally within normal CSG working hours Availability outside normal working hours Saturdays Sundays and public holidays is Subject to adv
100. er are based on mature Russian missiles technology The use of a digital control system provides e Improved flexibility and efficiency of the flight The Soyuz attitude control system ACS is capable of handling the aerodynamic conditions generated by the larger fairing The Soyuz is able to perform in flight roll maneuvers as well as in plane yaw steering dogleg maneuvers e Improved accuracy The use of an IMU provides the vehicle with more accurate navigation information and the computer allows to recover from deviations in the flight path Introduction of a satellite based navigation GPS update during the ascent flight can serve to mildly correct any drift or inaccuracies in the IMU measurements and further refine the accuracy of the initial injection orbit In any case it should be noted that the Fregat with its own independent IMU and on board computer corrects inaccuracies resulting from the ascent flight profile However the advantage of a more accurate lower composite flight will result in a lower propellant consumption of the Fregat to correct the errors and an actual improvement on certain orbits especially LEO Arianespace January 2006 A5 5 A5 1 5 2 Telemetry A digital telemetry system with transmitters operating in S band compatible with CSG ground network is located in the equipment bay of the third stage of the Soyuz The health monitoring parameters are downlinked to ground stations along the flight p
101. er the same at the same time These orders are supplied from dedicated battery and they are segregated from the umbilical links and other data links passing through dedicated connectors This pyro order is compatible with the initiator 1 A 1 W 5 min TBC with a resistance of the bridge wire equal to 1 05 Q 0 15 Q The one way circuit line resistance between the Fregat adapter interface and the spacecraft initiator must be less than 0 22 Q To ensure safety during ground operations two electrical barriers are installed in the Fregat pyrotechnic circuits The first barrier is closed 5 seconds before lift off and the second one is closed 20 seconds after lift off During flight the pyrotechnic orders are monitored by the Fregat telemetry system 5 16 Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft NOMINAL REDUNDANT M SPACECRAFT 14 100 KW LES a p KW For one way R 0 15 W ADAPTER BE T 113 ME DNE FREGAT CARBIO EN Nes Hall effect sensors for orders dating V1 V2 V3 6 MN Safety electrical barriers closed at HO 209 TM NE 1 S2 S3 Safety electrical barriers P closed at HO 5 s Battery PF 336 Principle of safety electrical Principle of pyrotechnic orders commutation barriers commutation The commands A1 B1 and C1 are elaborated by the 2 3 logic NOMINAL
102. erformance data for SSOs are presented in Figure 2 7 as a function of altitude Performance data for polar orbits are presented in Figure 2 8 2 4 2 2 Other circular orbits Almost all orbit inclinations can be accessed from the CSG Supply missions to the International Space Station satellite constellations deployment and scientific missions can also be performed by Soyuz from the CSG LV performance data for circular orbit missions with inclination 56 and 63 deg and altitudes between 400 and 25 000 km are presented in Figure 2 9 Arianespace January 2006 2 11 Performance and launch mission Soyuz CSG User s Manual Issue Draft 5300 104 5100 103 SSO inclination ae 4900 0 101 m g 4700 D 100 4500 5 E 99 4300 o S 98 7 4100 D 9 9 3900 Be 3700 95 3500 94 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1600 1700 1800 Circular Orbit Altitude km Figure 2 7 Preliminary LV performance for SSO orbits to be considered for trade off studies only For precise data please contact Arianespace 5100 5000 4900 4800 LV Performance kg 4700 4600 4500 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 1600 1700 Circular Orbit Altitude km Figure 2 8 LV performance for polar orbits to be c
103. es e SI Payload Processing Facility PPF located at the CSG Technical Centre e S3 Hazardous Processing amp Upper Composite Integration Facilities HPF UCIF located near to the ELA3 e S2 S4 Hazardous Processing Facilities HPF for pyro devices located near to the ELA3 e S5 Payload Hazardous processing facilities PPF HPF The complex is completed by auxiliary facilities the Propellant Storage Area ZSE Pyrotechnic Storage Area ZSP and chemical analysis laboratory located near the different EPCU buildings All EPCU buildings are accessible by two lane tarmac roads with maneuvering areas for trailers and handling equipment X hy PPF SS Area S1 HPF Area S3 Area S2 S4 r x PPF HPF Area S5 Figure 6 3 Payload Preparation Complex EPCU location Arianespace January 2006 6 5 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 2 2 1 S1 Payload Processing Facility The S1 Payload Processing Facility consist of buildings intended for the simultaneous preparation of several spacecraft It is located on the north of the CSG Technical Centre close to Kourou town The area location far from the launch pads ensures unrestricted all the year round access The area is completely dedicated to the Customer launch teams and is use for all non hazardous operations i i i f bare i i SIRIUS l JUPITER 2 po roue Ex ong V n noo Zz V d CEE y En les Space Es g
104. espace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 3 3 Communications Network 6 3 3 1 0perational data network The existing CSG network will extend its capability to cover new Soyuz facility and will provide the same level of quality Data links are provided between the Customer support equipment located in the different facilities and spacecraft during preparation and launch The Customer OCOE in the PPF Control room is connected with the satellite and COTE in the HPF UCIF LP Customer room catacomb Launch Centre and Mission Control Centre DMS CPS Console at Jupiter 2 The Customer is responsible for providing correct signal characteristics of EGSE to interface with the CSG communication system Customer data transfer is managed through the MULTIFOS system MULTIplex Fibres Optiques Satellites based on TBD dedicated optical fiber links Three main dedicated subsystems and associated protected networks are available STFO Syst me de Transmission par Fibres Optiques Transmission of TM TC between Customer s EGSE and satellite can be performed as follows e RF signals in S C and Ku frequency band e Base band digital rate up to 1 Mb s signals e Base band analog rate up to 2 Mb s signals ROMULUS R seau Op rationnel MULtiservice Usage Spatial Transmission of operational signals between Customer EGSE located in PPF and Mission Control Centre DMS console Green Red status P
105. ft and EGSE 5 18 A direct reception of RF emission from the spacecraft antenna can be provided as an optional service requiring additional hardware installation on the fairing and on the launch pad This option allows users to check the spacecraft RF transmission on the launch pad during countdown The following configurations are possible e Use of radio transparent windows on the fairing and of a repeater on the launch mast e Use of a passive repeater composed of 2 cavity back spiral antenna under the fairing and on its external surface with direct transmission to the spacecraft EGSE Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft SPACECRAFT es oN FA OM tA an um ET 7 lt a d SHO1 S C Adapter un E 3 D 1 Ill STAGE EE amp II STAGES LAUNCH TABLE Ti bf B E dI i 5 1 Specific strap to ground the shield Figure 5 7 Spacecraft grounding network diagram Arianespace January 2006 5 19 Spacecraft interfaces Soyuz CSG User s Manual 5 6 Issue Draft Interface verifications 5 6 1 Prior to the launch campaign 5 6 1 5 6 1 Prior to the initiation of the launch campaign the following interface checks shall be performed Specific LV hardware for these tests is provided according to the contractual provision 1 Mechanical fit checks The objectives of this fit check are to confirm that the s
106. fter Fregat separation The RDM system is switched on 20 minutes before the launch and is functional for a range up to 8000 km It comprises one transmitter one receiver and two antennas Each antenna ensures both transmission and reception The PPU system is designed for a range between 1000 and 45 000 km and is switched on during flight when the Fregat reaches an altitude higher than 1000 km It comprises one transmitter and one receiver each associated with one antenna Average power 0 075 W for a 0 7 us impulse 100 W Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft E 200 gt N E rss 68 z 8 d VES E E Sas 8 100 E 3 50 0 1 00E 05 1 00E 06 1 00E 07 1 00E 08 1 00E 09 1 00E 10 1 00E 11 Frequency Hz Figure 3 8 Spurious Radiation by Launch Vehicle and Launch Base Narrow band Electrical field TBD Arianespace January 2006 3 17 Environmental conditions Soyuz CSG User s Manual Issue Draft 3 6 Environment verification The Soyuz and Fregat telemetry system capture the low and high frequency data during the flight from the sensors installed on the fairing upper stage and adapter and then relay this data to ground station These measurements are recorded and pr
107. fy the compatibility with the launch vehicle This activity can be formalised in a Compatibility Agreement for a Spacecraft platform 7 4 1 1 nterface Management The technical interface management is based on the Interface Control Document DCI Document de Contr le d I nterface which is prepared by Arianespace using inputs from the Technical Specification of the Launch Service Agreement and from the Application to Use Arianespace LV DUA provided by the Customer the DUA template is presented in Annex 1 This document compiles all agreed Spacecraft mission parameters outlines the definition of all interfaces between the launch system LV operations and ground facilities and Spacecraft and illustrates their compatibility Nominally two major updates of the DCI are provided in the course of the mission after the release of the initial version Issue 0 as a consequence of the LSA signature e An update after the preliminary mission analysis Issue 1 e An update after the final mission analysis review Issue 2 All modifications of the DCI are approved by Arianespace and the Customer before being implemented This document is maintained under configuration control until launch In the event of a contradiction the document takes precedence over all other technical documents Arianespace January 2006 7 5 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 4 2 Mission Analysis 7 4 2 1 Introduc
108. g system Beepers are provided to the Customers during their campaign Videoconference communication system Access to the CSG videoconference studios located in the EPCU area is available on Customer specific request 6 3 3 3 Range information systems Time distribution network The Universal Time UT and the Countdown Time TD signals are distributed to the CSG facilities from two redundant rubidium master clocks to enable the synchronization of the check out operations The time coding is IRIG B standard accessed through BNC two wire connectors or RJ 45 plugs Operational Reporting Network CRE The Reporting System is used to handle all green red generated during final countdown Closed Circuit Television Network CCTV The PPF HPF and UCIF are equipped with internal closed circuit TV network for monitoring security and safety activities CCTV can be distributed within the CSG facility to any desired location Hazardous operations such as fuelling are recorded This system is also used for distribution of launch video transmission Public One Way Announcement System SONO The public one way announcement system ensures emergency announcement alarms or messages to dedicated CSG locations The system is activated through the consol of a Site managers 6 24 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 3 4 Transportation and Handling For all intersite transportation incl
109. ganic deposit generated by the Fregat s attitude control thrusters plume on the adjacent spacecraft surfaces does not exceed 2 mg m for a TBD minutes mission duration with typical altitude and spin manoeuvres The non volatile organic contamination generated during ground operations and flight is cumulative 3 14 Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft 3 5 Electromagnetic environment The LV and launch range RF systems and electronic equipments are generating electromagnetic fields that may interfere with satellite equipment and RF systems The electromagnetic environment depends from the characteristics of the emitters and the configuration of their antennas 3 5 1 LV and range RF systems Launcher The basic RF characteristics of the LV transmission and reception equipment are given in Table 3 7 Range The ground radars local communication network and other RF mean generate an electromagnetic environment at the preparation facilities and launch pad and together with LV emission constitute an integrated electromagnetic environment applied to the spacecraft The EM data are based on the periodical EM site survey conducted at CSG 3 5 2 The electromagnetic field The intensity of the electrical field generated by spurious or intentional emissions from the launch vehicle and the range RF systems do not exceed those given in Figure 3 8 These levels are measured at adapter Fregat i
110. gn A3 7 4 Cleanliness monitoring Continuous monitoring of organic deposit in clean room with one report per week Continuous counting of particles in clean room with one report per week Arianespace January 2006 A3 5 Items and services for an Soyuz CSG User s Manual Arianespace launch Issue Draft A3 7 5 Fluid and Gases Deliveries Gases Type Quantity Compressed air Industrial dedicated local As necessary network GN2 N50 dedicated local network de necessary available at 190 ar GN2 N30 dedicated network in S3 As necessary available at 190 area bar Ghe N55 dedicated local network As necessary available at 180 or 350 bar Fluid Type Quantity LN2 N30 As necessary IPA MOS SELECTIPUR As necessary Water Demineralised As necessary Note Any requirement different from the standard fluid delivery different fluid specification or specific use is subject to negotiation A3 7 6 Safety Equipment Type Quantity Safety equipment for hazardous Standard As necessary operations safety belts gloves shoes gas masks oxygen detection devices propellant leak detectors etc A3 7 7 Miscellaneous One video tape with launch coverage NTSC PAL or SECAM will be provided after the launch Office equipment e no break power 10 UPS 1 4 kVA at S1 or S5 offices for Customer PCs e copy machines 2 in S1 or S5 Area 1 for secretarial duties 1 fo
111. he Fregat upper stage and eencapsulation under the fairing in vertical position Te 2 oi R The dimensions of the hall are properly sized LEES for the integration activity The area is about mr 20 x 20 m and there is 19 m under the rail of EDE the crane The airlock door dimensions are 6 x ied Pe la 18 m Specific operations can be controlled from the TA control rooms on S3C building TE a Figure 6 12 The S3B layout in UCIF configuration Greund tose Lipper fir 6 2 3 2 Soyuz Launch Site ELS Ensemble de Lancement Soyuz The Soyuz launch site is a dedicated area designed for launch vehicle final preparation the upper composite integration with launch vehicle and final launch activities It includes the Launch Pad Zone de Lancement ZL the LV integration building MIK the Launch Control Building CDL Centre De Lancement and support buildings see Fig 6 15 Arianespace January 2006 6 13 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 2 3 2 1 LV Integration Building MIK The MIK is used for the LV s 3 stages and Fregat upper stage storage assembling and test The building is similar to the one used in Baikonur and Plesetsk No spacecraft or combined operations are conducted in this building 6 23 22 Launch Pad The launch pad consists of the metallic support structure integrated with the concrete launch table equipped with the support arms start system
112. hes and signed contracts for more than 250 payloads with some 55 operators customers Arianespace provides each customer a true end to end service from manufacture of the launch vehicle to mission preparations at the Guiana Space Centre and successful in orbit delivery of payloads for a broad range of mission Arianespace as a unique commercial operator oversees the marketing and sales production and operation from CSG of Ariane Soyuz and Vega launch vehicles Arianespace continues the Soyuz commercial operations started in 1999 in Baikonur by Starsem having as of January 2006 a record of 15 successful launches Kourou CSG Figure 1 3 The Arianespace worldwide presence Arianespace January 2006 1 11 Introduction Soyuz CSG User s Manual Issue Draft 1 6 2 Partners 1 12 Arianespace is backed by shareholders that represent the best technical financial and political resources of the 12 European countries participating in the Ariane and Vega programs e 22 Aerospace engineering companies from 10 European countries e 1 Space agency Building on the experience gained by its daughter company Starsem since 1996 with the Soyuz launches from Baikonur the Soyuz operation from CSG results of a transfer of the Soyuz commercial concession to Arianespace that will allow to improve the services provided on the commercial market Starsem is a 50 50 joint venture between Russian and European partners that draws on some of
113. hkin is also the technical authority for the assembled upper composite 1 6 4 4 KB OM V P Barmin Design Bureau for General Engineering was founded in 1941 KBOM specialises in the design and operation of launch facilities space rocket ground infrastructure and in orbit processing equipment KB OM is in charge of the development of the Russian systems for the Soyuz launch zone at the CSG 1 14 Arianespace January2006 Soyuz CSG User s Manual Issue Draft SSC TsSKB Progress Samara Russia Fairing ST Arianespace January 2006 eee NPO Avtomatika EADS Europe Payload Adapter Dispenser NPO Lavotchkine Khimki Russia FREGAT Upper Stage NPO Lavotchkine Khimki Russia Interstage structure RNII KP amp OKB MEI Moscow Russia Tracking systems Ekaterinburg Russia Digital control system for all stages TM system RNII KP Moscow Russia Telemetry System SSC TsSKB Progress Samara Russia 3 stage tanks stage integration tests Voronyezh Mechanical Factory Voronyezh Russia 3 stage engine RD 0110 or RD 0124 SSC TsSKB Progress Samara Russia 2 core stage tanks stage integration tests SSC TsSKB Progress Samara Russia 1 stage boosters tanks stage integration tests AO Motorostroitel Samara Russia 2 stage engine RD 108A AO Motorostroitel Samara Russia 1 stage engines RD 107A I zevsky radiozavod Izevsk Russia Introduction NPO Lavotchki
114. hout the visibility constraint of spacecraft separation are presented in Table 2 2 Actual mission duration will be determined as part of the detailed mission analysis taking into account ground station availability and visibility Arianespace January 2006 2 17 Performance and launch mission Soyuz CSG User s Manual Issue Draft Table 2 2 Typical Mission Duration up to Spacecraft Separation TBD E Altitude Mission Duration Mission km hh mm GTO and Super Sub GTO 20 000 120 000 00 20 01 30 SSO 800 01 00 01 30 Circular orbit 10 000 02 00 02 30 20 000 03 10 03 40 Elliptical orbit 1 000 x 39 464 01 00 02 30 Earth escape mission i 01 15 01 45 Note Mission duration depends on declination requirements 2 7 Launch windows The Soyuz LV can be launched any day of the year any time of the day respecting the specified lift off time The inaccuracy of any planned launch time in a nominal mission scenario is less than one second taking into account all potential dispersions in the launch sequencing and system start ignition processes The launch window is defined taking in to account the satellite mission requirements such as the orbit accuracy or the separation orbital position requirements for the right ascension of the ascending node RAAN and the respective ability of the launch vehicle to recover launch time error In case of shared dual launch Arianespace will taken into account the l
115. i 175 SAN TER NE HELI PAD ant i E pesa PLUTON o il I CENTAURE pone d AS ee Figure 6 4 S1 Area layout The facility is composed of 2 similar main buildings comprising one clean room each separated building for offices laboratory and storage areas The passage between buildings is covered by a canopy for sheltered access between the buildings The storage facility can be shared between buildings Figure 6 5 S1 area composition Arianespace January 2006 6 6 Soyuz CSG User s Manual Guiana Space Centre Issue Draft The S1A is building composed of 1 clean high bay of 490 m that can be shared by two payloads Western and Eastern areas and rooms and laboratories including 3 control room and storage areas The S1B building is composed of 1 clean high bay of 860 m that could be shared by two spacecraft Northern and Southern areas and rooms and storage areas including 4 control rooms Offices are available for spacecraft teams and can accomodate around 30 persons The S1C SIE and SIF buildings provide extension of the S1B office space The standard offices layout allows to accommodate around 30 persons Scale Offices S1 E LBC 1B NORTH HANGAR LBC 4B 27 CLEAN J HALL _ SN A d MM gt esr ee aa l meeting room S1 E Offices S1 C AIR LBC 2B CONDITIONED STORAGE A S LBC 3B Re S1 F Offices E TRANSIT hb HALL a n rr LBC 1 LBC 2 PTS 2 g
