SKYLON USERS` MANUAL
Contents
1. the end of burn mass of 950 kg The different payload interface options do not alter the mass to within the errors and margins of the mass budget at 1ts current status 8000 7000 6000 5000 4000 3000 A Velocity m s 2000 1000 0 2000 4000 6000 8000 10000 12000 14000 16000 Payload kg Figure B2 SUS Performance B3 1 1 Expendable Mode The nominal orbit for deployment of the SUS on an expendable mode mission 1s a 190 km circular orbit with an orbital velocity of 7790 m s In this orbit the maximum deployed mass of SUS with 1ts payload 1s 16 tonnes For a Geostationary transfer orbit mission the maximum payload 1s achieved with a propellant load of 6 68 tonnes and this delivers a payload of over 8 25 tonnes With this mission the SUS places this payload into an orbit with the following characteristics Apogee altitude 35787 km Perigee altitude 190 km Inclination as launch site 31 SKYLON Users Manual Rev 1 1 B3 1 2 Reusable Mode For the reference reusable mission to geostationary transfer orbit the SUS carries a fuel load of 6 75 tonnes and this corresponds to a payload of 6 25 tonnes With this mission the SUS places this payload into an orbit with the following characteristics Apogee altitude 35787 km Perigee altitude 300 km Inclination as launch site B3 2 Payload Interfaces B3 2 1 USIS Envelope and Attachment The baseline payload interface2. 3 4 4 Heating Flux 3 3 Payload Services 3 5 1 Disconnectable Electrical Connection 3 5 2 Data Bus Connection 3 5 3 Propellant 3 6 Mission Duration 111 VI 11 11 15 16 SKYLON Users Manual Rev 1 1 4 GROUND OPERATIONS 4 1 Spaceport Description 4 2 Payload Integration 4 3 Launch and Landing Seguence ANNEX A UNIVERSAL SPACE INTERFACE SYSTEM USIS A1 INTRODUCTION A2 USIS DESCRIPTION A2 1 Operation Types A2 2 USIS Interface Ring A2 3 Active Clamps A2 4 Pin Cone Docking Connection A2 5 Hatch ANNEX B SKYLON UPPER STAGE SUS B1 INTRODUCTION B2 SUS DESCRIPTION B2 1 SKYLON Upper Stage B2 2 Mission Profile B3 PAYLOAD INTERFACES B3 1 Performance B3 1 1 Expendable Mode B3 1 2 Reusable Mode B3 2 Payload Interfaces B3 2 1 USIS Envelope and Attachment B3 2 2 1666Adaptor Envelope and Attachment B3 3 Electrical Interfaces 1V 19 19 19 21 25 25 25 26 27 27 28 29 29 29 29 31 31 32 33 SKYLON Users Manual Rev 1 1 ANNEX C SKYLON ORBITING FACILITY INTERFACE SOFI C1 INTRODUCTION C2 SOFI DESCRIPTION C3 PAYLOAD INTERFACES ANNEX D SKYLON PERSONNEL LOGISTICS MODULE SPLM D1 INTRODUCTION D2 SYSTEM OUTLINE D2 1 SPLM Description D2 2 Mission Outline D3 PAYLOAD PROVISIONS D3 1 Mass Capability D3 2 Under Floor CTB Provisions D3 3 Cabin Bays D3 3 1 Passenger Seats D3 3 2 ISS Eguipment Rack D3 3 3 CTB Carrier ANNEX
3. SKYLON USERS MANUAL ANNEXES ANNEX A UNIVERSAL SPACE INTERFACE SYSTEM USIS ANNEX B SKYLON UPPER STAGE SUS ANNEX C SKYLON ORBITING FACILITY INTERFACE SOFI ANNEX D SKYLON PERSONNEL LOGISTICS MODULE SPLM ANNEX E SKYLON SMALL PAYLOAD CARRIER SSPC These annexes present the user interfaces for various elements which compliment SKYLON to give 1t additional capabilities over the basic vehicle The majority of payloads around 80 will require the use of one of these elements The designs reflected here are far more conceptual than the design definition of the basic SKYLON vehicle and consequently may not reflect the final designs which will enter operation Nor are they likely to be the only systems fulfilling the various roles for example 1t 1s expected there will be several competing upper stages differing in size technology operational philosophy and cost Eventually as they come to realisation all these systems will have independent Users Manuals They have been included here to give a more complete picture of how SKYLON will appear to users on entry to service It 1s hoped that by providing this broader picture of an operational SKYLON better feedback can be obtained on the suitability of the basic design 23 SKYLON Users Manual Rev 1 1 24 SKYLON Users Manual Rev 1 1 ANNEX A UNIVERSAL SPACE INTERFACE SYSTEM USIS A1 INTRODUCTION This annex defines the docking berthing Interface used b
4. 1 00E 04 Pressure Pa Figure 17 Payload Bay Ambient Pressure during Ascent and Descent 15 SKYLON Users Manual Rev 1 1 The design maximum rate of depressurisation during ascent is 700 Pa sec for 30 seconds and during descent 1t 1s 300 Pa sec 3 4 4 Heating Flux While in the payload bay the payload bay wall temperature is between 0 C and 20 C assuming that the payload 1s not powered and acting as a further heat source If suborbital deployment as outlined in section 3 2 1s employed then at the point of deployment the aerothermal heating load is below 1150 W m Other heating factors such as solar and Earth radiation fluxes are not included in this value Orbital deployment induces no appreciable aerothermal heating load 3 3 Payload Services 3 5 1 Disconnectable Electrical Connection Each SKYLON payload attachment point interface has a Disconnectable Electrical Connection which can provide electrical power and some status signals to the payload This connection is an integral part of the keel trunnion and the pin functions are defined in Figure 18 The payload electrical power connection provides a maximum 15 A at 28 V DC nominal to MIL STD 704F for reference this corresponds to a nominal power of 420 watts The total energy available to the payload throughout the mission starting when payload power supply 1s connected during integration is 500 A hr If two payloads are sharing the bay the maximum current tha