116. iews meetings and so on as described in the chapter 7 A3 2 System engineering support A3 2 1 Interface management DCI issue update and configuration control A3 2 2 Mission analysis Arianespace will perform the Mission Analyses as defined in chapter 7 in number and nature A3 2 3 Spacecraft Compatibility Verification Reviewing and approbation of the spacecraft compatibility with the L V through the documentation provided by the Customer test results qualification files A3 2 4 Post launch analysis Injection parameters S C orbit and attitude data Flight synthesis report DEL Arianespace January 2006 A3 1 Items and services for an Soyuz CSG User s Manual Arianespace launch Issue Draft A3 3 Launch vehicle procurement and adaptation Arianespace will supply the hardware and software to carry out the mission complying with the launch specification and the Interface Control Document DCI e one equipped 3 stages Soyuz launch vehicle with one dedicated flight program e one equipped Fregat upper stage with one dedicated flight program e launch vehicle propellants e one payload compartment under the fairing on or inside a dual launch carrying structure e one mission logo installed on the fairing and based on the Customer artwork supplied at L 6 e one adapter dispenser with separation system umbilical interface connector umbilical harnesses and instrumentation e two Check Out Terminal Equipm
117. ight model The release test is performed twice e An analytic demonstration of the qualification of each piece of equipment is conducted This analytic demonstration is performed as follows The release shocks generated at the spacecraft s interface and measured during the two above mentioned tests are compared to the release shock specified envelope The difference derived from the above comparison is then considered to extrapolate the measured equipment base levels to the maximum levels that can actually be observed during clamp band release These extrapolated shock levels are then increased by a safety factor of 3 dB and are compared to each piece of equipment qualification status Note that each unit qualification status can be obtained from environmental qualification tests other than shock tests by using equivalent rules e g from sine or random vibration tests Method Number Two Qualification by heritage An analysis is conducted on the basis of multiple previous clamp band release tests i e on a comprehensive shock database The acceptance test consists of performing a clamp band release under nominal conditions nominal tension of the band etc This single release test is usually performed at the end of the mechanical fit check A flight type adapter with the associated separation systems and consumable items can be provided in support of these shock tests as an optional service 4 12 Arianespace January 2006
118. in max tables and the time history of forces accelerations and deflections as well as L V Spacecraft interface acceleration and force time histories e provides inputs to analyze with Arianespace requests for notching during the Spacecraft qualification tests The results of the CLA allow the Customer to verify the validity of Spacecraft dimensioning and to adjust its qualification test plan if necessary after discussion with Arianespace 7 4 2 2 4 Preliminary Electromagnetic and RF Compatibility Analysis This study allows Arianespace to check the compatibility between the frequencies used by the LV the range and the Spacecraft during launch preparation and flight The analysis is intended to verify that the Spacecraft generated electromagnetic field is compatible with LV and range susceptibility levels and vice versa as defined in Chapter 3 amp 4 of this manual The Spacecraft frequency plan provided by the Customer in accordance with the DUA template is used as input for this analysis The results of the analysis allow the Customer to verify the validity of the Spacecraft dimensioning and to adjust its test plan or the emission sequence if necessary 7 4 2 2 5 Preliminary Thermal Analysis A preliminary thermal analysis is performed if necessary This analysis allows to predict the Spacecraft nodes temperatures during ground operations and flight to identify potential areas of concern and if necessary needed adaptation
119. ing with CSG and Arianespace support The ground equipment is unloaded in the transit hall and the Spacecraft in its container is unloaded in the high bay airlock of the PPF Pyrotechnic systems and any other hazardous systems of the same class are stored in the pyrotechnic devices buildings of the ZSP Hazardous fluids are stored in a dedicated area In the Spacecraft Operations Plan POS the Customer defines the way his equipment should be arranged and laid out in the facilities The Customer states which equipment has to be stored in an air conditioned environment Other equipment will be stored under the open shed Autonomous operations and checks of the Spacecraft are carried out in the PPF These activities include e Installation of the Spacecraft checkout equipment connection to the facilities power and operational networks with CSG support e Removal of the Spacecraft from containers and deployment in clean rooms This also applies for flight spare equipment e Spacecraft assembly and functional tests non hazardous mechanical and electrical tests e Verification of the interface with LV if needed such as electrical fit check e Battery charging The duration of such activities varies with the nature of the payload and its associated tests Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management Phase 2 Spacecraft hazardous operations Spacecraft filling and haza
120. ings and reviews Arianespace January 2006 7 1 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 2 Mission management 7 2 1 Contract organisation The contractual commitments between the launch service provider and the Customer are defined in the Launch Services Agreement LSA with its Statement of Work SOW and its Technical Specification Based on the Application to Use Arianespace launch vehicles DUA Demande d Utilisation Arianespace filled out by the Customer the Statement of work identifies the task and deliveries of the parties and the Technical Specification identifies the technical interfaces and requirements At the LSA signature an Arianespace Program Director is appointed to be the single point of contact with the Customer in charge of all aspects of the mission including technical and financial matters The Program Director through the Arianespace organization handles the company s schedule obligation establishes the program priority and implements the high level decisions At the same time he has full access to the company s technical staff and industrial suppliers He is in charge of the information and data exchange preparation and approval of the documents organization of the reviews and meetings During the launch campaign the Program Director delegates his technical interface functions to the Mission Director for all activities conducted at the CSG An operational link i
121. ink Spacecraft TC TM ROLE NS Optional N A see 5 5 4 T Arianespace will supply the Customer with the spacecraft side interface connectors compatible with equipment of the off the shelf adaptors Optional Jum The Customer will reserve three pins on each connector one for shielding and two for spacecraft telemetry separation monitoring as described hereafter Depending on S C power requirements lines can have to be wired in parallel Arianespace January 2006 5 9 Spacecraft interfaces Soyuz CSG User s Manual 5 10 Issue Draft Flight constraints During the powered phase of the launch vehicle and up to separation of the payload s no command signal can be sent to the payload s or generated by a Spacecraft onboard system sequencer computer etc During this powered phase a waiver can be studied to make use of commands defined in this paragraph providing that the radio electrical environment is not affected After the powered phase and before the spacecraft separation the commands defined in this paragraph can be provided to the spacecraft To command operations on the payload after separation from the launch vehicle microswitches or telecommand systems after 20 s can be used Initiation of operations on the payload after separation from the launch vehicle by a payload on board system programmed before lift off must be inhibited until physical separation HO 1h30 mn Upper stage burn out Separation
122. inly composed of 1 large high bay of 700 m that can be divided in 2 clean bays 4 control rooms and separated office areas the S5A area dedicated to spacecraft fuelling and other spacecraft hazardous processing is mainly composed of 1 clean high bay of 300 m the S5B area dedicated to fuelling large spacecraft and other spacecraft hazardous processing and is mainly composed of 1 clean high bay of 410 m The three halls transfer airlocks and the access corridors have a class 100 000 cleanliness The satellite is transported to the different halls on air cushions or trolleys In addition to the main facility the S5 area comprises the following buildings SSD dedicated to final decontamination activities of satellite fuelling equipment 5E dedicated to the preparation of SCAPE suits and training dressing and cleaning of propulsion teams The entrance to the area is secured at the main access gate Arianespace January 2006 6 11 Guiana Space Centre Soyuz CSG User s Manual Issue Draft S5 C Figure 6 11 PPF HPF S5 layout 6 12 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 2 3 Facilities for combined and launch operations 6 2 3 1 UCI F The building S3B of the S3 area will be used as the Upper Composite Integration Facility In the building the following operations will be performed FUELLING HALL HR e spacecraft and adapter dispenser integration on t
123. inly composed of two Fuelling Halls of 110 m and 185 m and one Assembly Hall of 165 m The S3B building is used as Upper Composite Integration Facility see 6 2 3 1 The S3C building is dedicated to the remote monitoring of the hazardous operations in the S3A and S3B as well as housing of the satellite team during these operations The building is shared with the safety service and Fire brigade The Customer s part of the building is composed of meeting room and Offices The S3E building is used by the spacecraft teams to carry out the passivation operations of the spacecraft propellant filling equipment and decontamination It is composed of one externally open shed of 95 m 26 CLEAN STORAGE AIRLOCK 2 02 FUELLING HALL HR t i 27 HR 2 03 ENCAPSULATION HALL HN 05 0 5m Scale i i i i i i i i i l i 30 23 i Technical room i t 14 FILLING 24 ASSEMBLY 03 HALL i o HAL 12 17 HA 25 r i Visitors i i i I Technical ro m 04 21 m UE 33 35 a CLEA o o a e e 34 09 i AIRLOCK 1 32 i 2 v B 04 02 10 i i 16 08 i 13 se i 09 e Vs Energy I echni m 9 i 15 20 i 18 01 HE HR 1 06 i i i Ca i i i i i i I i i i i i i J I i I I l i I i N 10 AIRLOCK STORAGE 05 11 i i i I i i i i i i I i I I
124. int Telephone System TS A restricted point to point telephone network TS can be used mainly during launch pad operations and countdown exclusively by Customer appointed operational specialists This network is modular and can be adapted for specific Customer request These telephone sets can only call and be called by the same type of dedicated telephone sets Arianespace January 2006 6 23 Guiana Space Centre Soyuz CSG User s Manual Issue Draft I ntercommunication system Intercom e Operational intersite Intercom system IO The operational communication during satellite preparation and launch is provided by independent Intercom system with a hosts at each EPCU facility This system allows full duplex conversations between fixed stations in various facilities conference and listening mode and switch to the VHF UHF fuelling network IE All communications on this network are recorded during countdown e The dedicated Intercom for hazardous operations IE The restricted independent full duplex radio system is available between operator s suits and control rooms for specific hazardous operations such as filling By request this system could be connected to the Operational Intercom OI VHF UHF Communication system The CSG facilities are equipped with a VHF UHF network that allows individual handsets to be used for the point to point mobile connections by voice Paging system CSG facilities are equipped with a pagin
125. ion 2 9 1 Orientation performance The attitude at separation can be specified by the Customer in any direction in terms of e Fixed orientation during the entire launch window or TBC e ime variable orientation dependant on the sun position during the launch window For other specific satellite pointing the Customer should contact Arianespace 2 9 2 Separation mode and pointing accuracy The actual pointing accuracy will result from the Mission Analysis The following values cover Soyuz compatible spacecrafts as long as their balancing characteristics are in accordance with para 4 5 3 They are given as satellite kinematic conditions at the end of separation and assume the adapter and separation system are supplied by Arianespace In case the adapter is provided by the Satellite Authority the Customer should contact Arianespace for launcher kinematic conditions just before separation Possible perturbations induced by spacecraft sloshing masses are not considered in the following values 2 9 2 1 Three Axis stabilized mode The 3 o attitude accuracy for a three axis stabilized mode are e geometrical axis depointing x 1 deg e angular tip off rates along longitudinal axis lt 0 3 deg s e angular tip off rates along transversal axis x 0 3 deg s 2 9 2 2 Spin stabilized mode The Fregat ACS can provide a roll rate around the upper composite longitudinal axis between TBD deg s and 30 deg s clockwise or counterclockwise Higher s
126. ion acoustics and shock The test plan shall include test objectives and success criteria test specimen configuration general test methods and a schedule It shall not include detailed test procedures e A Spacecraft environment test file comprising theoretical analysis and test results following the system level structural load and dynamic environment testing This file should summarize the testing performed to verify the adequacy of the Spacecraft structure for flight and ground loads For structural systems not verified by test a structural loads analysis report documenting the analyses performed and resulting margins of safety shall be provided After reviewing these documents Arianespace will edit the Compatibility Notice that will be issued before the RAV The conclusion of the mechanical and electrical fit check if required between Spacecraft and launch vehicle will also be presented at the RAV Arianespace requests to attend environmental tests for real time discussion of notching profiles and tests correlations Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 4 4 Post launch analysis 7 4 4 1 I njection Parameters During the flight the Spacecraft physical separation confirmation will be provided in real time to the Customer Arianespace will give within 1 hour after the last separation the first formal diagnosis and information sheets to Customer concerning
127. iring preparation eee al Fregat preparation agg Fregat feeling es Bee Payload autonomous preparation Spacecraft processing Spacecraft fueling hasardous operations Payload Combined operations ET Spacecrall mating with Adapter Frnegat Upper Composita encapsulation Upper Composite transher Launch Pad Operations Upper Composite Mating with LV Payload final verification 3d Launch vehicle tests 4h Fregat tests 10h LV rehearsal amp T fueling preparation LV final preparation h LV fueling amp countdown Launch GSE re packing Figure 7 4 Typical Spacecraft operational time schedule Arianespace January 2006 7 21 Soyuz CSG User s Manual Mission integration and Issue 7 5 5 7 22 Draft management 2 Spacecraft autonomous preparation Phase 1 Spacecraft arrival preparation and check out The Spacecraft and its associated GSE arrive at the CSG through one of the entry ports described in Chapter 6 Unloading is carried out by the port or airport authorities under the Customers responsibility in coordination with Arianespace Equipment should be packed on pallets or in containers and protected against rain and condensation After formal procedures the Spacecraft and GSE are transferred by road to CSG s appropriate facilities on the CSG transportation means On arrival at the PPF the Customer is in charge of equipment unloading and dispatch
128. is Arianespace January 2006 2 Performance and launch mission Soyuz CSG User s Manual Issue Draft 2 4 General performance data 2 4 1 Geostationary transfer orbit missions 2 4 1 1 Standard Geostationary Transfer Orbit GTO The geostationary satellites will benefit of the advantageous location of the Guiana Space Centre its low latitude minimizes the satellite on board propellant needed to reach the equatorial plane providing additional lifetime The Soyuz mission consists in a three stages sub orbital ascent and two Fregat burns leading to the injection into the GTO with osculating parameters at separation resulting in a AV requirement on the satellite s propulsion system of approximately 1500 m s Inclination I 7 deg Alttude of perigee Zp 250 km Altitude of apogee Za 35 786 km Argument of perigee 178 deg Notes Injection is defined as the end of upper stage thrust decay Z4 is equivalent to true altitude at first apogee The longitude of the first descending node is usually located around TBD deg West The Soyuz performance for this orbit with the RD 0110 or the RD 0124 3rd stage engine iS 2730 kg and 3060 kg respectively X GTO gt Za 35 786 km MN Zp 250 km T i 7 deg x Figure 2 5 Standard GTO mission profile 2 8 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 4 1 2 Super and sub Geostationary Transfer Orbits R
129. iteria and cleaned if necessary e Once encapsulated and during transfer and standby on the launch pad the upper composite will be hermetically closed and a Class 10 000 TBC air conditioning of the fairing will be provided e On the launch pad access can be provided to the payload The gantry not being air conditioned cleanliness level is ensured by the fairing overpressure Transfer between S C in EPCU and UCIF S ConL V buildings S C Transfer to launch location In CCU Not Zone On launch pad Encapsulated container encapsulated Ee duration 3 h Cleanliness 100 000 class 100 000 10 000 TBC 100 000 10 000 Filtration of air conditioning system standard HEPA H14 DOP 0 3 um 3 4 2 Contamination During all spacecraft ground activities from spacecraft delivery to launch site up to lift off the maximum organic non volatile deposit on the spacecraft surface will not exceed 2 mg m week The organic contamination in facilities and under the fairing is controlled The LV materials are selected to limit spacecraft contamination during flight The non volatile organic deposit on the spacecraft surface generated by the materials outgassing does not exceed 2 mg m The LV systems are designed to preclude in flight contamination of the spacecraft The LVs pyrotechnic devices used by the LV for fairing jettison and spacecraft separation are leak proof and do not lead to any satellite contamination The non volatile or
130. ject a payload directly into Geo Synchronous equatorial Orbit GSO by means of a three burn Fregat mission The injection scheme is the same as the one presented for the GTO mission but with a final Fregat burn to change the inclination and circularize on the GSO The maximum Launch Vehicle performance in GSO is 1340 kg 2 4 1 4 Super GTO and GSO injection While the injection orbit for a single launch on Soyuz can be optimized with a higher apogee and even technically speaking with a launch directly on the GSO the standard injection remains on the standard GTO that provides the customer the full benefit of the compatibility of the two launch systems Ariane and Soyuz 2 10 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 4 2 Circular orbits The typical Soyuz mission includes a three stage sub orbital ascent and two Fregat burns as follows e A first burn for transfer to the intermediate elliptical orbit with an altitude of apogee equal to the target value and e A second Fregat burn for orbit circularization 2 4 2 1 SSO and Polar orbits The earth observation meteorological and scientific satellites will benefit of the Soyuz capability to delivery them directly into the sun synchronous orbits SSO or polar circular orbits The performance on a 660km SSO is 4450 kg TBC with the Soyuz 2 1a The performance on a 660km SSO is 4900 kg TBC with the Soyuz 2 1b LV p