5. Definition Length 83 3 m Maximum air breathing thrust 2x 1350 kN Fuselage diameter 6 75 m Isp in air breathing mode 35000 N s kg Wingspan 25 4 m Maximum thrust in rocket mode 2x 1800 kN Unladen mass 53 tonnes Isp in rocket mode 4500 N s kg Propellant mass 271 tonnes Thrust range rocket mode 55 100 Nominal take off mass 345 tonnes Operational life 200 flights Table 1 SKYLON Configuration C2 Features SKYLON s main structure consists of a space frame constructed from carbon fibre reinforced plastic struts The non structural aluminium propellant tanks are suspended within the framework by Kevlar ties The frame 1s covered with sheets of a reinforced glass ceramic material which acts as the aeroshell and main thermal protection backed by a multilayer metallic heat shield SKYLON Users Manual Rev 1 1 In addition to the main propulsion system tanks there are a set of secondary cryogenic tanks which feed the orbital manoeuvring engines the reaction control thrusters and the fuel cell power supply 2 2 SABRE Engine SKYLON is powered by a combined cycle rocket engine which has two operational modes In one mode air captured from the atmosphere is used as the oxidiser and in the other liguid oxygen from the internal tanks is used as the oxidiser The SABRE engine Figure 3 uses sub cooled liguid hydrogen as its fuel and sub cooled liguid oxygen as the oxidiser in rocket mode In rocket mode the engine operates as a closed cycle h
6. E SKYLON SMALL PAYLOAD CARRIER SSPC El INTRODUCTION E2 SSPC DESCRIPTION E3 PAYLOAD INTERFACE E3 1 Mechanical Interfaces E3 2 Electrical Interfaces E3 3 Mass Properties 35 35 36 37 37 27 38 38 38 39 39 41 41 41 41 42 42 AFDX ASAP CTB DC FAA GEO GTO hr Hx ISO Isp ISS kg km kPa L D LEO LH LOX MECO mm N OMS Pa PAS 1666S RMS S SABRE SOFI SOMA SPLM SSPC SUS TBD USIS V W SKYLON Users Manual Rev 1 1 Acronyms and Abbreviations Amperes Avionics Full DupleX switched ethernet ARIANE Structure for Auxiliary Payloads Degrees Celsius Cargo Transfer Bag Direct Current Federal Aviation Administration Surface acceleration due to Earth s gravity Geostationary Earth Orbit Geostationary Transfer Orbit Hour Heat Exchanger International Standards Organisation Specific Impulse International Space Station Degrees Kelvin Kilogrammes Kilometres Kilo Newtons Kilo Pascals Lift to Drag Ratio Low Earth Orbit Liguid Hydrogen Liguid Oxygen Metres Main Engine Cut Off Millimetres Newtons Orbital Manoeuvring System Pascals Payload Adaptor System 1666S Remote Manipulator System Seconds Synergistic Air Breathing Rocket Engine SKYLON Orbiting Facility Interface SKYLON Orbital Manoeuvring Assembly SKYLON Personnel Logistics Module SKYLON Small Payload Carrier SKYLON Upper Stage To Be Determined Universal Spacec
7. Personnel Logistics Module SPLM which enables SKYLON to carry people and logistic supplies to orbital facilities The mix of passengers and logistics 1s very flexible but 1f optimised for passenger flight 1t can carry 24 people D2 SYSTEM OUTLINE D2 1 SPLM Description The SPLM is shown in Figure Dl It is a pressurised structure with an internal cabin diameter of 4 meters and a length of 8 5 meters Figure DI SKYLON Personnel Logistics Module SPLM The SPLM adds all the functions to SKYLON for human spaceflight In addition to a controlled pressurised cabin which stores seating and logistics it provides a simple galley and two hygiene facilities It also enhances the basic SKYLON provision with its own fuel cell power system thermal control and additional independent video and voice communications links The primary safety philosophy 1n the event of an accident 1s for the cabin to be a survivable safe haven in which the passengers stay until the hazard has passed It is structurally independent of SKYLON and in a crash uses the SKYLON structure as an energy absorbing crumple zone The exterior has heat shielding which can survive in a fire fuelled by the propellants The cabin is airtight and its control does not require any functions external to the cabin Should the cabin integrity be breached the passengers are eguipped with simple pressure suits In the event of an 1n flight disintegration of the SKYLON vehicle 1f the cabi
8. deployed during this mission is 30 tonnes which is determined by the structural strength of the payload interfaces However the payload must use some of this mass to provide its own propulsion system or a dedicated propulsion stage in order to raise itself to its operational orbit Typical velocity increments which will be necessary are To 300 km circular orbit A V1 858 m s A V2 42 m s 2 burn Hohmann transfer To GTO AV 3286 m s To escape velocity 4056 m s local escape velocity 11 051 m s 10 SKYLON Users Manual Rev 1 1 Individual users may calculate their propulsion reguirements on a case by case basis using the above data 3 2 Injection Accuracy The precise payload injection accuracy for SKYLON has not yet been established but it will be high The targets for an orbital deployment are to have an orbital inclinatlon accuracy of 0 01 degrees prior to deployment and to have the payload achieve a positional accuracy of 10 m and a velocity accuracy of 0 01 m s after deployment 3 3 Envelope and Attachments The SKYLON payload bay Figure 12 is sized to scope most existing launch system payload envelopes and be appropriate to the 15 tonne mass capability It 1s located at the centre of the vehicle over the wing structure and has a U shaped cross section with two opening doors above it which once in orbit expose the payload to space l Figure 12 The SKYLON Payload Bay The bay has two pavload interfaces