131. kets launched in the world Vehicles of this family that launched both the first satellite Sputnik 1957 and the first man Yuri Gagarin 1961 into space have been credited with more than 1700 launches to date The three stage version known as Soyuz first introduced in 1966 has been launched more than 850 times Due to their close technical similarity same lower three stages the Molniya and Soyuz vehicles are commonly combined together for reliability calculations In the last 25 years they have completed a success rate of 98 196 over more than 950 launches As the primary manned launch vehicle in Russia and the former Soviet Union and as today one of the primary transport to the International Space Station the Soyuz has benefited from these standards in both reliability and robustness The addition of the flexible restartable Fregat upper stage in 2000 allows the Soyuz launch vehicle to perform a full range of missions LEO SSO MEO GTO GEO and escape Table 1 1 shows a timeline of LV Soyuz development Table 1 1 Soyuz LV Family Evolution 1957 1960 R 7A Sputnik Two stage missile used to launch the Sputnik payload no longer in production 1958 1991 Vostok Three stage LV with the block E as third stage no longer in production 1960 Molniya Four stage LV with the block as third stage and block L or ML as upper stage 1963 1976 Voskhod Three stage LV with the block as third stage no longer in producti
132. launch This review is conducted by Arianespace The Customer is part of the review board The following points are addressed during this review e the LV hardware software propellants and consumables readiness including status of non conformities and waivers results of the dress rehearsal and quality report e the readiness of the Spacecraft Customer s GSE voice and data Spacecraft communications network including ground stations and control center e the readiness of the range facilities launch pad communications and tracking network weather forecast EMC status general support services e the countdown operations presentation for nominal and aborted launch and Go No Go criteria finalization e Areview of logistics and public relations activities Arianespace January 2006 7 19 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 4 9 Post flight debriefing CRAL Compte rendu Apres de Lancement 24 hours after the launch Arianespace draws up a report to the Customer on post flight analysis covering flight event sequences evaluation of LV performance and injection orbit and accuracy parameters 7 5 4 10 Launch service wash up meeting At the end of the campaign Arianespace organizes wash up meetings The technical wash up meeting will address the quality of the services provided from the beginning of the project and up to the launch campaign and launch The contractual wash up is o
133. letion of the separation s the launch vehicle carries out a dedicated maneuver to avoid the subsequent collision or the satellite orbit contamination 2 20 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 9 2 4 Multi separation capabilities The Soyuz LV is also able to perform multiple separations with mission peculiar payload dispensers or the internal dual launch carrying structure A conceptual definition of this kind of dispenser is presented in Annex TBD the dual launch carrying structure is defined in chapter 5 In this case the kinematics conditions presented above will be defined through the dedicated separation analysis For more information please contact Arianespace Arianespace January 2006 2 21 Introduction Soyuz CSG User s Manual Issue Draft 1 2 European Space Transportation System 1 2 To meet all Customer s requirements and to provide the highest quality of services Arianespace proposes to Customer a fleet of launch vehicles Ariane Soyuz and Vega Thanks to their complementarities they cover all commercial and governmental mission requirements providing access to the different type of orbits from Low Earth Orbit to Geostationary Transfer Orbit and even to interplanetary one This family approach provides Customers with a real flexibility to launch their spacecrafts and insure in a timely manner their planning for orbit delivery The Soyuz operatio
134. lities to act as one of the entity affecting countdown automatic sequence Arianespace January 2006 6 17 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 2 3 3 Mission Control Centre Technical Centre The main CSG administrative buildings and offices including safety and security service laboratories CNES ESA representative offices are located in the Technical Centre Its location a few kilometres from Kourou on the main road to the launch pads provides the best conditions for management of all CSG activity Along with functional buildings the Technical Centre houses the Mission Control Centre located in the Jupiter building The Mission Control Centre is used for e Management and coordination of final prelaunch preparation and countdown Processing of the data from the ground telemetry network Processing of the readiness data from the launch support team meteo safety Providing the data exchange and decisional process with Go No Go criteria Flight monitoring The spacecraft launch manager or his representatives stay in the Mission Control Centre during prelaunch and launch activities and if necessary can stop the countdown see Chapter 7 5 5 5 4 The Customer will have up to 3 operator s seats 1 monitoring place and room and visitors seats for other Customer s representatives fl A pins mi e er TEN p I tee ces eam 09 i I a eet im umi es i7 al Figure 6
135. loads seen by the spacecraft is assumed Picking loads induced by spacecraft The maximum value of the peaking line load induced by the spacecraft is allowed in local areas to be up to 10 over the dimensioning flux seen by adapter under limit load conditions An adaptor mathematical model can be provided to assess these values 4 2 4 3 Handling loads during ground operations During the encapsulation phase the spacecraft is lifted and handled with its adapter for this reason the spacecraft and its handling equipment must be capable of supporting an additional mass of 110kg The crane characteristics velocity and acceleration are defined in the EPCU User s Manual 4 2 4 4 Dynamic loads The secondary structures and flexible elements e g solar panels antennas and propellant tanks must be designed to withstand the dynamic environment described in Chapter 3 and must take into account the safety factors defined in paragraph 4 3 2 Arianespace November 2005 4 5 Design And Verification Requirements Soyuz CSG User s Manual Issue Draft 4 2 5 Spacecraft RF emission To prevent the impact of spacecraft RF emission on the proper functioning of the LV electronic components and RF systems during ground operations and in flight the spacecraft should be designed to respect the LV susceptibility levels given in Figure 4 1 In particular the spacecraft must not overlap the frequency bands of the LV 2206 5 MHz 2227 MHz 2254 5 MH
136. ltage overshoot induced by his circuits both at circuits switching and in the case of circuit degradation To protect spacecraft equipment a safety plug with a shunt on S C side and a resistance of 2kQ 1 0 25 W on the L V side shall be installed in all cases 5 5 2 1 Separation monitoring The separation status indication is provided by dry loop straps integrated in each spacecraft LV connectors as follows e one dry loop strap per connector on satellite side dedicated for the separation monitoring by the upper stage telemetry system e dry loop straps on adapter side dedicated for the separation monitoring by Satellite if required The main electrical characteristics of these straps are strap closed R lt 1 Q strap open R 100 kQ 5 5 2 2 Dry loop command Optional TBD commands are available The main electrical characteristics are Loop closed R lt 1Q Loop open R 100 kQ Voltage lt 32 V Current lt 0 5 A During flight these commands are monitored by the Fregat telemetry system 5 5 2 3 Electrical command Optional TBD commands are available with the following main electrical characteristics Input voltage 28V 4V Input current 0 5 A Number 8 Impulse duration n x 32 0 15 ms with n 1 lt n lt 6 These commands are redundant and are monitored by the upper stage telemetry system Arianespace January 2006 5 15 Spacecraft interfaces Soyuz CSG User s Manual Is
137. n as necessary to fit with the Customer requirements Their respective compatibility with the spacecraft is managed through the Interface Control Document ICD Arianespace January 2006 5 1 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft 5 2 The reference axes All definition and requirements shall be expressed in the same reference axis system to facilitate the interface configuration control and verification Figure 5 1 shows the three stage vehicle and the Fregat upper stage coordinate system that are the reference axis system The clocking of the spacecraft with regard to the launch vehicle axes is defined in the Interface Control Document taking into account the spacecraft characteristics volume access needs RF links Block Note Arrows shows direction of positive vehicle roll Ziy Block NI 11144 I Ike YLy Block D Block G i l II fm Ceu s Launch Tower Umbilical mast Figure 5 1 Soyuz coordinate system 5 2 Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft 5 3 Encapsulated spacecraft interfaces 5 3 1 Payload usable volume definition The payload usable volume is the area under the fairing or the dual launch carrying structure available to the spacecraft mated on the adapter dispenser This volume constitutes the limits that the static dimensions of the spacecraft including manufacturing tolerance thermal pro
138. n complements the Ariane 5 and Vega offer in the medium weight payload class for low earth orbit and provides additional flexibility in delivery of satellite up to 3 t to GTO orbit The decision to operate Soyuz from the Guyana Space Centre CSG was taken by the European Space Agency May 27 2003 associated with a perspective of evolution of the European launcher sector for the 2010 timeframe These decisions covered the continuity of the Ariane 5 launch service the development and commercial availability of the Vega small launch vehicle from 2008 onwards and the Soyuz commercial operations from the Guiana Space Centre starting in 2008 The exclusive exploitation of this launch vehicle family was entrusted to Arianespace a unique launch services operator relying on the European and Russian space industry The Customer will appreciate the advantages and possibilities brought by the present synergy using a unique high quality rated launch site a common approach to the LV spacecraft suitability and launch preparation and the same quality standards for mission integration and management Arianespace January 2006 Soyuz CSG User s Manual Introduction Issue Draft 1 3 Arianespace launch services Arianespace offers to its customers reliable and proven launch services that include e Exclusive marketing sales and management of Ariane 5 Soyuz and Vega operations e Mission management and support that covers all aspects of lau
139. n integration and Issue Draft management 7 4 2 2 Preliminary Mission Analysis The purposes of the Preliminary Mission Analysis are as follows to describe the compliance between the LV and the Spacecraft to evaluate the environment seen by the Spacecraft to enable the Customer to verify the validity of Spacecraft dimensioning to review the Spacecraft test plan see chapter 4 to identify all open points in terms of mission definition that shall be closed during the Final Mission Analysis to identify any deviation from the User s Manual waivers The output of the Preliminary Mission Analysis will be used to define the adaptation of the mission flight and ground hardware or to adjust the Spacecraft design or test program as needed Based on the results of the RAMP the DCI will be updated reissued and signed by both parties as Issue 1 7 4 2 2 1 Preliminary Trajectory Performance and Injection Accuracy Analysis The preliminary trajectory performance and injection accuracy analysis comprises definition of the preliminary reference trajectory and verification of the short and long range safety aspects definition of flight sequences up to separation command and deorbitation of the upper stage if necessary definition of the orbital parameters at separation evaluation of nominal performance and the associated margins with regard to Spacecraft mass and propellant reserves and preliminary assessment of launch ma
140. n of the CSG safety Manager Responsable support for operations in the Responsible rules during campaign and des Moyens Charge Utile EPCU facilities Responsable countdown Sauvegarde Sol RSV Flight Safety Responsible Responsible for the Responsable applications of the CSG Sauvegarde Vol safety rules during flight ISLA Representative of the Safety ISCU Responsible for the Launch Area Safety Responsible on the launch Payload Safety monitoring of the payload Officer Ing nieur site Officer Ing nieur hazardous operations Sauvegarde Lancement Sauvegarde Charge Arianespace Utile 7 16 Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management Figure 7 3 Countdown organization PPF Payload Preparation Facilities Launch Site ISCU Launch ISLA team i RPS 1 l l l l I Automatic I sequence I a PR Lu On a p RE w t Ww m Operational intersite m ns _ intercom system Mission Control Centre DMS 1 lt lt eee z et r i s ww n g T ic l l l l l l M AE DTC TSSKB amp NPO L launcher authorities KBOM authority Weather forecast station d U in tm J D D E E eee SS E E NND un ee ee B Responsibles of CSG facilities and dawn range station network RSG RSV Arianespace January 2006 7 17 Soyuz CSG User
141. n of the flight program for the on board computer 7 4 2 3 2 Final Spacecraft Separation and Collision Avoidance Analysis The final Spacecraft separation and collision avoidance analysis updates and confirms the preliminary analysis for the latest configuration data and actual Spacecraft parameters e Last estimate of Spacecraft and LV properties e Last estimate of attitude and angular velocities at separation e Actual parameters of the separation device 7 4 2 3 3 Final dynamic coupled loads analysis The final CLA updates the preliminary analysis taking into account the latest model of the Spacecraft validated by tests It provides e For the most severe load cases the final estimate of the forces and accelerations at the interfaces between the adapter the final estimate of forces accelerations and deflections at selected Spacecraft nodes e he verification that the Spacecraft acceptance test plan and associated notching procedure comply with the final data 7 4 2 3 4 Final Electromagnetic Compatibility Analysis The final electromagnetic compatibility analysis updates the preliminary study taking into account the final launch configuration and final operational sequences of RF equipment with particular attention on electromagnetic compatibility between Spacecraft in the case of multiple launches Arianespace January 2006 7 9 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 4 2 3
142. nch activities and preparation from contract signature through launch e Systems engineering support and analysis e Procurement verification and delivery of the launch vehicle and all associated hardware and equipment including all adaptations required to meet customer requirements e Ground facilities and support GRS for customer activities at launch site e Combined operations at launch site including launch vehicle and Spacecraft integration and launch e Launcher telemetry and tracking ground station support and post launch activities e Assistance and logistics support which may include transportation and assistance with insurance customs and export licenses e Quality and safety assurance activities e Insurance and financing services on a case by case basis Arianespace provides the customer with a project oriented management system based on a single point of contact the Program Director for all launch service activities in order to simplify and streamline the process adequate configuration control for the interface documents and hardware transparence of the launch system to assess the mission progress and schedule control Arianespace January 2006 1 3 Introduction Soyuz CSG User s Manual Issue Draft 1 4 Soyuz launch vehicle family 1 4 1 History The Soyuz is the most recent of a long line of Soyuz family vehicles that taken together are acknowledged to be the most frequently roc
143. nd Vega and allow strictly limited access to the spacecraft The security management is also compliant with the US DOD requirements for the export of US manufactured satellites or parts and has been audited by American Authorities e g in frame of ITAR rules The security measures include e Restricted access to the CSG at the road entrance with each area guarded by the Security service e Escort for the satellite transportation to and within the CSG e Full control of the access to the satellite access to the facilities used for Spacecraft preparation is limited to authorized personnel only through a dedicated electronic card system the clean and control rooms are monitored 24 hours a day and 7 days a week by a CCTV system with recording capability Security procedures can be adapted to the specific missions according to the Customer s requirements Arianespace January 2006 6 27 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 4 3 Safety The CSG safety division is responsible for the application of the CSG Safety Rules during the campaign and especially for the equipment operator certification and permanent operation monitoring All CSG facilities are equipped with safety equipment and first aid kits Standard equipment for various operations like safety belts gloves shoes gas masks oxygen detection devices propellant leak detectors etc are provided by Arianespace On request from the Customer CSG
144. ne Khimki Russia Entire stage structure power thermal amp RF system NPTs AP Moscow Russia Control system OKB Orion Moscow Russia Batteries KB Khimash Moscow Russia Attitude Control thrusters KB Khimash Moscow Russia 5 92 engine KB OM Moscow Russia French Guiana France Launch pad and launch pad operations Figure 1 5 The Soyuz subcontractors 1 15 Soyuz CSG User s Manual Issue Draft ENVIRONMENTAL CONDITIONS Chapter 3 3 1 General During the preparation for launch at the CSG and then during the flight the spacecraft is exposed to a variety of mechanical thermal and electromagnetic environments This chapter provides a description of the environment that the spacecraft is intended to withstand All environmental data given in the following paragraphs should be considered as limit loads applying to the spacecraft The related probability of these figures not being exceeded is 99 Without special notice all environmental data are defined at the spacecraft base i e at the adapter spacecraft interface The following sections present the environment for the two configurations Soyuz 2 1a and Soyuz 2 1b It is further noted that the introduction of the RD 0124 engine on the Soyuz 2 1b configuration is not expected to measurably affect either the quasi static loads or the sine vibration levels since its thrust is identical to that of the RD 0110 engine and moreover a sequenc
145. ng the equipment to CSG with attention of ARIANESPACE the customer benefits from the adapted transit procedure fast customs clearance and does not have to pay a deposit in accordance with the terms agreed by the Customs authorities However if after a campaign part of the equipment remains in French Guiana it will be subject to payment of applicable local taxes Arianespace will support the Customer in obtaining customs clearances at all ports of entry and exit as required 6 28 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 4 5 3 Personnel Transportation Customers have access to the public rental companies located at Rochambeau airport or through the assistance of Arianespace s affiliated company Free Lance Arianespace provides the transportation from and to Rochambeau Airport and Kourou at arrival and departure as a part of the General Range Support 6 4 5 4 Medical Care The CSG is fully equipped to give first medical support on the spot with including first aide kits infirmary and ambulance More over the public hospital with very complete and up to date equipment are available in Kourou and Cayenne The Customer team shall take some medical precautions before the launch campaign the yellow fever vaccination is mandatory for any stay in French Guiana and anti malaria precautions are recommended for persons supposed to enter the forest areas along the rivers 6 4 5 5 VI P
146. nnected with the EPCU by road about 75 kilometers away Cayenne harbor is located in the south of the Cayenne peninsula in Degrad des Cannes The facilities handle large vessels with less than 6 meters draught The harbor facilities allow the container handling in Roll On Roll Off Ro Ro mode or in Load On Load Off Lo Lo mode A safe open storable area is available at D grad des Cannes The port is linked to Kourou by 85 km road The Pariacabo docking area is located on the Kourou river close to Kourou City This facility is dedicated to the transfer of the launcher stages and or satellites by Arianespace ships and is completely under CSG responsibility The area facilities allow the container handling in Roll On Roll Off Ro Ro mode The docking area is linked to EPCU by a 9 km road Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft 6 2 2 Payload preparation complex EPCU The Payload Preparation Complex EPCU is used for spacecraft autonomous launch preparation activities up to integration with the launch vehicle and including spacecraft fuelling The EPCU provides wide and redundant capability to conduct several Simultaneous spacecraft preparations thanks to the facility options The specific facility assignment is finalized usually one month before spacecraft arrival The Payload Preparation Complex consists of 4 major areas and each of them provides Similar capabiliti