9. for the SUS is the USIS This can be the simple integrated variant but if the stage is to be reused then the Passive Unpressurised Docking variant 1s reguired and the pin cone protrusions above the interface plane need to be accounted for The envelope available to the payload envelope for the SUS is defined in Figure B3 The cross section is as the normal SKYLON deployment envelope defined in Figure 13 1 LI LI LI LI i 1450 Envelope with i reusable stage i 1 1 LI LI LI 1 1 1 LI LI Front pavload attachment centreline i USIS interface 5 799 Plane Figure B3 SUS with USIS Interface Payload Envelope B3 2 2 1666 Adaptor Envelope and Attachment For an expendable mission the SUS payload interface can be made compatible with the Ariane 5 PAS 1666S adaptor as defined in the Ariane 5 User Manual Issue 5 Revision O July 2008 The connection is an aluminium ring with the payload held in place with a clamp band Separation is via a soft opening of the clamp band and 12 separation springs equi spaced outside the ring The payload envelope and key features of the mounting interface are defined in Figure B4 The cross section 1s as the normal SKYLON deployment envelope defined in Figure 13 As currently 32 SKYLON Users Manual Rev 1 1 envisaged the overall payload interfaces would be identical or less constraining than on Ariane 5 with the exception of the facilities for nitrog
10. one 1n the front and the other at the rear The front location has provisions to load crvogenic oxvgen hvdrogen and helium but in all other respects the two interfaces are identical and mirror each other A pavload can therefore be placed at either end without alteration Pavloads will use the provision which locates the centre of mass to be within the constraints defined in Section 3 3 3 this will in most cases be the front mounting It is possible to use both attachments simultaneously to mount two pavloads in the bay at one time providing that when combined the mass and mass properties constraints are met 11 SKYLON Users Manual Rev 1 1 3 3 1 Payload Bay Envelope The volume available to the payload and the location of the payload attachments in the SKYLON payload bay are shown in Figure 13 This is a static volume and assumes a 20 mm allowance for payload dynamic movement outside this envelope Deployed payload Fixed or RMS removed envelope payload envelope L 2400 2400 3Port protrusions Sill mounting centreline 142 ie Sna Paylo ad b ay Y centreline Fuselage 10 deg Ref Centre S Dimensions in mm Payload envelope Payload bay X centreline and Keel mounting centreline Largestenclosed cylinder Skylon Structure 1 1 1 J Sill Sill attachment attachment Payload bay centreline Clea
11. or drogue is guided to the centre of the cone where capture latches in the pin s tip engage and make the initial connection These have been used on past docking systems for example Apollo and Soyuz However in these cases the two ports to be mated were different one was with the pin or drogue and the other with the guide cone To make the USIS port androgynous the port has both a pin and a cone offset from the centre Only the pin 21 SKYLON Users Manual Rev 1 1 on the active side needs to activate its capture latches whilst the other passive pin in the active side s cone takes out rotational misalignments The USIS pin has a conical guidance skirt beneath the capture latches to take out rotational misalignments about X and Y axes Both the cone and pin extend beyond the interface plane The cone protrudes by 110 mm and the pin by 198 mm To make the USIS a soft dock system the active pin is mounted to a Stewart platform which can control the pin with a sufficient 6 degrees of freedom movement This is to enable it to be guided with minimal force into the cone s receptor before engaging the capture latch A2 5 Hatch The key reason for adopting the twin offset pin cone docking arrangement is to enable the hatch in the pressurised variants of the USIS to fully utilise the 1480 mm internal diameter of the interface ring The resulting hatchway dimensions are defined in Figure A4 616 616 Figure A4 USIS Hatch Openin
12. to Geostatlonary Transfer Orbit GTO from a near eguatorial launch site The SUS its payload in the front payload position and a recovery system mounted in the rear position are launched into a 300 km altitude circular orbit which has a 7 1 resonance with the GTO After deployment the SUS places the payload into GTO with a perigee burn After one complete orbit it performs another circularisation burn to place it back into a 300 km LEO which 1s close enough for the SKYLON that launched it to dock safe the stage and return to the forward payload location for return to Earth Because of the need to dock the SUS for recovery reusable missions will reguire the use of the USIS interface The use of the SUS as the make up propulsion with suborbital deployment manoeuvre as described in section 3 1 2 1s also possible This mode will increase the both the total and specific LEO launch costs as the cost of the SUS and the cost recovery from the downrange landing site must be included This mode 1s expected to be used when the payload 1s larger than the SKYLON s orbital capability and it 1s not practical to divide the payload up and assemble 1t in orbit 30 SKYLON Users Manual Rev 1 1 B3 PAYLOAD INTERFACES B3 1 Performance Figure B2 gives the AV the SUS can provide against payload mass as determined by the rocket eguation given the SOMA engines have a specific impulse of 4562 N s kg the stage has maximum usable fuel load of 7000 kg