147. nsive qualification program it is projected that the flight reliability of Soyuz with the new components of the launch vehicle such as the larger payload fairing third stage engines and control system will not be affected Arianespace January 2006 1 5 Introduction Soyuz CSG User s Manual Issue Draft 1 5 Launch system description Arianespace offers a complete launch system including the vehicle the launch facilities and the associated services 1 5 1 Launch vehicle general data The Soyuz LV consists primarily of the following components e A lower composite consisting of four liquid fueled boosters first stage a core second stage and a third stage e Arestartable Fregat upper stage e A payload fairing and interstage section and e A payload adapter dispenser with separation system s Depending on the mission requirements a variety of different adapters dispensers may be used The Soyuz configuration used at CSG and corresponded vehicle data is shown in Figure 1 1 and outlined in the Annex 5 1 6 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Spacecraft 7 _ Spacecraft Adapter Fregat Upper Stage Interstage 3 Stage _ 2 Core Stage __ 1 Stage Strap on f Boosters Liftoff mass 308 t Figure 1 1 LV property data Arianespace January 2006 Introduction PAYLOAD FAI RINGS Fairing ST S Diameter 4 110 m 3 715 m Length 11
148. nterface Actual levels will be the same or lower taking into account the attenuation effects due to the adapter dispenser configuration or due to worst case assumptions taken into account in the computation Actual spacecraft compatibility with these emissions will be assessed during the preliminary and final EMC analysis Arianespace January 2006 3 15 Environmental conditions Soyuz CSG User s Manual Issue Draft Table 3 7 LV RF system characteristics Frequency Power Antenna Equipment MHz Power W dBW Number SOYUZ 3 STAGES Uu L QD 4 E Uu C L H n L D 2 QD O D c TM System 2200 2290 Radar transponder 5400 5900 system Radar transponder 5690 system Satellite Navigation 1595 25 System SSN TC Neutralisation 440 460 Tl JJ m C Receivers Transmitters XX OK 2K gt K OK OK 2K gt K OK OK K 3 16 Satellite Navigation 1595 25 System SSN Tracking PPU 5754 9 0 3 Tracking RDM 2805 11 0 075 100 x Tracking PPU 3410 0 125 Telemetry TMC M4 2200 2290 Redundant channel with a 3 second transmission delay with the nominal one The TMC M4 system comprises one transmitter and three antennas e One antenna equipped with a reflector and located on the interstage section below the Fregat operates as long as the Fregat is not separated from the third stage and e Two antennas located on the top of the Fregat operate a
149. nterface A1 3 4 Mass properties The data required are for the spacecraft after separation If the adaptor is supplied by the Customer add also spacecraft in launch configuration with adapter and adapter alone just after separation A1 3 4 1 Range of major minor inertia axis ratio A1 3 4 2 Dynamic out of balance if applicable Indicate the maximum dynamic out of balance in degrees A1 3 4 3 Angular momentum of rotating components Arianespace January 2006 A1 5 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft A1 3 4 4 MBI Properties nen Mass S of s Coefficients of inertia Matrix i e s c ka coordinates kg m adapter g mm g XG YG ZG Lx Ivy Izz Ixy lyz Ix Tolerance Min Max Min Max Min Max Min Max Min Max Min Max Notes CoG coordinates are given in S C axes with their origin at the separation plane Inertia matrix is calculated in S C axes with origin of the axes at the Center of gravity and 1 g conditions The cross inertia terms must be intended as the opposite of the inertia products Ixy Pxy A1 6 Arianespace January 2006 Soyuz CSG Manual Issue Draft A1 3 5 Propellant pressurant characteristics Application to use Arianespace s launch vehicle Density team SP S Frank voue QT CE CS 0 o po fuiquidvoume O o o o o poo C SE LM LL d Center of gravity of propellant loaded tank Pendulum atta
150. ntre Issue Draft 6 4 CSG OPERATIONS POLICY 6 4 1 CSG planning constraints Normal working hours at the CSG are based on 2 Shifts of 8 hours per day between 6 00 am and 10 00 pm from Monday to Friday Work on Saturday can be arranged on a case by case basis with advance notice and is Subject to negotiations and agreement of CSG Authorities No activities should be scheduled on Sunday and public holiday In all cases access to the facility is possible 24 hours a day 7 days a week with the following restrictions mainly due to safety reasons e no hazardous operation or propellant in the vinicity e no facility configuration change e use of cranes and other handling equipment only by certified personnel e no requirement for range support After spacecraft processing and transfer to other facilities and with advance notice from Arianespace the PPF may be used by another spacecraft In this case the spacecraft equipment shall be evacuated from the PPF Clean room 24 hours after spacecraft departure The CSG is equipped with different storage facilities that can be used as for the temporary equipment storage during the campaign and optionally outside of the campaign 6 4 2 Security The French Government CSG Authorities and Arianespace maintain strict security measures that are compliant with the most rigorous international and national agreements and requirements and they are applicable to the three launch system Ariane Soyuz a
151. nual Design And Verification Requirements Issue Draft 4 3 3 4 Acoustic vibration tests Acoustic testing is accomplished in a reverberant chamber applying the flight limit spectrum provided in Chapter 3 and increased by the appropriate safety factors The volume of the chamber with respect to that of the spacecraft shall be sufficient so that the applied acoustic field is diffuse The test measurements shall be performed at a minimum distance of 1 m from spacecraft Table 4 5 Acoustic vibration test levels Flight Limit Level dB Octave Center reference Test Frequency 0 dB 2x 10 Pa tolerance Test duration No fill factor correction is applied Arianespace November 2005 4 11 Design And Verification Requirements Soyuz CSG User s Manual Issue Draft 4 3 3 5 Shock qualification The demonstration of the spacecraft s ability to withstand the separation shock generated by the LV shall be based on one of the two following methods Method Number One Qualification by release test and analytic demonstration e A clamp band release test is conducted with the tension of the belt set as close as possible to its maximum value during which interface levels and equipment base levels are measured This test can be performed on the STM on the PFM or on the first flight model provided that the spacecraft structure close to the interface as well as the equipment locations and associated supports are equivalent to those of the fl
152. o 0 x ou 50 Time s Figure 3 3 Typical pressure variation under the fairing Arianespace January 2006 3 7 Environmental conditions Soyuz CSG User s Manual Issue Draft Figure 3 4 Typical depressurization rate under fairing 3 8 Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft 3 3 Thermal environment 3 3 1 1 ntroduction The thermal environment provided during spacecraft preparation and launch has to be considered at following phases e Ground operations o The spacecraft preparation within the CSG facilities o The upper composite and launch vehicle operations with spacecraft encapsulated inside the fairing o Before fairing jettisoning o After fairing jettisoning 3 3 2 Ground operations The environment that the spacecraft experiences both during its preparation and once it is encapsulated under the fairing is controlled in terms of temperature relative humidity cleanliness and contamination 3 3 2 1 CSG Facility Environments The typical thermal environment within the most of air conditioned CSG facilities is kept around 23 C 2 C for temperature and 55 5 for relative humidity More detailed values for each specific hall and buildings are presented in the EPCU User s Manual and in Chapter 6 3 3 2 2 Thermal conditions under the fairing During the encapsulation
153. ocessed during post launch analysis a synthesis of the results is provided to the customer Should a Customer provides the adapter Arianespace will supply the Customer with transducers to be installed on the adapter close to the interface plane if needed 3 18 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft SPACECRAFT DESIGN AND VERI FI CATI ON REQUIREMENTS Chapter 4 4 1 Introduction The design and dimensioning data that shall be taken into account by any Customer intending to launch a spacecraft compatible with the Soyuz launch vehicle are detailed in this chapter Arianespace January 2006 4 1 Design And Verification Requirements Soyuz CSG User s Manual Issue Draft 4 2 Design requirements 4 2 1 Safety Requirements The User is required to design the spacecraft in conformity with the CSG Safety Regulations 4 2 2 Selection of spacecraft materials In case of a dual launch or of a launch with a co passenger the spacecraft materials must satisfy the following outgassing criteria e Total Mass Loss TML lt 1 9o e Collected Volatile Condensable Material CVCM x 0 1 measured in accordance with the procedure ECSS Q 70 024A 4 2 3 Spacecraft Properties 4 2 3 1 Payload mass and CoG limits Off the shelf adapters provide accommodation for a wide range of spacecraft masses and centre of gravity See annexes referring to adapters for detailed values For satellites with characteristi
154. of telephone and fax equipment for voice and data transmission through the CSG local phone network with PABX Commutation Unit Public external network The CSG Telephone System CTS is commutated with external public network of France Telecom including long distance paid ISDN calls opportunities and access The GSM system cellular phones are operational at CSG through public operator providing roaming with major international operator Direct or CSG PABX relayed external connection e Connection to Long Distance Leased lines LL The Customer could subscribe at external provider for the Long Distance Leased lines or satellite based communication lines These lines will be connected to the CSG PABX Commutation Unit or routed directly to the Customer equipment For the satellite based communication lines the antennas and decoder equipment will be supplied by Customer e PABX Relay lines connection LIA On Customer request the Long Distance Leased lines or satellite based communication lines could be relayed with other PABX communication network providing permanent and immediate exchange between two local communication systems e Connection to the point to point external data lines In addition to the Long Distance Phone Leased lines the Customer may extend the subscription for the lines adapted to the data transmission They could be connected to the CSG PABX through the specific terminal equipment or to the LAN CSG Point to Po
155. of the Soyuz vehicle to provide access to a full range of orbits The upper stage consists of six welded 1 8 mm thick spherical tanks made of aluminum alloy AMG 6 four for propellant two for avionics distributed in a circle with 8 trusses passing through the tanks providing structural support The propulsion system consists of a single chamber NTO UDMH engine capable of in plane translation and controlled by electrohydraulic actuators In addition to the main engine FREGAT uses twelve thrusters for three axis attitude control and for propellant settling before ignition of the main engine The thrusters are distributed in 4 clusters on the top of the spherical tanks Up to 85 kg of hydrazine is stored in two tanks dedicated to the ACS The three axis inertial measurement unit the onboard computer and the GPS GLONASS navigation system form the core of the FREGAT control system The control system is based on a triple redundant architecture Both three axis stabilized orientation and spin stabilized modes are provided Telemetry system provides transfer of health monitoring data from FREGAT to the ground either via a direct transmission mode or via a playback mode The S band transmitter enables communication with CSG ground stations The FREGAT power supply consists of two Lithium Chloride batteries One battery is dedicated to the control system only the other is dedicated to the remaining equipment The number of batteries can be
156. of the two fairing halves The final jettisoning is provided by lateral springs This separation system standard for Russian launch vehicles produces low shocks at separation and allows its functionality to be verified during launch vehicle acceptance tests The payload volume is shown in Figure 5 2 Carrying structure description A dual launch internal carrying structure has been studied in order to make the best use of the Soyuz performance in Low Earth orbits such as SSO The usable volume offered for the upper and lower passengers are defined in Figure 5 4 Any of the Soyuz adapters can be used in conjunction with this carrying structure to provide for separation Arianespace January 2006 Soyuz CSG User s Manual Spacecraft interfaces Issue Draft R543 1105 9508 5060 sero s CAT z TL 2200 Figure 5 3 ST fairing access door and RF transparent window areas 1 amp 5 Air conditioning system hatches 2 8 satellite access doors with a diameter 400 mm 3 4 Fregat access doors 4 Venting ports to ensure the correct venting of the upper composite o Arianespace January 2006 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft 722 l tower volume SI NN SK NS NN c uere 244 4049 b di ne Pee ThirdStage Figure 5 4 Soyuz internal dual launch carrying structure usable volumes Soyuz CSG User s Manual Spacec
157. on 1966 1976 Soyuz Voskhod upgrade for the launch of the Soyuz manned capsule no longer in production 1973 Soyuz U Unified LV for the replacement of Voskhod Soyuz 1982 1995 Soyuz U2 Soyuz U upgrade for use of the improved fuel Sintin in the second stage no longer in production 1999 Introduction of Ikar upper stage for commercial missions no longer in production 2000 Introduction of Fregat upper stage 2001 Introduction of upgraded first and second stage engines RD 107A and RD 108A 2004 6 Introduction of a digital control system the ST fairing and the upgraded third stage engine RD 0124 Note Molniya launch vehicle is still operational and will be progressively replaced by the Soyuz with the Fregat upper stage 1 4 Arianespace January 2006 Soyuz CSG User s Manual Introduction Issue Draft The Soyuz is launched from the Baikonur Cosmodrome in Kazakhstan from the Plesetsk Cosmodrome in the North of Russia and from the Guiana Space Centre in French Guiana to meet the needs of the commercial market and continuing to serve the needs of Russian government and other institutional and international programs Soyuz LVs continue to be mass produced in Samara Russia by the Samara Space Center whose facilities have been designed to accommodate the production of up to four LVs per month As a result of the continued demand from the Russian government International Space Station activity and commercial
158. on and data transmission safety support and logistics e The verification that the facility configuration is compliant with DCI requirements and finalization and approval of the POI and POC e The approval of the campaign organization particularly organizational charts the presentation of each function individuals involved and their presence on site and workday planning e The status of the safety submission and open points e The approval of the EPCU readiness certificate The facility configuration for combined operations could be discussed if required 7 5 4 5 Spacecraft consent to fuel meeting The objective of this meeting is to confirm the readiness of the hazardous facility and Spacecraft for fueling and of the L V to proceed with the subsequent operations Readiness statements are issued at the end of the meeting 7 18 Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 4 6 Combined operations readiness review BT POC Bilan Technique POC The objective of this review is to demonstrate the readiness of the Spacecraft the flight items and the CSG facilities to start the combined operations according to POC It addresses the following main points e POC presentation organization and responsibility for combined operations e he readiness of the Upper composite items adapter fairing upper stage preparation status non conformities and waivers overview
159. ons Arianespace January 2006 d ion an management integrat ission M Soyuz CSG User s Manual Issue Draft SSS E ARI ERU ERE LE PL T qns Aiday qns Z Ajdas jeu fans T Ajday 10d deu 90d aah Rete gt sod p 310d34 u une t jeul4 S3jnsaJ 159 AUG pend awaneduio C O ueld 3521 2pouu eut l pow 94d Jepoui 2Jd sisAjeue jeuld En RR 0 T 0 c enss T anss 0 anssI vna uv Hd e 2 5 1 uS p E ien ne 2 hood e e e imis Od AVY VOD Ene SIA 9S2 dv OX V d ubieduie Jii penu Oy j 1 Ee Ze Ted 1 1 ap s S 1 9 1 Z 1 8 6 30T TI 1ZT 5ET 1 bT 1ST 191 3ZT 381 6T 5 OC 1 TZ ZZ n EC 1p uoissiuqns Ajyajes u unej 9g ubieduie youney ue d uonejodo poeulrquio2 paAeo 193UT 20d ue d uonejedo peurquio5 SOd uejd uoneaado 3jeu o eds uonea4edoad ubieduie youne SISAJEUE u2unej JSod 22u2 3iJ JEN UeYIEW e21323 3 UOI282IU9A i igiyeduuo2 3jeu2o 2edsg sisAjeue Jeui9u Ay Iqiyeduuo2 44 8 DW3 sisAjeue peo pajdnoz SISAJBUB DDUBPIOAR UOISI OD 8 uoneiedas sisAjeue A10329 e4 SIS JGUP UOISSIN IDga Juauinsop o43uo2 a2ej19Ju uoddns Gurissuibus W JS S uonejdepe uawus1in201d 1oy2une SM9IA9M 9 Z S s Z cs bol EPL Ere Tez v Z Note and B the deliverables and tasks of the Customer Figure 7 1 Typical Mission Integration Schedule 7 3 Arianes
160. onsidered for trade off studies only For precise data please contact Arianespace 2 12 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft TO BE ISSUED LATER Figure 2 9 LV performance for circular orbits Orbit inclination 56 deg Arianespace January 2006 2 13 Performance and launch mission Soyuz CSG User s Manual Issue Draft 2 4 3 Elliptical orbit missions 2 14 The Fregat restartable capability offers a great flexibility to servicing a wide range of elliptical orbits A typical Soyuz mission includes the three stages sub orbital ascent and two or three Fregat burns as follows e A first burn to transfer to an initial parking orbit followed by a coast phase up to a point corresponding to the required argument of perigee of the targeted elliptical orbit in case of sub orbital mission e A second Fregat burn to transfer to an intermediate elliptical orbit with an altitude of apogee equal to the target value and e A third Fregat burn to raise the perigee to the required value In some cases when a lower altitude of perigee is required the mission will be reduced to two Fregat burns LV performance data for a 51 8 degree inclination and a perigee altitude of 200 km are presented in Figure 2 10 and Figure 2 11 Specific mission profiles for elliptical orbits can be analyzed on a mission peculiar basis Arianespace January 2006 Soyuz CSG User s Manual
161. onur SoyuzU Manned Soyuz TM 24 X 1599 775 August 29 1996 Plesetsk Molniya Unmanned Prognoz M2 X 1600 October 24 1996 Plesetsk Molniya Unmanned Molniya 3 X 1601 Mac Baikonur SoyuzU Unmanned Progress M 33 X 1602 116 le Plesetsk SoyuzU Unmanned Bion 11 X 1603 T7 February 10 1997 Baikonur SoyuzU Manned Soyuz TM 25 X 1604 778 April 6 1997 Baikonur SoyuzU Unmanned Progress M 34 X 1605 779 April 9 1997 Plesetsk Molniya Unmanned Kosmos 2340 X 1606 May 14 1997 Plesetsk Molniya Unmanned Kosmos 2342 X 1607 May 15 1997 Baikonur SoyuzU Unmanned Kosmos 2343 X 1608 780 July 5 1997 Baikonur SoyuzU Unmanned Progress M 35 X 1609 781 August 5 1997 Baikonur SoyuzU Manned Soyuz TM 26 X 1610 782 VEDI d Plesetsk Molniya Unmanned Moiniya 1T X 1611 if October 5 1997 Baikonur SoyuzU Unmanned Progress M 36 X 1612 783 October 9 1997 Plesetsk SoyuzU Unmanned Foton 11 X 1613 784 November Be Plesetsk SoyuzU Unmanned Resurs F1M X 1614 785 T cael a Plesetsk SoyuzU Unmanned Kosmos 2348 X 1615 786 T c Baikonur SoyuzU Unmanned Progress M 37 X 1616 787 January 29 1998 Baikonur SoyuzU Manned Soyuz TM 27 X 1617 788 February 17 1998 Baikonur SoyuzU Unmanned Kosmos 2349 X 1618 189 March 15 1998 Baikonur SoyuzU Unmanned Progress M 38 X 1619 790 May 7 1998 Plesetsk Molniya Unmanned Kosmos 2351 X 1620 May 15 1998 Baikonur SoyuzU Unmanned Progress M 39 X 1621 791 June 24 1998 Plesetsk SoyuzU Unmanned Kosmos 2358 X 1622 792 June 25 1998 Baikonur SoyuzU Unmanned Kosmos
162. oosters Soyuz first stage the central core second stage and the Soyuz third stage are assembled and integrated together in the LV Integration Building MIK of the Soyuz Launch Area Autonomous and combined tests are performed on the first second and third Soyuz stages Then the three stage launch vehicle is transported to the launch pad and erected in vertical position These activities are conducted in parallel with the Spacecraft activities in PPF HPF UCIF 75 5 3 2 Fregat Upper Stage Preparation The Fregat upper stage is installed on its test banch inside LV Integration Building MIK where the following operations are performed e Fregat autonomous verification Fit check of the adapter dispenser mechanical and electrical with the Fregat Then Fregat is transported to the S3B one of the UCIF clean halls for its fueling last verifications and integration with adapter and Spacecraft These activities are performed in parallel with Spacecraft preparation and may interact with Spacecraft fueling if the same room is used The campaign planning will properly arbitrate time sharing if needed Arianespace January 2006 7 23 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 5 4 Combined operations 7 5 5 4 1 Operations in the UCIF The Spacecraft integration with the adapter dispenser the Fregat upper stage and the fairing with its adaptation bay is carried out in the UCIF under Arianespac
163. or C DCI Review 7 Review of S C Operations Plan POS L 6 M O S K Preparation of Interleaved Ops Plan POI Security aspects DCI Review amp Final Mission Analysis kick off L 9 M E S C DCI Review Safety Submission Status 19 Final Mission Analysis Review RAMF L 2 5 M E E 10 Campaign Preparation Final Meeting L 3 M O S E 11 LV Flight Readiness Review RAV bez M E O S E 12 Satellite preshipment Review L 2 M E C or X 13 Range Configuration Review M O S K 14 Consent to S C filling meeting Before filling M O S K 15 POC Readiness Review e M O S K 16 Transfer Readiness Review Pre RAL L 5 days K 17 Launch Readiness Review RAL L 1 day M E O S K 18 Launch campaign wash up L 1 day M O K 19 Post Flight Debriefing CRAL 1 day after M E O K launch Meeting target dates are given taking into account the respective commitments of both parties for the delivery of the documentation as described in this Annex parts 2 amp 3 Dates are given in months relative to L where L is the first day of the latest agreed Launch period Slot or approved launch day as applicable A2 4 Arianespace January 2006 Soyuz CSG User s Manual Review and documentation Issue Draft checklist M Management E Engineering O Operations S Safety E Evry K Kourou C gt CUSTOMER HQ X Contractor Plant To be held at Spacecraft Team arrival in Kourou To be held the day before the agreed day for starting the POC Operations
164. orders the Soyuz LV is in uninterrupted production at an average rate of 10 to 15 LVs per year with a capability to rapidly scale up to accommodate users needs The Fregat upper stage production by NPO Lavochkine Moscow Russia is well suited with this production rate 1 4 2 Vehicle Reliability Table 1 2 shows the information on Soyuz reliability Reliability figures are presented individually for the lower three stages of the vehicle and for the Fregat upper stage This is primarily due to the large statistical database of flights with the lower three stages To provide most relevant data to future missions it was chosen to present reliability figures for the flights performed in the past 25 years The figures presented include the Soyuz and Molniya flights as these two configurations has a nearly identical lower three stages Furthermore since 1977 the Soyuz and Molniya configurations are the only vehicles of the Soyuz family to remain in production replacing all previous versions Table 1 2 Flight Success Ratio Component Vehicle Soyuz amp Molniya Fregat upper stage Time frame 1977 2005 2000 2005 Number of Flights 968 8 Number of Failures 19 0 Flight Success Rate 96 98 100 Note The flight success rate is the overall ratio of successful flights over flight attempts It takes into account all launch system failures regardless of corrections or modifications Taken into account the design objectives and exte
165. ore the Launch order 20s The new launch date can be rescheduled within 24 hours of the first launch attempt Note In the event of a launch abort after upper composite umbilical disconnection 2m35s reconnection will occur within 1 hour and 30 minutes TBC The last instant lines connecting Spacecraft and COTE remain active e Decision after Launch order 20s The launcher must be removed from the pad for refurbishment After the Spacecraft is set into a safe mode and brought back to the EPCU LV removal operations are executed in the reverse order of the scenario used for setup Arianespace January 2006 7 27 Soyuz CSG User s Manual Mission integration and Issue 7 6 Draft management Safety assurance 7 6 1 General The safety objectives are to protect the staff facility and environment during launch preparation launch and flight This is achieved through preventive and palliative actions e Short and long range flight safety analysis based on Spacecraft characteristics and on trajectory ground track e Safety analysis based on the Spacecraft safety submission e Training and prevention of accidents e Safety constraints during hazardous operations and their monitoring and coordination e Coordination of the first aide in case of accident CSG is responsible for the implementation of the Safety Regulations and for ensuring that these regulations are observed All launches from the CSG require approvals f
166. pace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 3 Launch vehicle procurement and adaptation 7 3 1 Procurement Adaptation process Arianespace ensures the procurement of LV hardware according to its industrial organization procedures The following flight items will be available for the Customer launch e One equipped launch vehicle and its propellants e Dedicated flight program s e One standard fairing with optional access doors and optional passive repeaters or radio transparent windows e One adapter or dispenser with its separation system s umbilical harnesses and instrumentation e Mission dedicated interface items connectors cables and others e Mission logo on the LV from Customer artwork supplied not later than 6 months before launch If any components of the LV need to be adapted due to specific mission requests to the output of mission analysis etc adaptation in terms of specification definition and justification will be implemented in accordance with standard quality rules The Customer will be involved in this process 7 3 2 LV Flight Readiness Review RAV Revue d Aptitude au Vol 7 4 The review verifies that the launch vehicle after acceptance tests at the manufacturer s facilities is technically capable to execute its mission During this review all changes non conformities and waivers encountered during production acceptance test
167. pace Center TsSKB Progress was created in 1996 by combining the TSSKB Central Samara Design Bureau and the Progress production plant pa The Samara Space Center is one of the world leaders in the design of launchers spacecraft and related systems Its history goes back to the CKB DPOrPECC start of the space program in 1959 when a branch of the Moscow OKB 1 UGKB NPOTPECC design bureau was established in the city of Kuibyshev now known as Samara The Center developed a family of launch vehicles derived from the OKB 1 s R 7 intercontinental ballistic missile Approximately 10 versions were developed including Sputnik which carried the first man made satellite into orbit Vostok used for the initial manned space flight Molniya and Soyuz In addition to years of experience building launch vehicles TSSKB Progress has also built numerous earth observation and scientific satellites 1 6 4 3 NPO Lavotchkine NPO Lavotchkine was founded in 1937 as an aircraft manufacturer and is one of the industry leaders in the development and implementation of interplanetary astrophysical and earth monitoring projects such as 4 National programs Luna Mars Venera Bankir International programs VEGA Phobos IRS 1 Granat Mars 96 Interbol Yip Klaster FF Advanced programs Spektr Phobos Grunt Solnyechniy Zond and others NPO Lavotchkine adapts produces and is the technical authority for the Fregat upper stage NPO Lavotc
168. per stage Ikar based on the Kometa satellite bus was added to the lower three stages of the Soyuz U This LV configuration allowed the Soyuz to reach circular orbits above 500 km and was used for six flights to deploy half 24 satellites of the Globalstar constellation In 2000 the Soyuz began flying the Fregat upper stage developed by NPO Lavochkin It has a larger propellant capacity then the Ikar stage and is also restartable In 2001 the 1 st and 2nd stage engine was upgraded This improvement primarily involved modifying the injector pattern for the engines to improve the propellant mixing and combustion hence raising the overall specific impulse of the engines by 5 s Since 2001 they used permanently including manned mission A5 13 A5 2 2 Launch Record 1957 2005 Vehicles based on the R 7 ICBM have been launched 1705 times through December 28 2005 A breakdown of these launch attempts by vehicle class is shown below 1957 6 2 6 2 1958 11 8 8 5 3 3 1959 20 4 15 3 5 1 1960 17 6 1 0 14 4 2 2 1961 16 2 14 2 2 0 1962 15 2 9 1 6 1 1963 19 3 13 2 4 1 2 0 1964 28 4 14 0 8 4 6 0 1965 37 3 13 1 12 2 12 0 1966 40 4 15 1 9 1 14 1 2 1 1967 40 3 9 0 T 0 20 3 4 0 1968 42 2 2 0 6 1 29 1 5 0 1969 44 1 3 1 4 0 32 0 5 0 1970 44 1 5 0 T 0 30 1 2 0 1971 44 4 5 0 3 0 31 4 9 0 1972 48 1 5 0 11 0 29 1 3 0 1973 54 1 3 0 10 0 32 1 9 0 1974 52 3 6 0 7 0 24 2 15 1 1975 59 1 6 0 12 0 28 0 13 1 1976 55 1 5 0 11 0 12 0 2 1 1977 56 2
169. phase and once mated on the launch vehicle the spacecraft is protected by an air conditioning system provided by the ventilation through the pneumatic umbilicals high flow rate H and through the launch vehicle for the last 45 minutes when the gantry has been rolled away low flow rate L See fig 3 5 Arianespace January 2006 3 9 Environmental conditions Soyuz CSG User s Manual Issue Draft Table 3 6 Air Conditioning under the Fairing Air conditioning Relative Flow Nm h Humidity system Operations UCIF air 23 1 C 50 5 ICE system 2 weeks max in UCIF conditioning if necessary system Transfer CARAVAN 16 C lt 60 1500 3 h from UCIF to Launch Pad Upper lt 27 C lt 60 No venting composite overpressure hoisting and mating on the LV Launch High Any value lt 20 lt 2000 preparation mode specified venting between 11 C and 25 C Accuracy 2 C Final Low mode Any value lt 20 lt TBD HO 2h00 min countdown venting specified up to lift off between 11 C and 2B59 C t Accuracy za 22 lt 20 lt TBD few minutes after abort up to High flow Aborted Low mode Any value launch venting specified between 11 C and 25 C Accuracy 2 C mode reconnection HO 4h00m Note The air temperature before lift off shall be agreed on a case by case basis in order to take into account the Fregat s constraints and the spacecr
170. pin rates are possible but shall be specifically analyzed Arianespace January 2006 2 19 Performance and launch mission Soyuz CSG User s Manual Issue Draft Although the spacecraft kinematic conditions just after separation are highly dependant on the actual spacecraft mass properties including uncertainties and the spin rate the following values are typical results The 3 o attitude accuracy for a 30 deg sec spin mode are e Spin rate accuracy lt 1 deg s e Transverse angular tip off rates lt 0 3 deg s e Depointing of kinetic momentum vector half angle x 1 deg e Nutation angle x 10 deg 1 Orientation of composite around Z axis 2 Orientation of composite around Y axis I 3 Spin up 4 4 Spacecraft separation 5 Spin down 6 Orientation for deorbitation 5 Figure 2 13 Typical separation sequence 2 9 2 3 Separation linear velocities and collision risk avoidance The payload adapter s separation systems are designed to deliver a minimum relative velocity between spacecraft and upper stage ranging from 0 3 m s to 1m s For each mission Arianespace will verify that the distances between orbiting bodies are adequate to avoid any risk of collision until the launcher final maneuver For this analysis the Customer has to provide Arianespace with its orbit and attitude maneuver flight plan otherwise the spacecraft is assumed to have a pure ballistic trajectory i e no s c maneuver occurs after separation After comp
171. ponses and decisions and tailor made solutions for start ups or established players With offices in the United States Japan Singapore and Europe and with program representatives elsewhere in the world Arianespace is committed to forging service package that meet our Customer s requirements as closely as possible An experienced and reliable company Arianespace established the most trusted commercial launch system satisfactorily managing more than 250 contracts the industry record Arianespace competitiveness is demonstrated by the market s largest order book that confirms the past and present confidence of Arianespace worldwide customers Arianespace has a unique processing and launch experience with all commercial satellite platforms as well as with very demanding scientific missions A dependable long term partner Backed by the combined recourses of its shareholders and the European and national Space Agencies Arianespace relies on the scientific and technical expertise of its European and other country s industrial partners European political support periodically confirmed and international cooperation agreements at state level Russia Ukraine brings non comparable advantages The reference system Any time any mass to any orbit 1 IV Arianespace Soyuz CSG User s Manual Issue Draft User s Manual Configuration Control Sheet Revision ire Note The present Manual is in close link with the U
172. portation between CSG facilities Arianespace January 2006 A3 3 Items and services for an Soyuz CSG User s Manual Arianespace launch Issue Draft A3 7 2 Payload preparation facilities allocation A3 4 The Payload Preparation Complex with its personnel for support and equipped as described in the EPCU User s Manual may be used simultaneously by several Customers Specific facilities are dedicated to the Customer on the following basis activities performed nominally within normal CSG working hours or subject to negociations and agreement of authorities as defined in chapter 6 4 CSG operations policy PPF and HPF areas e spacecraft preparation clean room 350 m e lab for check out stations LBC 110 m e offices and meeting rooms 250 m e filling hall dedicated Storage Any storage of equipment during the campaign Two additional months for propellant storage Schedule restrictions The launch campaign duration is limited to 30 calendar days from S C arrival in French Guiana to actual departure of the last spacecraft ground support equipment as described in chapter 6 Extension possible subject to negotiations Transfer of S C and its associated equipment to the HPF facilities not earlier than 21 working days TBC before Launch Spacecraft Ground Support Equipment must be ready to leave the range within 3 working days after the launch After S C transfer to HPF and upon request by Arianespace the
173. proven by means of adequate tests The verification logic with respect to the satellite development program approach is shown in Table 4 2 Table 4 2 Spacecraft verification logic S C development Model Static Sine Random Acoustic approach vibration vibration Shock test STM Qual Qual test Qual test Qual test characterization test and analysis With By Shock test Structural FM1 heritage Protoflight Protoflight Protoflight characterization Test Model from test test test and analysis or by STM STM heritage Acceptance Acceptance Subsequent heritage test test Acceptance By heritage optional optional test PFM FM1 Qual test Protoflight Protoflight Protofligt Shock test test test characterization and analysis or by heritage Subsequent Acceptance Acceptance Acceptance By heritage FM s heritage test m optional optional f qualification is claimed by heritage the representativeness of the structural test model STM with respect to the actual flight unit must be demonstrated Protoflight approach means qualification levels and acceptance duration sweep rate With ProtoFlight heritage Model The mechanical environmental test plan for spacecraft qualification and acceptance shall comply with the requirements presented hereafter and shall be reviewed by Arianespace prior to implementation of the first test Also it is suggested that Customers will implement tests to ve
174. r manned missions for very long but remained operational until 1991 From 1962 to 1969 this LV was used to launch the first generation of earth observation satellites From 1966 to 1983 it was used for meteorological and communications satellites From 1984 to 1991 the vehicle was used less frequently for the launching of remote sensing satellites to SSO including the Indian IRS 1A and 1B spacecraft A5 11 A5 12 ey X omm cma ionic RN Molniya 1960 Present The Molniya is a four stage LV that replaces the Block E third stage of Vostok with a significantly more powerful LOX kerosene Block third stage and adds a LOX Kerosene nonrestartable fourth stage This Block L fourth stage is adapted specifically for ignition in a vacuum having been used to launch Soviet interplanetary probes before a four stage version of the Proton LV was introduced in 1964 From 1960 to 1964 the Molniya LV launched the following interplanetary probes Luna 4 through 14 Mars 1 Venera 1 through 8 and Zond 1 through 3 Since 1964 the Molniya has been used to launch Molniya communication satellites Prognoz science satellites military satellites and Earth remote sensing satellites all on highly elliptical orbits The introduction in 2000 of the Fregat upper stage will lead to the phasing out of the Block L stage used with Molniya due in part to the advantages of the Fregat s restartable main engine Voskhod 1963 1976 The Voskhod L
175. r extensive reproduction paper provided A3 6 Arianespace January 2006 Soyuz CSG User s Manual Items and services for an Issue Draft Arianespace launch A3 8 Optional items and services The following Optional items and Services list is an abstract of the Tailored and optional services list available for the Customer and which is updated on a yearly basis A3 8 1 Launch vehicle hardware pyrotechnic command electrical command dry loop command spacecraft GN flushing RF transmission through the payload compartment either SRP or RF window access doors at authorized locations for access to the encapsulated spacecraft A3 8 2 Mission analysis Any additional Mission Analysis study or additional Flight Program requested or due to any change induced by the Customer A3 8 3 Interface tests Note any loan or purchase of equipment adaptor clampband bolts separation pyro set can be envisaged and is subject to previous test plan acceptance by Arianespace e fit check mechanical electrical with ground test hardware at Customer s premises e fit check mechanical electrical with flight hardware in Kourou e fit check mechanical electrical with ground test hardware and one shock test at Customer s premises A3 8 4 Range Operations e spacecraft and or GSE transport to Kourou the Customer may contact Arianespace to discuss the possibility to use an Arianespace ship to transport the spacecraft and or its associate
176. raft interfaces Issue Draft 5 4 Mechanical I nterface The Soyuz offers a range of standard off the shelf adapters and their associated equipment compatible with most of the spacecraft platforms These adapters belong to the family of the Ariane and Vega adapters providing the same interface definition on the spacecraft side Their only specificity is the accommodation to the Fregat upper stage standard interface plane with a diameter of 2000mm at the adapter bottom side The Customer will use full advantage of the off the shelf adapters Nevertheless dedicated adapter or dispenser especially in the case of dispensers can be designed to address specific Customer s needs and requirements All adapters are equipped with a payload separation system brackets for electrical connectors In some cases to reduce the production time or facilitate the switch between LV Ariane adapters can be used directly with the Soyuz LV For this case a dedicated structure will be used to adapt the lower interface to the Fregat mating interface The payload separation system is a clamp band system consisting of a clamp band set release mechanism and separation springs The electrical connectors are mated on two brackets installed on the adapter and Spacecraft side On the spacecraft side the umbilical connector s brackets must be stiff enough to prevent any deformation greater than 0 5 mm under the maximum force of the connector spring Standard So
177. rations involving the Spacecraft and or LV activities Arianespace January 2006 7 13 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 14 e Operational requirements and constraints imposed by each satellite and the launch vehicle e A reference for each operation to the relevant detailed procedure and associated responsibilities The POC is approved at the Combined Operations Readiness Reviews BT POC Bilan technique POC 7 5 2 1 5 Detailed procedures for combined operations Two types of combined operations are identified e Operations involving each Spacecraft or launch vehicle independently these procedures are specific for each Authority e Operations involving Spacecraft Launch Vehicle interaction managed by common procedures The common procedures are prepared by Arianespace and submitted to the Customer s approval Arianespace use computer aided activities management to ensure that the activities associated with on site processing operations are properly coordinated Typically the procedure includes the description of the activities to be performed the corresponding sequence the identification of the responsibilities the required support and the applicable constraints 7 5 2 1 6 Countdown Manual Based on the Satellite Operations Plan Arianespace establishes a countdown manual that gathers all information relevant to the countdown processing on launch day including e A de