13. Delivered Mass for 15 degree Launch Site Payload Launch Site Latitude 30 Tonnes 17 ej F aj es 3100 TRA rss 2 Lo App 11 me mo T T 9 Or SO g 14 l Tr gp V S S A al l Br PR 4 AA eee ll T 2 98 SJ ees ee ee es ee A 200 300 400 500 600 700 800 Altitude Km Figure 8 Delivered Mass for 30 degree Launch Site SKYLON Users Manual Rev 1 1 Payload Launch Site Latitude 45 Tonnes 17 jr f J S A A _ d ja ff E Ll tp __ ml sol lol _ d ja A As E E sd T g OE 45 gt L gq slo o Lai ado O ee ee L I gq Y PA sq LE 88 a mg E eee L T VEN E rom 200 300 400 500 600 700 800 Altitude Km Figure 9 Delivered Mass for 45 degree Launch Site Payload Launch Site Latitude 60 Tonnes bi Lo e II mxo J mx J pm mL S S 2 1 e tt 1 TAR TT a E Pe O 7 lA ll ee A A E Y FP A A e ll TI a TL a gt E e es O AAA i E 200 300 400 500 600 700 800 Altitude Km Figure 10 Delivered Mass for 60 degree Launch Site SKYLON Users Manual Rev 1 1 3 1 2 Suborbital Deployment SKYLON has the capability of maximising the payload mass by performing a suborbital deployment and using a payload supplied propulsion system to pe
14. PLANE 200 VIEW ON A ITOSEAT 2000 EDGE UNDERFLOOR CTH STORE UNDERFLOOR CTB STORE Figure D3 Cabin Bay Dimensions D3 3 1 Passenger Seats There are two types of passenger seat which can be installed in each bay upright seats and supine couches The upright seats are intended for personnel undertaking a short term visit to space less than 14 days These seats contain storage provisions for a single CTB for the passenger s personal luggage The supine couches are intended for personnel undertaking long term visits to space over 14 days These seats contain storage provisions for two single CTBs for the passenger s personal luggage The mass allowance for each seat is 190 kg for the upright seat and 195 kg for the supine seats This includes the passenger the seat a 20 kg single CTB for personal effects stored in the seat and a pressure suit The seat also has a 4 day supply of oxygen and lithium hydroxide As expected the life support consumables increase as passenger seats are added D3 3 2 ISS Equipment Rack Each bay has the basic mounting provisions for one standard ISS Equipment Rack with a mass up to 700 kg The mounting provisions the width 1014 mm and height 2016 mm remain as the existing ISS standard However the depth is additionally constrained to 800 mm compared with around 900 mm in the existing ISS standard due to door and hatchway limitations 39 SKYLON Users Manu
15. SKYLON USERS MANUAL Contact One of the purposes of this document is to elicit feedback from potential users as part of the validation of SKYLON s requirements Comments are most welcome and should be sent to Reaction Engines Ltd Building D5 Culham Science Centre Abingdon Oxon OX14 3DB UK Email enquiries reactionengines co uk SKYLON Users Manual Rev 1 k NES tt EN GI i REACTION SKYLON USERS MANUAL Compiled Mark Hempsell and Roger Longstaff Authorised Alan Bond Doc Number SKY REL MA 0001 Version Revision 1 1 Date Jan 2010 Reaction Engines Limited 2009 Reaction Engines Ltd Building D5 Culham Science Centre Abingdon Oxon OX14 3DB UK Email enquiries reactionengines co uk SKYLON Users Manual Rev 1 1 Frontispiece SKYLON Take off 11 SKYLON Users Manual Rev 1 1 SKYLON USERS MANUAL Contents Acronyms and Abbreviations 1 INTRODUCTION 1 1 Scope 1 2 Purpose 2 VEHICLE DESCRIPTION 2 1 SKYLON Configuration C2 2 2 SABRE 2 3 Typical Mission Profile 3 PAYLOAD INTERFACES 3 1 Payload Mass 3 1 1 Orbital performance 3 1 2 Suborbital Performance 3 2 Injection Accuracy 3 3 Envelope and Attachments 3 3 1 Payload Bay Envelope and Attachment 3 3 2 Attachment Interface 3 3 3 Payload Centre of mass Constraints 3 4 Environment 3 4 1 Load Environment 3 4 2 Acoustic Environment 3 4 3 Atmosphere Environment
16. acted along the Z axis The payload sill attachment also incorporates a deployment mechanism to eject the payload during flight without the need for any additional eguipment The sill attachment opens to release the trunnions and two synchronised actuators push on the sill trunnions with a travel of 200 mm along 13 SKYLON Users Manual Rev 1 1 the guides shown in Figure 13 These guides are supplemented by the keel trunnion which also reacts the cantilever loads The mechanism accelerates at 0 66 m s to give a release velocity of 0 5 m s 3 3 3 Payload Centre of Mass Constraints In addition to the overall mass constraint determined by SKYLON s overall performance defined 1n sections 3 1 1 for orbital mission and 3 1 2 for suborbital missions there are constraints on the payload mass due to centre of mass constraints imposed by the limitations of SKYLON s pitch control system during re entry The centre of mass versus overall mass constraints which are applicable to the X axis are shown in Figure 16 Note the payload bay fittings are sized for a maximum payload mass of 30 tonnes Maximum Payload Front Bay Rear Mass Attachment Centreline Attachment tonnes al 30 l l l 1 al er T PS ON awn lU HE Ps sm 0 Ms Hami 6 5 4 3 2 1 0 1 2 3 4 5 6 Payload Centre of Mass Along A axis m O Figure 16 Maximum Payload Mass versus Payload Centre of Mass along X axis In the Y and Z
17. ad by the rear 50 mm sguare section of the sill trunnions Figure 15 Once in the payload bay the loading rack is disconnected and the SKYLON hold downs clamps are activated The electrical connectors 1n the keel trunnion are made by the loading without further action If data bus or propellant connections are reguired they are made by hand and are accessed from the ground access doors while the payload 1s mounted 1n the bay Payload preparation bays 50 2s SC u I Smer Overhead crane corridor Operator Offices a Terminal Figure 21 SKYLON Hanger and Payload Integration Facility s MA Main Area 40 m x20 m Access doors 8m x 8m m os Figure 22 Interior of SKYLON Payload Integration Facility 20 SKYLON Users Manual Rev 1 1 There are two access doors to the payload bay The location and size are shown in Figure 23 One 1s at the front of the bay on the port side and the other at the rear on the starboard side They are positioned in this way in order to enable the same access to the payload whether it is located in the front or rear payload mounting interface The door opening 1s sized to correspond to a FAA Type B emergency exit FAR Part 25 Section 807 520 512 i A i Sill attachment 200 i l I I m l 1 1 L Front access door Port side payload attachment centreline Rear acces