178. rdous operations are performed in the HPF The facility and communication network setup are provided by Arianespace The pyrotechnic systems are prepared in S2 S4 area including X ray verification and final assembly by Spacecraft team with Arianespace technical support In case of liquid propulsion Arianespace brings the propellant from the storage area to the dedicated facilities of the HPF The Spacecraft team carries out the installation and validation of Spacecraft GSE such as pressurization and filling equipment and setup of propellant transfer tanks A dedicated meeting authorizes the beginning of filling hazardous operations The Customer fills and pressurizes the Spacecraft tanks to flight level Hazardous operations are monitored from a remote control room CSG Safety department ensures safety during all these procedures The integration of hazardous items category A pyrotechnic devices etc into Spacecraft are carried out in the same way Weighing devices are available for Customer in HPF On request S C weighing can be performed under the Customer s responsibility by Arianespace authority Spacecraft batteries may be charged in HPF if needed except during dynamic hazardous operations Fluids and propellant analyses are carried out by Arianespace on Customer s request as described in the DCI 7 5 5 3 Launch vehicle processing 7 5 5 3 1 Preparation of the Lower Three Stages of the Launch Vehicle The four strap on b
179. rganized to close all contractual items 7 20 Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 5 Summary of a typical launch campaign 7 5 5 1 Launch campaign time line and scenario The Spacecraft campaign duration from equipment arrival in French Guina until and including departure from Guiana shall not exceed 30 calendar days 27 days before launch and day of launch and three days after launch The Spacecraft shall be available for combined operations 8 working days TBC prior to the Launch at the latest as it will be agreed in the operational documentation A typical Spacecraft operational time schedule is shown in Figure 7 4 The Spacecraft check out equipment and specific COTE Check Out Terminal Equipment necessary to support the Spacecraft Launch Vehicle on pad operations shall be made available to ARIANESPACE and validated two days prior to operational use according to the approved operational documentation at the latest All Spacecraft mechanical amp electrical support equipment shall be removed from the various EPCU buildings amp Launch Pad packed and made ready for return shipment within three working days after the Launch Operalinns Days 34 33 32 31 30 29 28 27 28 25 24 23 22 21 20 19 18 17 16 15 144 13 12 11 10 9 B 7 B 5 d 3 2 Launch day Launch Vehicle Preparation LV 3 stages preparation transfer ee ns Fa
180. rify the susceptibility of the spacecraft to the thermal and electromagnetic environment and will tune by these way the corresponding spacecraft models used for the mission analysis Arianespace November 2005 4 7 Design And Verification Requirements Soyuz CSG User s Manual Issue Draft 4 3 2 Safety factors Spacecraft qualification and acceptance test levels are determined by increasing the design load factors the flight limit levels which are presented in Chapter 3 and Chapter 4 by the safety factors given in Table 4 3 The spacecraft must have positive margins of safety for yield and ultimate loads Table 4 3 Test Factors rate and duration SC tests Qualification Acceptance Factors Duration ul eee Static QSL 1 3 ultimate 1 3 ultimate 1 1 yield 1 1 yield Sine vibrations 1 3 0 5 oct min 1 0 oct min 1 0 oct min Random vibrations or 3 dB or 3 dB i a wide or 3 dB or 3 dB Note Factor by which to multiply the Power Spectral Density 4 8 Arianespace January 2006 Soyuz CSG User s Manual Design And Verification Requirements Issue Draft 4 3 3 Spacecraft compatibility tests 4 3 3 1 Static tests Static load tests in the case of an STM approach are performed by the customer to confirm the design integrity of the primary structural elements of the spacecraft platform Test loads are based on worst case conditions i e on events that induce the maximum me
181. rom Ground and Flight Safety Departments These approvals cover payload hazardous systems design all transportation and ground activities that involve Spacecraft and GSE hazardous systems and the flight plan These regulations are described in the document CSG Safety Regulation R glement de savegarde du CSG 7 6 2 Safety submission In order to obtain the safety approval a Customer has to demonstrate that his equipment and its utilization comply with the provisions of the Safety Regulations Safety demonstration is accomplished in several steps through the submission of documents defining and describing hazardous elements and their processing Submission documents are prepared by the Customer and are sent to Arianespace providing the adequate Support in the relation with CSG Authorities The time schedule for formal safety submissions shows the requested deadlines working backwards from launch date L is presented in Table 7 2 A safety checklist is given in the Annex 1 to help for the establishment of the submission documents 7 6 3 Safety training 7 28 The general safety training will be provided through video presentations and documents submitted to the Customer before or at the beginning of the launch campaign At the arrival of the launch team at CSG a specific training will be provided with on site visits and detailed practical presentations that will be followed by personal certification In addition specific safet
182. rt for countdown 4 Operations 4 1 Handling and transport requirements for spacecraft and ancillary equipment 4 2 Tasks for launch operations including description of required access after encapsulation 5 Equipment associated with the spacecraft 5 1 Brief description of equipment for launch operations 5 2 Description of hazardous equipment with diagrams 5 3 Description of special equipment PPF HPF Launch table 6 Installations 6 1 Surface areas 6 2 Environmental requirements 6 3 Communications 7 Logistics 7 1 Transport facilities 7 2 Packing list Arianespace January 2006 Soyuz CSG User s Manual Issue Draft ITEMS AND SERVICES FOR AN ARI ANESPACE LAUNCH Annex 3 Within the framework of the Launch Service Agreement Arianespace supplies standard items and conduct standard services In addition Arianespace proposes a tailored service the General Range Service GRS to suit the needs of satellite operations during the launch campaign at CSG Other items and services to cover specific Customer s requirements are additionally provided as options through the Launch Service Agreement or ordered separately A3 1 Mission management Arianespace will provide a dedicated mission organisation and resources to fulfill its contractual obligations in order to satisfy the Customer s requirements focusing on the success of the mission contract amendments payments planning configuration control documentation rev
183. ry 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 2 Spacecraft launch campaign preparation phase During the launch campaign preparation phase to ensure activity coordination and compatibility with CSG facility Arianespace issues the following operational documentation based on Application to Use Arianespace s Launch Vehicles and the Spacecraft Operations Plan POS Plan des Op rations Satellite e An Interleaved Operation Plan POI e A Combined Operations Plan POC e The set of detailed procedures for combined operations e A countdown manual For the Customer benefit Arianespace can organize a CSG visit for Satellite Operations Plan preparation It will comprise the visit of the CSG facilities review of a standard POC Master Schedule as well as a verification of ICD provisions and needs The operational documentation and related items are discussed at the dedicated technical meetings and status of the activity presented at mission analysis reviews and RAV 7 5 2 1 Operational documentation 7 5 2 1 1 Application to Use Arianespace s Launch Vehicles DUA Demande d utilisation Arianespace Besides interfaces details Spacecraft characteristics the DUA presents operational data and launch campaign requirement See annex 1 7 5 2 1 2 Spacecraft Operations Plan POS The Customer has to prepare a Spacecraft Operations Plan POS Plan d Op ration Satellite defining the operation
184. s 6 Third stage Fregat separation 528 s 7 Fregat burn for orbit insertion 50 DY 200 400 600 800 1000 1200 1400 1600 1800 Relative distance km Figure 2 1 Typical ascent profile Arianespace January 2006 2 3 Performance and launch mission Soyuz CSG User s Manual Issue Draft p a 64105148 202241 270 305 350 390 420445 465 495 5055 4 Figure 2 2 Typical ground path for the Soyuz three stages GTO mission 2E i 0 Me 530 NE s 2 4 Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 250000 200000 150000 Altitude m 100000 50000 eo 100 200 300 400 500 600 Time s 8000 7000 6000 5000 4000 Velocity m s 3000 2000 1000 eo 100 200 300 400 500 600 Time s Figure 2 3 Altitude and relative velocity during the ascent profile of the first three stages Arianespace January 2006 2 5 Performance and launch mission Soyuz CSG User s Manual Issue Draft 2 3 2 Fregat upper stage flight profile Following the third stage cut off the restartable Fregat upper stage delivers the payload or payloads to their final orbits A typical Fregat flight profile is shown in Figure 2 4 This profile consists of the following events Intermediate orbit ascent profile after third stage separation and Fregat injection in the parking orbit
185. s and storage will be presented and justified Moreover the L V S C interfaces will be examined with reference to the DCI as well as the status of the launch operational documentation and CSG facility readiness The review IS conducted by Arianespace and the Customer is invited to attend The review will conclude on the authorization to begin the launch campaign or on the reactivation of the L V preparation if that L V has already been transported at the CSG or has performed a first part of its integration Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 4 Systems engineering support The Arianespace s launch service includes the engineering tasks conducted to ensure system compatibility between the Spacecraft its mission and the launch system as well as the consistency of their respective interfaces The final target of this activity is to demonstrate the correct dimensioning of the Spacecraft the ability of the launch vehicle to perform the mission to perform the hardware and software customization for the launch and to confirm after the launch the predicted conditions In this regard the following activities are included e Interface management e Mission analysis e Spacecraft compatibility verification e Post launch analysis In some cases the engineering support can be provided before contract signature to help the Spacecraft platform design process or to veri
186. s a single or dual one with different customers For the preparation and execution of the Guiana operations the Arianespace launch team is managed by a specially assigned Mission Director who will work directly with the Customer s operational team Customers Authorities Ariane Authority Arianespace Launch Vehicle Manufacturing Spacecraft 1 Interface Manager Arianespace Arianespace Program Launch Director 1 Operations Program Director 2 C S G Spacecraft 2 Interface Manager Principle of Customers Arianespace relationship dual launch 1 10 Arianespace J anuary2006 Soyuz CSG User s Manual Introduction Issue Draft 1 6 Corporate organization 1 6 1 Arianespace Arianespace is a French joint stock company Societe Anonyme which was incorporated on March 26 1980 as the first commercial space transportation company In order to meet the market needs Arianespace has established a worldwide presence in Europe with headquarter located at Evry near Paris France in North America with Arianespace Inc its subsidiary in Washington D C and in the Pacific Region with its representative offices in Tokyo Japan and Singapore Arianespace is the international leader in commercial launch services and today holds an important part of the world market for satellites launched to the geostationary transfer orbit GTO From its creation in 1980 Arianespace has successfully performed over 160 launc
187. s against the levels indicated in the Interface Control Document All sensor outputs were processed by the Ikar telemetry System The Globalstar dispenser also held the electrical harness necessary for umbilical links as well as for separation orders and telemetry data transmission from and to the Ikar This harness was tailored to Globalstar s needs and included the transmission of spacecraft battery temperature and voltage up to separation The Globalstar dispenser mass was 391 kg A4 24 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters TO BE ISSUED LATER Figure A4 7 1 Typical dispenser General view Arianespace January 2006 A4 25 Soyuz CSG User s Manual Issue Draft LAUNCH VEHI CLE DESCRI PTI ON Annex 5 A5 1 Launch vehicle Description A5 1 1 General data The Soyuz LV consists of A lower composite consisting of four liquid fueled boosters first stage a core second stage and a third stage A restartable Fregat upper stage A payload fairing and interstage section and A payload adapter dispenser with separation system s The Fregat adapter and spacecraft are all contained within the fairing representing the Upper Composite of the launch vehicle Depending on mission requirements a variety of different adapters dispensers may be used The Soyuz launch vehicle in the present configuration is in operation since 1966 except for the Fregat upper stage
188. s established between the Program Director and the Mission Director Besides the meetings and reviews described hereafter Arianespace will meet the Customer when required to discuss technical contractual or management items The following main principles will be applied for these meetings e The dates location and agenda will be defined in advance by the respective Program Directors and by mutual agreement e The host will be responsible for the meeting organization and access clearance e The participation will be open for both side subcontractors and third companies by mutual preliminary agreement 7 2 2 Mission integration schedule 7 2 The Mission Integration Schedule will be established in compliance with the milestones and launch date specified in the Statement of Work of the Launch Service Agreement The Mission Schedule reflects the time line of the main tasks described in detail in the following paragraphs A typical schedule for non recurring missions is based on a 24 months timeline as shown in Figure 7 1 This planning can be reduced for recurrent Spacecraft taken into account the heritage of previous similar flights or in case of the existence of compatibility agreement between the Spacecraft platform and the launch system For a Spacecraft compatible of more than one launch system the time when the launch vehicle type and configuration will be assigned to the Spacecraft will be established according to the LSA provisi
189. s to be executed on the Spacecraft from arrival in French Guiana including transport integration checkout and fueling before assembly on the L V and operations on the Launch Pad The POS defines the scenario for these operations and specifies the corresponding requirements for their execution A typical format for this document is shown in Annex 1 7 5 2 1 3 Interleaved Operation Plan POI Based on the Spacecraft Operations Plan and on the interface definition presented in the DCI Arianespace will issue an Interleaved Operation Plan POI plan d Op rations Imbriqu es that will outline the range support for all Spacecraft preparations from the time of arrival of Spacecraft and associated GSE equipment in French Guiana until the combined operations To facilitate the coordination one POI is issued per launch campaign applicable to all passengers of a launch vehicle and approved by each of them 7 5 2 1 4 Combined Operation Plan POC Based on the Spacecraft Operations Plan and on the interface definition presented in the DCI Arianespace will issue a Combined Operation Plan POC Plan d Op rations Combin es that will outline all activities involving a Spacecraft and the launch vehicle simultaneously in particular e Combined operations scenario and LV activities interfacing with the Spacecraft e Identification of all non reversible and non interruptible Spacecraft and LV activities e Identification of all hazardous ope
190. s to the mission A Spacecraft thermal model provided by the Customer in accordance with Arianespace specifications TBD is used as input for this analysis Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 4 2 3 Final Mission Analysis FMA The Final Mission Analysis focuses on the actual flight plan and the final flight prediction The Final mission demonstrates the mission compliance with all Spacecraft requirement and reviews the Spacecraft test results see chapter 4 and states on its qualification Once the final results have been accepted by the Customer the mission is considered frozen The DCI will be updated and reissued as Issue 2 7 4 2 3 1 Final trajectory performance and injection accuracy analysis The final trajectory analysis defines e The LV performance taken into account actual LV mass breakdown margins with respect to propellant reserves propulsion parameters adjustments etc and Spacecraft properties e The nominal trajectory or set of trajectories position velocity and attitude for confirmed launch dates and flight sequence and the relevant safety aspects short and long range e Injection orbit accuracy prediction e Specific attitude sequence during flight if any and Spacecraft attitude and associated accuracy at Spacecraft separation e The tracking and ground station visibility plan The final analysis data allows the generatio
191. ser s Manual of Soyuz launched from Baikonur ST GTD SUM 01 Issue 3 Revision O April 2001 In case of conflict between the two documents the present Manual takes precedence for launches from the Guiana Space Center CSG Arianespace V Soyuz CSG User s Manual Issue Draft Table of contents FOREWORD USER S MANUAL CONFIGURATION CONTROL SHEET TABLE OF ONTENTS ACRONYMS ABBREVIATIONS AND DEFINITIONS CHAPTER 1 INTRODUCTION 1 1 PURPOSE OF THE USER S MANUAL 1 2 EUROPEAN SPACE TRANSPORTATION SYSTEM 1 3 ARIANESPACE LAUNCH SERVICES 1 4 SOYUZ LAUNCH VEHICLE FAMILY HISTORY 1 4 1 History 1 4 2 Vehicle reliability 1 5 LAUNCH SYSTEM DESCRIPTION 1 6 1 5 1 Launch vehicle general data 1 5 2 European spaceport and CSG facilities 1 5 3 Launch service organization CORPORATE ORGANIZATION 1 6 1 Arianespace 1 6 2 Partners 1 6 3 European space transportation system organization 1 6 4 Main suppliers CHAPTER 2 PERFORMANCE AND LAUNCH MISSION Zel 22 2 3 2 4 20 2 6 2 7 2 8 INTRODUCTION PERFORMANCE DEFINITION TYPICAL MISSION PROFILES 2 8 1 Phase Ascent of the first three stages 2 3 2 Phase ll Fregat upper stage flight profile 2 3 3 Phase lll Fregat deorbitation or orbit disposal maneuver GENERAL PERFORMANCE DATA 2 4 1 Geosynchronous transfer orbit missions 2 4 2 Circular orbits 2 4 3 Elliptical orbit missions 2 4 4 Earth escape missions INJECTION ACCURACY MIS
192. shielded pairs with a cross section of power and 2 5 mm wired in parallel thus minimizing voltage remote control losses in the ground harnesses KTO12 Spacecraft 14 TBC twisted shielded pairs with across section of power and 2 5 mm wired in parallel thus minimizing voltage remote control losses in the ground harnesses KTO13 Spacecraft 10 TBC twisted shielded pairs with a cross section of check and 1 0 mm THonitoriHg 4 TBC twisted shielded pairs with a cross section of 0 20 mm and with low capacitance lt 12 nF for 100 m KTO14 Spacecraft 16 TBC twisted shielded pairs with a cross section of check and 0 20 mm and with a specific impedance 75 5 Q monitoring Last instant Last instant umbilical lines lines KRO11 14 PRECII eee 4 TBC twisted shielded pairs with a specific last instant impedance 75 5 Q Gauge 24 for the LV adaptor remote control portion up to the Fregat connection and with a cross and check section of 0 20 mm from the LV adapter Fregat interface to the EGSE 6 TBC single shielded wires with a cross section of 0 35 mm from the SC to the connector R15 and a cross section 3 mm from the connector R15 to the EGSE In case of dual launch these lines are to be shared by both passengers Arianespace January 2006 5 13 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft 5 5 1 3 Electrical Characteristics of the lines The ground lines are configured to support a permanent
193. sibility 5 3 3 Special on fairing insignia 5 3 4 Payload compartment description 5 4 MECHANICAL INTERFACE 5 5 ELECTRICAL AND RADIO ELECTRICAL INTERFACES 5 5 1 Spacecraft to EGSE umbilical lines 5 5 2 L V to spacecraft electrical functions 5 5 3 Electrical continuity interface 5 5 4 RF communication link between spacecraft and EGSE 5 6 INTERFACES VERIFICATIONS 5 6 1 Prior to the launch campaign 5 6 2 Pre launch validation of the electrical I F CHAPTER 6 GUIANA SPACE CENTRE 6 1 INTRODUCTION 6 1 1 French Guiana 6 1 2 The Europe s spaceport 6 2 CSG GENERAL PRESENTATION 6 2 1 Arrival areas 6 2 2 Payload preparation complex EPCU 6 2 3 Facilities for combined and launch operations 6 3 CSG GENERAL CHARACTERISTICS 6 3 1 Environmental conditions 6 3 2 Power supply 6 3 3 Communications network 6 3 4 Transportation and handling 6 3 5 Fluids and gases 6 4 CSG OPERATIONS POLICY 6 4 1 CSG Planning constraints 6 4 2 Security 6 4 3 Safety 6 4 4 Training course 6 4 7 Customer assistance Arianespace IX Soyuz CSG User s Manual Issue Draft CHAPTER 7 MISSION INTEGRATION AND MANAGEMENT 7 1 INTRODUCTION 7 2 MISSION MANAGEMENT 7 2 1 Contract organization 7 2 2 Mission integration schedule 7 3 LAUNCH VEHICLE PROCUREMENT AND HARDWARE SOFTWARE DEVELOPMENT ADAPTATION 7 3 1 Procurement Adaptation process 7 3 2 LV Flight Readiness Review RAV Revue d Aptitude au Vol 7 4 SYSTEMS
194. spacecraft preparation clean room may be used by another spacecraft Arianespace January 2006 Soyuz CSG User s Manual Issue Draft A3 7 3 Communication Links Items and services for an Arianespace launch The following communication services between the different spacecraft preparation facilities will be provided for the duration of a standard campaign including technical assistance for connection validation and permanent monitoring Service Type Remarks RF Link S C Ku band 1 TM 1 TC through optical fiber Baseband Link S C Ku band 2 TM 2 TC through optical fiber Data Link V11 and V24 network For COTE monitoring amp remote control Ethernet Planet network 10 Mbits sec 3 VLAN available per project Umbilical Link Copper lines 2x37 pins for S C umbilical amp 2x37 pins for auxiliary equipment Internet Connection to local provider Closed Circuit TV As necessary Intercom System As necessary Paging System 5 beepers per Project CSG Telephone As necessary Cellular phone GSM Rental by Customer International Telephone Links 9 With Access Code lt 10 ISDN RNIS links Subscribed by Customer Routed to dedicated Customer s working zone Facsimile in offices O9 l Video Conference O9 Equipment shared with other Customers AS necessary Note traffic to be paid at cost on CSG invoice after the campai
195. ss budget evaluation of orbit accuracy verification of compliance with attitude requirements during flight if any and evaluation of attitude accuracy at separation the tracking and ground station visibility plan 7 4 2 2 2 Preliminary Spacecraft separation and collision avoidance analysis The preliminary Spacecraft separation and collision avoidance analysis comprises Arianespace definition of the sequence of events evaluation of the relative velocity between the Spacecraft and the LV and their respective attitude verification of the feasibility of the required orientation verification of the post separation kinematic conditions requirements taking into account sloshing effect definition of the necessary separation energy clearance evaluation during Spacecraft separation Short and long term non collision prospects after Spacecraft separation January 2006 1 7 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 8 7 4 2 2 3 Preliminary dynamic coupled loads analysis CLA The preliminary CLA uses a preliminary Spacecraft dynamic model provided by the Customer according to the Arianespace specification TBD The preliminary dynamic coupled load analysis CLA e performs the modal analysis of the LV and the Spacecraft e provides the dynamic responses of the Spacecraft for the most severe load cases induced by the LV e gives at nodes selected by the relative Customer the m
196. sue Draft 5 5 2 4 Spacecraft telemetry retransmission Optional The spacecraft telemetry data can be interleaved with the launch vehicle TM data and retransmitted to the LV ground station by the upper stage telemetry system during the flight The data signal characteristics are Analog low frequency signals 0 6 V Discrete signals with output resistance 1 kQ in the closed state gt 100 kQ in the open state 5 5 2 5 Power supply to spacecraft Optional Independent from LV on board systems an additional power without regulation can be Supplied to the spacecraft through specific lines The main characteristics are Input voltage 28V 2V Nominal current 1 5 A Capacity 120 Ah non standard voltage can be made available also The Customer should contact Arianespace for this option 5 5 2 6 Pyrotechnic command Optional The Fregat has the capability to issue all needed and redundant orders to initiate adapter or dispenser separation systems In addition to LV orders for spacecraft separation other pyrotechnic commands can be generated by the Fregat power system to be used for spacecraft internal pyrotechnic system or in case where adapter with separation system is supplied by the Customer The electrical diagram is presented in Figure 5 The main electrical characteristics are Minimal current 4 1A Nominal current 5A Impulse duration 32 msec 0 15 msec Nominal battery voltage 27 V The redundant ord
197. t R RAAN RAL RAMF RAMP RAV RF RMS rpm RPS RS RSG RSV RTW S C SCA SCOE SIW SONO SOW SPM SRS SSO STFO STM SYLDSO UC UCIF UDMH UT Arianespace Right Ascension of the Ascending Node Launch readiness review Final mission analysis review Preliminary mission analysis review Launch vehicle flight readiness review Radio Frequency Root Mean Square Revolutions per minute Spacecraft preparation manager Safety manager Ground safety officer Flight safety officer Radio Transparent Window Spacecraft Attitude control system Special Check Out Equipment Satellite Injection Window Public One Way Announcement System Statement Of Work Solid Propellant Motor Shock Response Spectrum Sun Synchronous Orbit Optical Fiber Data Transmission System Structural Test Model Payload internal carrying structure To Be Defined Telecommand Countdown Time Telemetry Total Mass Loss Transfer Readiness Review Point To Point Telephone Network Upper Composite Upper Composite I ntegration Facility Unsymmetrical Dimethyl Hydrazine Universal Time Revue d Aptitude au Lancement Revue d Analyse de Mission Finale Revue d Analyse de Mission Pr liminaire Revue d Aptitude au Vol du lanceur Responsable Pr paration Satellite Responsable Sauvegarde Responsable Sauvegarde Sol Responsable Sauvegarde Vol Systeme de Contr le d Attitude Systeme de Transmission par
198. t MAIN LBC 3A AIRLOCK CLEAM S1A HALL pe E 4 A T g je i 1 7 SOUTH HANGAR CSG dedicated technical room a Figure 6 6 S1 layout Arianespace January 2006 6 7 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 2 2 2 53 Hazardous amp UC Integration Facility The S3 Hazardous amp Upper Composite Integration Facilities consists of buildings used for different hazardous operations basically fuelling of mono and or bipropellant and integration of solid propellant apogee kick off motors For Soyuz LV these facilities will be used also for the final spacecraft encapsulation under the fairing see paragraph 6 2 3 1 The area is located on the south west of the Ariane 5 launch pad ZL3 fifteen kilometers from the CSG Technical Centre CT The area close location to the Ariane and Vega launch pads imposes precise planning of the activity conducted in the area m mm ER nn A M S M AS RM Rm m Card ERO Figure 6 8 S3 area overview 6 8 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft The Customer s facility includes three separated building S3A S3C S3E The S3A building is dedicated to the middle class spacecraft main tanks and attitude control system fuelling integration with solid motors weighing pressurization and leakage tests as well as final spacecraft preparation and integration with adapter The building is ma
199. t of the separation attitude with regard to the actual launch time relative to the sun position or other should be indicated A1 2 3 4 Sequence of events after S C separation Describe main maneuvers from separation until final orbit including apogee firing schedule Arianespace January 2006 Soyuz CSG Manual Application to use Issue Draft Arianespace s launch vehicle A1 3 Spacecraft description A1 3 1 Spacecraft Systems of Axes The S C properties should be given in spacecraft axes with the origin of the axes at the separation plane Include a sketch showing the spacecraft system of axes the axes are noted Xs Ys Zs and form a right handed set s for spacecraft A1 3 2 Spacecraft geometry in the flight configuration A drawing and a reproducible copy of the overall spacecraft geometry in flight configuration is required It should indicate the exact locations of any equipment requiring access through shroud lifting points locations and define the lifting device Detailed dimensional data will be provided for the parts of the S C closest to the static envelope under shroud antenna reflectors deployment mechanisms solar array panels thermal protections Include the static envelop drawing and adapter interface drawing Preferably a 3D CAD model limited to 30Mo IGES or STEP extension shall be supplied A1 3 3 Fundamental modes Indicate fundamental modes lateral longitudinal of spacecraft hardmounted at i
200. tailed countdown sequence flow including all communication exchanges instruction readiness status progress status parameters etc performed on launch day e Go No Go criteria e The communications network configuration e A list of all authorities who will interface with the customer including launch team members names and functions and e Launch abort sequence Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 3 Launch campaign organization 7 5 3 1 Satellite launch campaign management During the operations at CSG the Customer interfaces with the Mission Director CM Chef de Mission The Program Director the Customer s contact in the previous phases maintains his responsibility for all the non operational activities The range operations manager DDO interfaces with the Mission Director He is in charge of the coordination of all the range activities dedicated to Customer s support support in the payload preparation complex transport telecommunications weather forecast for hazardous operations ground safety of operations and assets security and protection on the range Launcher down range stations set up for flight The launch campaign organization is presented in Figure 7 2 Positions and responsibilities are briefly described in Table 7 1 S C Team 1 S C Team 2 T DMS 1 DMS 2 S C Mission C Mission Director Director T Li
201. tection installation appendices may not exceed It has been established having regard to the potential displacement of the spacecraft complying with frequency requirements described in the Chapter 4 Allowance has been made for manufacturing and assembly tolerances of the upper part fairing intermediate bay upper stage and adapter for all displacements of these structures under ground and flight loads and for necessary clearance margin during carrying structure separation In the event of local protrusions located slightly outside the above mentioned envelope Arianespace and the Customer can conduct a joint investigation in order to find the most suitable layout The payload usable volume is shown in Figure 5 2 The allocated volume envelope in the vicinity of the adapter dispensed is described in the annexes dedicated to the each of the off the shelf adapters Accessibility to the mating interface separation system functional requirements and non collision during separation are also considered for its definition 5 3 2 Spacecraft accessibility The encapsulated spacecraft can be accessible for direct operations up to 4 hour 30 minutes TBC before lift off through the access doors of the fairing structure If access to specific areas of spacecraft is required additional doors can be provided on a mission specific basis Doors shall be installed in the authorized areas The payload platform of the gantry is not air condition
202. that was introduced in 2000 Since 1966 a few improvements were introduced to the Soyuz Launch vehicle to increase the safety and reliability of the vehicle and at the same time increase the performance of the launcher The latest improvements that were introduced to the Soyuz Launch System from 2000 to 2005 include Amelioration of the propellant burning in the chambers of the 1st and 2nd stage engines Soyuz FG current configuration for the manned flights Replacement of the analogic control and telemetry systems by the digital ones flown in 2004 Soyuz 2 13 Introduction of a larger fairing 4 110 m in diameter and 11 433 m in length Non critical ameliorations of the Fregat dry mass propulsion management and electrical components Amelioration of the 3rd stage layout adapted to the implementation of two different types of engine RD 0110 current version and RD 0124 more powerful version The launch conditions at GSC impose a few minor adaptation of the Launch Vehicle system to cope with the specific French Guiana environment and safety regulations in particularly Adaptation of the Soyuz and Fregat telemetry systems to cope with the S band and IRIG specification of the CSG ground stations Adaptation to the French Guiana climatic conditions in particular tuning the launcher air conditioning system to the Guiana temperature and humidity Adaptation to comply with the CSG safety regulations to be able to send from
203. the orbit characteristics and attitude of the Spacecraft just before its separation For additional verification of LV performance Arianespace requires the Customer to provide satellite orbital tracking data on the initial Spacecraft orbit including attitude just after separation if available The first flight results based on real time flight assessment will be presented during Post Flight Debriefing next to launch day 7 4 4 2 Flight Synthesis Report DEL Document d Evaluation du Lancement Arianespace provides the Customer with a Flight Synthesis Report within 45 days after launch This report covers all launch vehicle payload interface aspects flight event sequences LV performance injection orbit and accuracy separation attitude and rates records for ground and flight environment and on board system status during flight Arianespace January 2006 7 11 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 5 Launch campaign 7 5 1 I ntroduction The Spacecraft launch campaign formally begins with the delivery in CSG of the S pacecraft and its associated GSE and concludes with GSE shipment after launch 7 12 Prior to the launch campaign the preparation phase takes place when all operational documentation is issued and the facilities compliance with Customer needs is verified The launch campaign divided in three major parts differing by operation responsibilities and facility configura
204. the worldwide best known names in the space industry e The European Aeronautic Defense and Space Company EADS STARSEM e Arianespace gt FE Jc osa e The Russian Federal Space Agency e The Samara Space Center TSSKB Progress Starsem board consisting of representative of the three leading companies and space agency still covers the strategic decisions and common policy with regard to the commercial operation of Soyuz providing production and institutional support Arianespace J anuary2006 Soyuz CSG User s Manual Introduction Issue Draft 1 6 3 European Space transportation system organization Arianespace benefits from a simplified procurement organization that relies on a prime supplier for each launch vehicle The prime supplier backed by his industrial organization is in charge of production integration and launch preparation of the launch vehicle The prime suppliers for Ariane and Vega launch vehicle are respectively EADS LV and European Launch Vehicle ELV The prime supplier for the Soyuz launch vehicle is the Russian Federal Space Agency with SSC TsSKB Progress as the Soyuz LV Authority and NPO Lavotchkine as the provider of the Fregat upper stage Ariane Soyuz and Vega launch operations are managed by Arianespace with the participation of the prime suppliers and range support from CNES CSG The Soyuz operational team is based on SSC TsSKB Progress NPO L and KB OM representatives who are responsible for Soyuz
205. tion To design the LV mission and to ensure that the mission objectives can be achieved and that the Spacecraft and the launch vehicle are mutually compatible Arianespace conducts the mission analysis Mission analysis is generally organized into two phases each linked to Spacecraft development milestones and to the availability of Spacecraft input data These phases are e the Preliminary Mission Analysis PMA and e the Final Mission Analysis FMA Depending on Spacecraft and mission requirements and constraints the Statement of Work fixes the list of provided analysis Typically the following decomposition is used Analysis Preliminary run Final run Trajectory performance and injection accuracy L L analysis Spacecraft separation and collision avoidance J analysis Dynamic Coupled Loads Analysis CLA Electromagnetic and RF compatibility analysis Thermal analysis Note The Customer can require additional analysis as optional services Some of the analysis can be reduced or canceled in case of a recurrent mission Mission analysis begins with a kick off meeting At the completion of each phase a Preliminary Mission Analysis Review RAMP Revue d Analyse de Mission Pr liminaire and RAMF Revue d Analyse de Mission Finale are held under the joint responsibility of Arianespace and the Customer with support of the appropriate document package 7 6 Arianespace January 2006 Soyuz CSG User s Manual Missio
206. tion as following Spacecraft autonomous preparation It is includes the operations from the Spacecraft arrival to the CSG and up to the readiness for integration with LV and is performed in two steps Phase 1 Spacecraft preparation and checkout Phase 2 Spacecraft hazardous operations The operations are managed by the Customer with the support and coordination of Arianespace for what concerned the facilities supplying items and services The operations are carried out mainly in the PPF and the HPF of the CSG The major operational document used is an Interleaved Operation Plan POI Plan d Op rations Imbriqu es Combined operations It includes the Spacecraft mating on the launch vehicle adapter the transfer to the launch pad the integration on the launch vehicle and the verification procedures The operations are managed by Arianespace with direct Customer s support The operations are carried out mainly in the UCIF of the CSG The major operational document used is the Combined Operation Plan POC Plan d Op rations Combin es Launch countdown It covers the last launch preparation sequences up to the launch The operations are carried out at the launch pad using dedicated Arianespace Customer organization The following paragraphs provide the description of the preparation phase launch campaign organization and associated reviews and meetings as well as typical launch campaign flow chart Arianespace Janua
207. tion to the launch The last failure occurred on June 21 2005 with a Molnya launch vehicle The block A on Molnya operates close to the maximim flow rate acceptable by the RD 0108 which is not the case of Soyuz specific engine and flow control block characteristics on that flight led to engine operating range to be exceeded These deviated conditions provoked kerozene leak and therefore oxygen flow increase The block engine was ighited at a time when block A propellant were depleted leading to turbopump explosion and then to vehicle loss of control These anomaly is inherently linked to the Molnya launch vehicle characteristics and in no way affects Soyuz launches A5 18 Arianespace January 2006
208. titude of the launch vehicle its orientation the position of the sun with respect to the launch vehicle and the orientation of the considered spacecraft surfaces During daylight with long ballistic and or coast phases the sun radiation has to be taken into account In order to reduce the heat flux the launcher can be spun up to TBD 9 s A specific attitude with respect to the sun may also be used to reduce the heating during boosted TBC and or coast phases This will be studied on a case by case basis Wim Emm 1200 800 Stream density 400 Tk 5 10 15 20 Time sec Figure 3 6 Aerothermal Flux Decay after fairing jettisoning Arianespace January 2006 Soyuz CSG User s Manual Environmental conditions Issue Draft 3 3 3 3 Other thermal fluxes 3 3 3 3 1 Thermal Flux Reflected from Separated Stages No thermal flux coming from separated stages need be considered 3 3 3 3 2 Thermal Flux Radiated from Fregat s Attitude Control System As the Fregat attitude control thrusters are located in the vicinity of the spacecraft they may generate a heat flux that must be taken into account if sensitive equipment is located on the bottom surface of the spacecraft The heat flow Q distribution along the spacecraft bottom surface for one of the thrusters pair is given in Figure 3 7 where r the distance from the spacecraft longitudinal axis p the angle counted from the plane in the thrust direction where the