18. al Rev 1 1 D 3 3 3 CTB Carrier Each bay can be fitted with a CTB carrier to supplement the permanent under floor provisions This mounts on the same interface as the ISS Equipment Racks but it cannot pass through the docking berthing port and so cannot be moved to the orbiting facility The CTB Carrier has 9 triple CTB bays in a 3 by 3 array The carrier structure has a mass of 60 kg Each bay can carry a total of 80 kg up to a maximum for all 9 bays of 640 kg The total maximum installed mass for the CTBS and carrier structure 1s 700 kg 40 SKYLON Users Manual Rev 1 1 ANNEX E SKYLON SMALL PAYLOAD CARRIER SSPC E1 INTRODUCTION This annex outlines the user interfaces for the SKYLON Small Payload Carrier SSPC The purpose of the SSPC 1s to carry payloads which are too small to be realistically carried by the main SKYLON interface It is the SKYLON equivalent of the Space Shuttle s Getaway Special carrier or the Ariane 5 ASAP platform It gives SKYLON the capability to fly small satellites and fixed payloads E2 SSPC DESCRIPTION The SSPC Figure El is an aluminium bridge structure across the payload bay with five payload mounting locations each in separate bays There is a limited avionics capability to distribute the power and command signals provided by the SKYLON vehicle defined in section 3 5 1 to each payload It is envisaged that it would normally be flown as a payload of opportunity when the mass and d
19. axes the payload centre of mass must not produce a moment greater than 60 000 N m about the payload bay reference axis 14 SKYLON Users Manual Rev 1 1 3 4 Environment 3 4 1 Load Environment The guasi static design limit loads applicable to the payload are given in Table 2 CASE 39 0 5 g 0 5 g 298 0g 0 5 g 0 5 g 29 0g Table 2 Ouasi Static Design Loads Loading on payloads mounted to the complimentary systems such as the SKYLON Upper Stage Annex B or the SKYLON Small Payload Carrier Annex E have not vet been determined but are unlikely to greatly exceed those in Table 2 3 4 2 Acoustic Environment The acoustic environment in the payload bay has not yet been determined but is expected to be below 100 dB at all freguencies where 0 dB corresponds to 2 x 10 Pa RMS 3 4 3 Atmosphere Environment Once the payload bays doors are closed in the integration hall the payload bay is purged to a pure dry nitrogen atmosphere with a pressure of 102 kPa 0 5 kPa and a temperature between 10 C 40 C During ascent the nitrogen in the payload bay is vented to the ambient static pressure During re entry descent dried air is introduced into the payload bay again to match the ambient static pressure Figure 17 shows the pressure history during ascent and re entry to and from 80 km altitude 1 00E 05 QUE O2 f 0 O0E 03 L L 1000 1500 2000 2500 3000 3500 4000 4500 Time seconds
20. ce stations while leaving most of the payload bay available for the main payload which once the SOFT has connected the SKYLON and the facility can be removed C2 SOFT DESCRIPTION SOFI Figure C1 mounts in the rear payload location and has a standard USIS docking port to connect to the orbiting facility The port is held in the rear payload bay protrusion by five struts which connect back to a U shaped frame which stretches across the payload bay This frame is also the structure to which the other eguipment and the hold down trunnions are mounted Figure Cl SKYLON Orbiting Facility Interface SOFT In addition to the docking berthing port the SOFT carries the radar and optical alignment system needed for final approach and alignment to the orbital facility It also has a standard grapple point to enable SKYLON and its payload to be captured in free flight and then berthed as opposed to docked if the orbiting facility has a Remote Manipulator System The design philosophy is that the main payload needs no provisions to reach the facility except a grapple point 1f it is required to be removed from the bay Although primarily designed to deliver unpressurised payloads the port is a capable of being pressurised The concept design has added a small pressurised container to the docking port which can carry a double Cargo Transfer Bag up to 50 kg in mass The flight can therefore be used to deliver a small amount of urgent or otherwise opportune l
21. d in Table El PIN FUNCTION SPECIFICATION 28 V 4 V for 2 seconds 28 V 4 V for 2 seconds Table El Electrical Connector Pins The total power drawn by the SSPC has been limited to ensure that the electrical power available to the main payload is not changed by the inclusion of a fully laden SSPC E3 3 Mass Properties The SSPC has a mass of 260 kg and occupies 0 05 m towards the payload bay centre and 0 88 m towards the payload bay end Centre of mass of an unladen SSPC relative to payload bay centre is X 3 55m Y 0 05 Z 0 09 It 1s possible for all of the payload bays to be fully occupied in the rear position without exceeding the mass constraints defined in Section 3 3 3 42 All CGI artwork by Adrian Mann www bisbos com U nioeoogooooo P U I ON ENGINES Reaction Engines Ltd Building D5 Culham Science Centre Abingdon Oxon OX14 3DB UK www reactionengines co uk Email enguiries Oreactionengines co uk