209. tly verifies their validity and he gives the relevant clearance for the any hazardous operations On request from the Customer the CSG can provide specific protection equipment for members of the Spacecraft team In case of the launch vehicle the Spacecraft and if applicable its co passenger imposes crossed safety constraints and limitations the Arianespace representatives will coordinate the respective combined operations and can restrict the operations or access to the Spacecraft for safety reasons Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management 7 7 Quality assurance 7 7 1 Arianespace s quality assurance system To achieve the highest level of reliability and schedule performance the Arianespace s Quality Assurance system covers the launch services provided to Customer and extends up to the launch vehicle hardware development and production by major and second level suppliers in addition to their proper system imposed by their respective government organization Arianespace quality rules and procedures are defined in the company s Quality Manual This process has been perfected through a long period of implementation starting with the first ARIANE launches more than 20 years ago and is certified as compliant with the ISO 9000 V 2000 standard The extension of the commercial operations to Soyuz does not affect the quality assurance system and the same rules are applie
210. tment C Quality monitoring of the industrial activities In compliment to the supplier s product assurance system Arianespace manages the production under the following principles acceptance of supplier s quality plans with respect to Arianespace quality management specification visibility and surveillance through key event inspection approbation through hardware acceptance and non conformity treatment Arianespace has access to the industrial anomaly resolution system build by Soyuz manufacturer since the 60 s combining failure review analysis and corrective actions for the whole Soyuz family The anomaly reviews and acceptance of the LV procurement gathers this experience and Arianespace methodological approach Arianespace January 2006 7 31 Soyuz CSG User s Manual Mission integration and Issue Draft management During the Launch campaign at Customer s request specific meetings may be organized with the Launch Vehicle and Quality authorities as necessary to facilitate the understanding of the anomalies or incidents The system is permanently under improvement thanks to the Customer s feedback during Launch Services Wash up meeting at the end of the mission 7 7 2 Customised quality reporting optional 7 32 In addition and upon request ARIANESPACE may provide the Customer with a dedicated access right and additional visibility on the Quality Assurance QA system by the implementation of e A Quality System
211. to allow remote control e Set of the ground cables for satellite verification The installation interfaces as well as environmental characteristics for the COTE are described in the Chapter 6 Arianespace January 2006 5 21 Soyuz CSG User s Manual Issue Draft GUIANA SPACE CENTRE Chapter 6 6 1 1 ntroduction 6 1 1 French Guiana The Guiana Space Centre is located in French Guiana a French Overseas Department D O M It lies on the Atlantic coast of the Northern part of South America close to the equator between the latitudes of 2 and of 6 North at the longitude of 50 West It is accessible by sea and air served by international companies on regular basis There are flights every day from and to Paris either direct or via the West Indies Regular flights with North America are available via Guadeloupe or Martinique The administrative regulation and formal procedures are equivalent to the one applicable in France The climate is equatorial with a low daily temperature variation and a high relative humidity The local time is GMT 3 h Figure 6 1 The French Guiana on the map Arianespace January 2006 6 1 Guiana Space Centre Soyuz CSG User s Manual 6 2 Issue Draft 6 1 2 The European spaceport The European spaceport is located between the two towns of Kourou and Sinnamary and is operational since 1968 The CSG is governed under an agreement between France and the European Space Agen
212. ture that takes the form of a truncated cone with a diameter of 1194 mm at the level of the spacecraft separation plane see Figure TBD Its minimal height 230 mm enables users to save as much space as possible in the volume under the fairing allocated to the spacecraft itself The adapter 1194 SF is equipped with a Saab 1194A separation system a standard Ariane device The spacecraft installed on top of the adapter is secured by a clamp band consisting of an iron strip that holds in place a series of clamps hooked onto the spacecraft and adapter interfacing frames see Figure TBD At separation the band is severed in two places by a bolt cutter mounted on the adapter with all pieces remaining captive to the adapter The spacecraft is then forced away from the launcher by 4 to 12 spring actuators that are also part of the adapter and that bear on the spacecraft rear frame see Figure TBD In this way the relative velocity between the spacecraft and the launcher can be adjusted to mission requirements Once the clamp band has been installed and the springs have been released each actuator applies a maximum force of 1200 N on the spacecraft rear frame with a 24 N tolerance Note that the clamp band tension does not exceed 30 100 N at any time including dispersions due to temperature variations on ground and in flight This ensures no gapping or sliding between the spacecraft and adapter interfacing frames during all phases of the mission The
213. ual launch system if used the adapter or dispenser Available payload adapters are shown in Appendix 4 and their masses are approximately 937 SF 45 kg Q1194 SF 110kg 01666 SF 100 kg Performance computations are based on the following main assumptions Sufficient propellant reserve is assumed to reach the targeted orbit with a 99 7 probability except otherwise specified The Fregat s fuel capacity is sufficient for deorbitation or for transfer to a safe orbit as required Aerothermal flux at fairing jettisoning is less or equal to 1135 W m Altitude values are given with respect to a spherical earth radius of 6378 km Launch from the CSG French Guiana taking into account the relevant CSG safety requirements Nevertheless the performance value may slightly vary for specific missions due to ground path and azimuth specific constraints The customer is requested to contact Arianespace for accurate data Data presented herein do not take into account additional equipment or services that may be requested in particular as function of mission duration ST fairing RD 0110 Soyuz 2 1a and RD 0124 Soyuz 2 1b third stage engines Arianespace January 2006 Soyuz CSG User s Manual Performance and launch mission Issue Draft 2 3 Typical mission profiles A typical mission profile consists of the following three phases e Ascent of the first three stages of the LV e Fregat upper stage flight profile for payload delivery to
214. uding transportation from the port of arrival of Spacecraft and support equipment CSG provides wide range of the road trailers trolley and trucks These means are adapted to various freight categories as standard hazardous fragile oversized loads low speed drive etc The spacecraft is transported either e inside its container on the open road trailer e in the dedicated Payload Containers CCU Container Charge Utile mainly between PPF and HPF and UCIF e encapsulated inside the Launch Vehicle Upper Composite between UCIF and Launch Pad The Payload Containers CCU ensures transportation with low mechanical loads and maintains environments equivalent to those of clean rooms Two Containers are available e CCU2 with maximum capacity 5 tons internal dimensions 3 65 x 10 38 m height e CCU3 with maximum capacity 22 tons internal dimensions 5 20 x 5 20 x 17 10 m Handling equipment including travelling cranes and trolleys needed for spacecraft and its Support equipment transfers inside the building are available and their characteristics are described in the EPCU User s Manual Spacecraft handling equipment is provided by the Customer refer to para 4 2 4 3 Figure 6 19 The CCU2 and CCU3 Payload containers Arianespace January 2006 6 25 Guiana Space Centre Soyuz CSG User s Manual Issue Draft 6 3 5 Fluids
215. ule Soyuz from CSG user s manual Manuel Utilisateur Soyuz du CSG Not Applicable Non Conformity Report Nitrogen Tetroxide Overall Acoustic Sound Pressure Level On Board Computer Overall Check Out Equipment Private Automatic Branch eXchange Central T l phonique Priv Pulse Coded Modulation Payload console Pressurization Depressurization Equipment Preliminary Design Review Payload access platform Proto Flight Model Transport platform Pyro Interception Plug Pupitre Charge Utile PlateForme CU PlateForme de Transport Prise d Interception Pyrotechnique Payload Local Area NETwork Preliminary Mission Analysis Preliminary Mission Analysis Document Preliminary Mission Analysis Review RAMP Revue d Analyse de Mission Pr liminaire Plan d Op rations Combin es Prise Ombilicale Electrique Plan d Op rations I mbriqu es Prise Ombilicale Pneumatique Plan des Op rations Satellite Combined operations plan Electrical umbilical plug Interleaved Operation Plan Pneumatic umbilical plug Spacecraft operations plan Payload Preparation Facility Propellant and Pressurant Loading Systems Payload safety console Pupitre Sauvegarde Charge Utile Power Spectral Density Quality Assurance Qualification Review Quasi Static Load equivalent to design load factor Quality System Meeting Quality System Presentation Quality Status Review Arianespace Soyuz CSG User s Manual Issue Draf
216. umigaseki Building 31FI 3 Shenton Way 3 2 5 Kasumigaseki Chiyoda ku Singapore 068805 Tokyo 100 6031 Japan Fax 65 62 23 72 68 Fax 81 3 3592 2768 Website French Guiana Launch Facilities Arianespace E BP 809 Www ANS RUE CAEN 97388 Kourou Cedex French Guiana Fax 594 594 33 62 66 This document will be revised periodically In case of modification introduced after the present issue the updated pages of the document will be provided on the Arianespace website www arianespace com before the next publication Arianespace 11 Soyuz CSG User s Manual Issue Draft Foreword Arianespace the business friendly launch service company Tuned to customer needs Arianespace is a fully industrial operational and commercial company providing complete personalized launch solutions In house flexibility is proposed through a family of powerful reliable and flexible launch vehicles operated from the same spaceport and providing a complete range of lift capabilities Ariane 5 the heavy lift workhorse for GTO missions provides through the dual launch policy the best value for money Soyuz the Ariane 5 complement in GTO is also perfectly suited for medium mass specific missions LEO escape Vega offers an affordable launch solution for small to medium missions Arianespace combines low risk and flight proven launch systems with financing insurance and back up services providing reactivity for quick res
217. under the launch table at the level 5 4 m Details of anti sismic racks installation and interfaces can be obtained from Arianespace Up to 2 anti sismic racks can be provided by Arianespace The equipments installed in the COTE are to be qualified either in acoustic or random wrt the following levels e Acoustic a Mer paw Qualification ss i32 es laze 123 neo 118 level dB Time duration 1 minute e Random eff on 3 axes The rooms are protected from the environment generated by the launch vehicle at lift off and they are not accessible during the launch Arianespace January 2006 6 15 Guiana Space Centre Soyuz CSG User s Manual Issue Draft LV assembly Launch control Road to building MI K center Sinnamary Launch pad Propellant storage areas Figure 6 15 Soyuz Launch Site 6 16 Arianespace January 2006 Soyuz CSG User s Manual Guiana Space Centre Issue Draft Figure 6 16 Launch Pad overview 62 32 32 Launch Centre CDL The Launch Centre which is located TBD km from the launch pad and houses the launch vehicle operational team launch desk and launch pad monitoring equipment The Launch Centre is used by the launch vehicle operational team for managing of the final launch preparation and launch and monitoring the health of the LV and LV s and launch pad readiness for the launch The Launch Centre is integrated in the CSG operational communication network providing capabi
218. ve followed a conservative evolutionary path of development and have been in continuous and uninterrupted production and flight for more than 45 years Owing to this development philosophy such vehicles have achieved a high launch rate as well as a high degree of reliability Table A5 1 shows a chronology of the most significant versions in this launch vehicle family Arianespace January 2006 A5 9 Table A5 1 Soyuz R 7 Family Evolution General view J ATi saa Al Designation R 7A Sputnik Molniya Voskhod First launch 1957 1958 1960 1963 1966 1 Stage Blocks B V G D Blocks B V G D Blocks B V G D Blocks B V G D Blocks B V G D 2m Stage Block A Block A Block A Block A Block A 3 Stage Block E BIOGR Block Block w o control system 4 Stage z Block L Status cane Out of production Operational Out of production Out of production production Fairings Soyuz Progress Capsule General view 1 Designation Soyuz First launch Stepwise introduction from 2004 st Blocks B V G D enhanced FG 1 Stage engine oe Stage Block A Block A enhanced FG engine Enhanced Block 3 Stage Block with digital control system and RD 0124 4 Stage Ikar Fregat Fregat Status Operational from CSG from 2008 Operational onwards Note Between 1982 and 1995 the more powerful Soyuz U2 configuration with Block A filled by synthetic fuel was used At present this configuration is out of production Ist and
219. ved mark DETAIL A 0 5x0 5 on one S C lateral axis e 1211 2 015 8 E C ve aT zl 3 01184 05 re 1215 05 10 025 Ta ACU1184SF SC Upper frame Rear frame COATING For surfaces in contact MODE See 4 4 1 between S C and ACU frames Chromic acid Chromic acid STIFFNESS Applicable length mm 25 Section area mi 460 15 Inertia ixx mm 51000 15 lyy mm 12000 15 DETAIL B 9 1215205 X 1209 17 0 13 1184 28 05 t 25 z 0 2x45 Imi 0 2 x 45 N a R 0 5 20 13 4 a we VS Lo E Em 9 1211 2 015 S 0 5x0 5 ENGRAVED REFERENCE MARK F ON ONE S C LATERAL AXIS 1238 0 3 i 1194SF Ogo 20 45 THE RADIUS WHICH HAVE NO DIMENSION 3 Figure A4 2 3 Adapter 1194 SF Interface frames A4 12 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters NO MLI ON SPACECRAFT FRAME FACING ACTUATORS 3 98 1 0 2 J 3 R 50 15 3 0 6 Reduced Stroke 66 3 1 Nominal Stroke SEPARATION PLANE Spring housing Figure A4 2 4 Adapter 1194 SF Actuators Arianespace January 2006 A4 13 Soyuz CSG User s Manual Standard Payload Adapters Issue Draft Limit of local allowable liri reina 1194 S C usable volume 157825 Q 4815 y E N 03 uim ii ba s 3 EL 95 S C o gt a xd 2 EX amp dem 7 z SEP PLANE __ CR g1215 Max allowable volume Max 9 6
220. xis km km e Eccentricity e Inclination deg deg e Argument of perigee deg deg e RAAN _ deg deg Orbit constraints e Any element constrained by the spacecraft injection time limitation aerothermal flux ground station visibility A1 2 2 Launch window s definitions A1 2 2 1 Constraints and relevant margins Targeted launch period launch slot Solar aspect angle eclipse ascending node moon constraints A1 2 2 2 Targeted window The targeted launch window shall be computed using the reference time and reference orbit described in the User s Manual if any The resulting launch window must include the dual launch window when applicable as specified in the User s Manual for any launch period The launch window s data is preferably supplied as an electronic file MS Excel Constraints on opening and closing shall be identified and justified Arianespace January 2006 A1 3 Application to use Soyuz CSG User s Manual Arianespace s launch vehicle Issue Draft A1 2 3 Flight manoeuvres and separation conditions A1 2 3 1 Attitude control during flight and prior to separation Any particular constraint that the spacecraft faces up to injection in the separation orbit should be indicated solar aspect angle constraints spin limitation due to gyro saturation or others Any particular constraint that the spacecraft faces after injection during the Roll and Attitude Control System sequence prior to separation
221. y training on the hazardous operations like fueling will be given to the appointed operators including operations rehearsals Arianespace January 2006 Soyuz CSG User s Manual Mission integration and Issue Draft management Table 7 2 Safety Submission Time Schedule Safety Submissions Typical Schedule Phase O Feasibility optional Before contract A Customer willing to launch a satellite containing signature inventive and innovating systems or subsystems can obtain a safety advice from CSG through the preliminary submission Phase 1 Design After the contract The submission of the Spacecraft and GSE design and signature and description of their hazardous systems It shall cover before PMA kick off component choice safety and warning devices fault trees for catastrophic events and in general all data enabling risk level to be evaluated End of Phase 1 submission Not later than PMA Review or L 12 m Phase 2 Integration and Qualification As soon as it The submission of the refined hardware definition and becomes available respective manufacturing qualification and acceptance and not later than documentation for all the identified hazardous systems L 12m of the Spacecraft and GSE The submission shall include the policy for test and operating all systems classified as hazardous Preliminary Spacecraft operations procedures should also be provided End of Phase 2 submission Not later than L 7m Phase 3
222. yuz adapters The general characteristics of the off the shelf adapters and adaptation structures are presented in the Table 5 1 A more detailed description is provided in the Annex 4 A dispenser design flight proven on previous missions is given in Annex 4 as an example Note In some situations the Customer may wish to assume responsibility for payload adapter dispenser In such cases the Customer shall ask the Arianespace approval and corresponding requirements Arianespace will supervise the design and production of such equipment to insure the compatibility at system level Arianespace January 2006 5 7 Spacecraft interfaces Soyuz CSG User s Manual Issue Draft Table 5 1 SOYUZ standard adapters H 750 mm 937B CASA Flight qualified Mars Truncated cone composite Express structure sandwich with CFRP 2003 skins and an aluminium honeycomb core The upper ring and the eight lower brackets are made of aluminium alloys M 40 kg Tension 27 7 kN H 230 mm 1194A SAAB Flight Tension 30 1 kN qualified M 110 kg Cluster Truncated cone composite mission structure sandwich with CFRP 2000 skins and an aluminium honeycomb core The upper and lover rings are made of aluminium alloys H 457 mm 1666H EADS CASA First flight M 90 kg d Truncated cone composite structure sandwich with CFRP skins
223. yway 1666 Adapter Adaptor connector in free position Two places Figure A4 4 5 Adapter 1666 SF Umbilical connectors A4 21 Arianespace January 2006 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft TO BE ISSUED LATER Figure A4 4 6 Adapter 1666 SF Usable volume A4 22 Arianespace January 2006 Soyuz CSG User s Manual Issue Draft Standard Payload Adapters A4 4 Dual launch structure An internal dual launch carrying structure similar in its principle to the Ariane SYLDA is being developed to offer dual launch opportunities The usable volume offered by this structure is presented in Chapter 5 3 4 Customers interested by this launch configuration are requested to contact Arianespace to get further details Arianespace January 2006 A4 23 Standard Payload Adapters Soyuz CSG User s Manual Issue Draft A4 5 Dispenser Dispensers are specific interface structures that are devoted to satellite constellation deployment and that allow for the handling and separation of at least two spacecraft per launch As mission requirements and constraints differ significantly from one constellation to another such structures are generally mission specific and thus cannot be considered off the shelf devices Consequently the information provided below with regard to the Globalstar dispenser is intended mainly to present Arianespace s ability to manage the development qualification
224. z 2267 5 MHz And 2284 MHz with a margin of 1 MHz The spacecraft transmission is allowed during ground operations Authorisation of transmission during countdown and or flight phase and spacecraft separation will be considered on a case by case basis In any case no change of the spacecraft RF configuration no frequency change no power change is allowed between Ho 1h30m until 20 s after separation During the launch vehicle flight until separation of the spacecraft s no uplink command signal can be sent to the spacecraft or generated by a spacecraft on board system sequencer computer etc For dual launch in certain cases a transmission time sharing plan may be set up on Arianespace request Spacecraft transmitters have to meet general IRIG specifications TO BE ISSUED LATER A specification of 100 dBuV m from 10 MHz to 20 GHz has to be considered before further refinement Figure 4 1 Spurious radiations acceptable to launch vehicle 4 6 Narrow band electrical field measured at the FREGAT adapter interface Arianespace January 2006 Soyuz CSG User s Manual Design And Verification Requirements Issue Draft 4 3 Spacecraft compatibility verification requirements 4 3 1 Verification Logic The spacecraft authority shall demonstrate that the spacecraft structure and equipments are capable of withstanding the maximum expected launch vehicle ground and flight environments The spacecraft compatibility must be

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