22. e a technical definition of the SKYLON spaceplane to its potential stakeholders 11 to provide a controlled definition of the user interfaces at a level comparable to other launchers This definition will be an aid for technical studies by those wishing to use SKYLON as the assumed launch system 111 to elicit feedback from potential users on the performance and interfaces as currently envisaged This will act as the key validation of the user requirements before finally committing to the system development stage The SKYLON launch system has the reguirement to be able to place payloads into Low Earth Orbit LEO However many payloads reguire higher energy orbits or need to be delivered to orbiting facilities or are too small to match the payload mounting provisions To meet the additional reguirements SKYLON will have a range of complimentary systems to extend its capability These include An upper stage capable of reaching other Earth orbits and escape trajectories called SKYLON Upper Stage SUS An adaptor to enable docking and berthing with orbiting facilities called SKYLON Orbiting Facilities Interface SOFT A pressurised module that can carry crew and logistics called SKYLON Personnel Logistics Module SPLM A carrier structure capable of carrying smaller payloads called the SKYLON Small Payload Carrier SSPC The user interfaces for these complimentary systems are given in Annexes A E The systems
23. ear interface positions The precise connection type and its location are not yet established but it will be located in the area defined in Figure 19 Payload Bay i Centreline 1400 Access Door i Figure 19 Pavload Connector Location PAYLOAD CONNECTOR AREA Payload L Attachment 1 Centreline Connect The form of the main SKYLON data bus has not yet been established It will be a flexible architecture high data rate standard which can be certified to meet aerospace safety requirements It could be an existing aircraft standard such as AFDX or it could be an enhanced version of a space standard such as Spacewire Given the complex interactions this interface generates 1t 1s only available in special circumstances and the compatibility analysis would incur significant extra costs over the basic launch cost for the payload use It 1s envisaged that basic infrastructure elements such as the SUS SOFI and SPLM which extend SKYLON s capability would be used many times 17 SKYLON Users Manual Rev 1 1 3 5 3 Propellant Supply The front payload attachment interface has the provision for the payload to connect into SKYLON s propellant fill drain and venting system These provisions are defined in Table 3 Propellant Liguid Hydrogen I Fill drain Liguid Oxygen Eill drain 2 Fill drain Table 3 Propellant Delivery Connections The exact nature of these connections has not y
24. en purge on SKYLON Front payload attachment centreline Separation 799 plane Figure B4 SUS 16665 Compatible Attachment Interface This interface 1s capable of carrying a maximum mass of 9 tonnes and a moment of 22 500 kg m Other adaptor standards could also be accommodated Like the 1666 Adaptor these would attach to the SUS via a specialist cone structure connecting back to the main panel using 64 M8 bolts equi spaced on a 3240 mm diameter circle B3 3 Electrical Interfaces A power supply of 28V and 0 5A maximum current 1s available to the payload The commands and telemetry available to the payload are TBD but will be consistent with the data link provisions of the USIS 33 SKYLON Users Manual Rev 1 1 34 SKYLON Users Manual Rev 1 1 ANNEX C SKYLON ORBITING FACILITY INTERFACE SOFI C1 INTRODUCTION While SKYLON can perform the orbital manoeuvres to rendezvous with orbiting facilities it does not have the provisions reguired to physically connect either by docking or berthing as part of the main airframe If this function is reguired it must either be integrated into the payload or a SKYLON Orbiting Facility Interface SOFI must be flown with the payload This annex describes and defines the user interfaces for the SOFI The SOFI provides means by which SKYLON with a main unpressurised payload can dock or berth as 1t has provision for both types of operation with orbiting facilities such as spa
25. et been determined but their location is in the area defined in Figure 19 These capabilities are expected to be used with upper stages using cryogenic propellants such as the SUS or systems like the SPLM which use fuel cells to generate electrical power Given the complex interactions this interface generates it is only available in special circumstances and would incur significant extra costs over the basic launch cost for the compatibility analysis 3 6 Mission Duration SKYLON can remain on orbit for up to 4 days This must include any contingency time to handle any problems that might develop during the mission so 1t 1s anticipated in most instances the nominal mission time would be no more than 2 days 18 SKYLON Users Manual Rev 1 1 4 GROUND OPERATIONS 4 1 Spaceport Description SKYLON operates like an aircraft Its integration and servicing occur in a hanger it is supported horizontally on its undercarriage and for flight it 1s towed out to a runway for fuelling and take off The location and detailed design of the launch site or sites have not yet been established therefore this section describes an idealised flow for launch facilities and operations which would alter from port to port and operator to operator It follows that the interfaces defined here are more indicative and illustrative than definitive Figure 20 shows a conceptual spaceport layout It centres on a 5 5 km runway for exclusive use by the SKYLON veh
26. from various launch site latitudes The graphs show the payload mass delivered into circular orbit plotted against orbital altitude Each graph has a series of curves for various orbital inclinations The value for 52 1s given as this is the inclination of the ISS and an inclination of 98 is given as an approximation to a Sun Synchronous orbit Where the orbit inclination is below the launch site latitude the results are not given in general as these orbits are not practical The current established maximum orbital altitude is 800 km as the ability for SK YLON to return above that altitude has not been fully evaluated If altitudes greater than 800 km are of interest please contact Reaction Engines Limited to establish their feasibility Payload Launch Site Latitude 0 Tonnes 17 gi Et a L L 41 A S y o Bq re a A r Oe mi o me M Al a 10 LA SA si im o Be T A LO ina O FA S OO 2 TIT S GO ees GA Hd S EE A Fa S eee eee F II Y a4 3 Pn as FS 1 ee eee eee eee A g 200 300 400 500 600 700 800 Altitude Km Figure 6 Delivered Mass for Eguatorial Launch Site SKYLON Users Manual Rev 1 1 Payload Launch Site Latitude 15 Tonnes 11 o_O TI ma b ml TT o 30 ks US qd ee S 71 EE 2 dc BI Pi KN IM q eee G LP i 1 ggo p Ll OJ n eee 200 300 400 500 600 700 800 Altitude Km Figure 7
27. g Dimensions 28 SKYLON Users Manual Rev 1 1 ANNEX B SKYLON UPPER STAGE SUS B1 INTRODUCTION SKYLON has only the capability to place payloads into Low Earth Orbit To reach higher orbits and Earth escape orbits reguires an upper stage It 1s anticipated many commercial upper stages would be developed for SKYLON filling specialist market needs and trying to exploit some technical or commercial innovation However there will be one stage that 1s developed as part of the SKYLON system to provide a full launch capability on entry into service This is called the SKYLON Upper Stage SUS The SUS stage is optimised to provide the maximum payload into geostationary transfer orbit from a once round suborbital deplovment However it can also deliver effective payloads to all high earth and planetary escape orbits using both sub orbital and orbital deployment and it can also lift payloads into Low Earth Orbit that are substantially heavier than SKYLON alone can achieve using down range suborbital deployment In some cases the SUS stage can be recovered for reusability This annex describes and defines the user interfaces for the SUS B2 SUS DESCRIPTION B2 1 SKYLON Upper Stage As shown in figure B1 the SUS has a compact design to minimise the payload bay occupied by the stage and hence maximise the volume available to the payload A disk shaped 4 7 m diameter panel is the main structure The attachment trunnions are directly connected to t
28. h time it fires its orbital manoeuvring system OMS engines in order to circularise the orbit After routine system checkouts the vehicle opens its payload bay doors and deploys its payload The payload then proceeds with its mission independently SKYLON Users Manual Rev 1 1 40 30 20 10 150 mofo a a wo Y wo fo oN ato f e O E y Zo s XM u gdi ee l S7j jp E NI PT sf ON EA TB T OA EET YAA Y L A NA 0 1000 2000 3000 4000 Time seconds Figure 5 Descent Trajectory The SKYLON vehicle now returns to 1ts base After the payload bay doors have been closed the OMS engines make a retrograde burn in order to achieve a suitable velocity vector for re entry This manoeuvre 1s timed to return the vehicle to 1ts launch site or any other nominated landing site via a pre calculated trajectory The vehicle descent trajectory 1s unpowered with energy management achieved through S turns as a glider in the same manner as the Space Shuttle but with much increased manoeuvrability due to a higher L D ratio and the vehicle lands automatically A typical descent trajectory 1s shown in Figure 5 Landing speed 1s around 130 knots 65 m sec with crosswinds of up to 30 knots The SKYLON vehicle 1s then serviced and prepared for its next mission SKYLON Users Manual Rev 1 1 3 PAYLOAD PROVISIONS 3 1 Mass 3 1 1 Orbital Deployment Figures 6 to 10 below give SKYLON s performance for orbital deployment
29. he passive active option there 1s a 16 element functional matrix of operational options as shown in Figure A2 Figure A2 also shows that the 16 options can be accommodated by 8 implementations of the USIS standard Integrated Berthing Hard Dock Soft Dock Unpressurised Passive Figure A2 USIS Functional Variants Unpressurised Active Pressurised Passive Pressurised Active The mass of the USIS will clearly depend on what version is incorporated and how it is integrated into the final systems It thought to range from 130 kg including mounting cone or cylinder for an unpressurised passive ring only version to 360 kg for an active pressurised soft dock system A 2 2 USIS Interface Ring The most basic version consists of the interface ring and the bolt holes and would be used for permanent ground integration of two systems such as the space station modules which will be launched mated together This ring 1s the foundation of the USIS It has an outer diameter of 1620 mm and a minimum inner diameter of 1480 mm It has the following functions 26 SKYLON Users Manual Rev 1 1 the main bearing surface a redundant pair of sealing O rings 8 Bolts for a permanent connection or with explosive bolts if separation is reguired 4 spring locations and corresponding pusher plates 4 Berth guides that take out 30 mm of misalignment 4 Capture clamps used with clamps mechanisms for multiple attachments 1 set of elec
30. his panel as is the liguid oxygen tank The toroidal hydrogen tank and engine assembly are connected to a cantilevered truss structure The payload mounting interface connects to the other side of the panel by a conical structure The payload interface can be either the USIS described in Annex A or a conventional marmon clamp interface such as the Ariane 5 PAS 1666S The engine is the SKYLON Orbital Manoeuvring Assembly SOMA used by SKYLON as primary propulsion after MECO It uses liguid oxygen and liguid hydrogen propellants and has inherent usability derived from its role on SKYLON This assembly consists of 2 engines each with 2 thrust chambers and provides a total thrust of 50 kN B2 2 Mission Profile The SUS 1s loaded into the SKYLON payload bay with its payload already integrated but without propellants Once SKYLON 1s on the fuelling apron the liguid oxygen and liguid hydrogen propellants for the SUS are loaded as part of the overall loading process through the connections defined in section 3 5 3 The stage can be used in both an expendable and reusable mode In a nominal expendable mission SUS deployment takes place from a very low Earth orbit with an altitude of 190 km Deployment would take place on the first orbit with a minimum of 10 minutes between deployment and SUS main engine burn 29 SKYLON Users Manual Rev 1 1 Figure Bl SKYLON Upper Stage Only one reusable mission has been looked at in detail and this 1s
31. icle and a 3 2 km runway for aviation use The operators of SKYLON fleets have separate hangers and payload support facilities There is a general SK YLON maintenance building used by all operators Propellant Plant 4 ar e Oe Payload Integration Facility Maintenance Facili o Propellant cme kai Loading 7 I e Apron entres 442 Secondary Runway Figure 20 Spaceport Layout 4 2 Payload Integration It is anticipated that payload launch preparation would occur in special areas as part of the hanger and that overhead cranes would carry the payload from its mechanical support eguipment rig in the preparation area to the SKYLON vehicle to be lowered into the payload bay A concept design for this facility is given in Figure 21 and an artist impression of the interior in Figure 22 The air quality in the payload integration and loading areas is to ISO 9 as defined in ISO 14644 1 Clean rooms and associated controlled environments Part 1 Classification of air cleanliness While most payload preparation operations would be conducted in this facility any propellant loading required by the payload would be done in a separate fill area The fuelled spacecraft would then be returned and ready for integration 19 SKYLON Users Manual Rev 1 1 The payload is lifted from its integration fixtures and lowered into the payload bay by a loading rack and overhead crane The crane attaches to the paylo
32. igh performance rocket engine In air breathing mode the liguid oxygen flow is replaced by atmospheric air The airflow is drawn into the engine via an axisymmetric intake and is cooled to cryogenic temperatures by a pre cooler heat exchanger The pre cooler heat exchanger is part of a closed cycle helium loop using the hydrogen fuel as the heat sink before 1t enters the combustion chamber After cooling the air is compressed and fed to the combustion chamber Throughout most of the flight regime the intake captures more air than required The excess air 1s passed down a spill duct which incorporates a burner to recover some of the drag losses 2 shock axisymmetric intake The main precooler heat exchanger HX1 Drive turbine Pre burner and HX3 Hydrogen pump He Circulator Regenerators HX4 Heat Shield Moveable Centrebody Air Turbo Compressor Spill duct Lox Pump Spill duct ramjet burners 4 bell nozzle thrust chambers ED alternative under consdieration Figure 3 The SABRE Engine SKYLON Users Manual Rev 1 1 2 3 Typical Mission Profile SKYLON mission activity will start with the loading of the payload in an integration facility It will then be towed out to a fuelling apron to be loaded with liguid hydrogen liguid oxygen and helium Once loaded and powered up SKYLON is towed to the head of the take off runway With the vehicle stationary the engines are ignited in air breathing mode bu
33. imensions of the primary payload allow 1t to be fitted into the rear interface However the SSPC could also be used in pairs as the primary payload to launch a constellation of 10 micro satellites into the same orbit for example Figure El SKYLON Small Payload Carrier SSPC E3 PAYLOAD INTERFACE E3 1 Mechanical Interfaces Each bay can carry a payload of up to 200 kg The envelope available to each payload 1s defined in Figure E2 Extension of the 500 mm diameter region beyond the 300 mm guoted is possible and the 1200 mm could be extended in the centre three positions The payload is attached to the SSPC by 12 M5 bolts equispaced in a 650 mm circle These join the payload to the bay floor made of aluminium alloy Figure E2 also shows the location of the 4 SKYLON Users Manual Rev 1 1 electrical connector and the height of the SSPC wall The attachment is fixed and therefore any separation and deployment mechanisms which are reguired are the responsibility of the payload M5 12 off Egui space Mounting Plane Electrical on 650 dia Connector circle l 1200 En 350 sa S t 800 500 sia s R y AE ES v Dia R A s sm _ Sa SSPC Rear Wall Dimensions in Millimetres 15 EF Figure E2 SSPC Payload Envelope E3 2 Electrical Interfaces Each bay has a 5 pin electrical connection which provides a nominal 28 watts of electrical power and two commands to the payload The pin allocation is define
34. n 1s thrown clear then there is a parachute to reduce the ground impact loads to survivable levels In the event of an in orbit failure whereby SKYLON is deemed unfit to attempt a re entry there is a two day survival life support capability giving time for a second SKYLON equipped with a SPLM to rendezvous and dock with the stranded SKYLON Passengers can then transfer to the second SKYLON for return to Earth 37 SKYLON Users Manual Rev 1 1 The SPLM main cabin Figure D2 is designed for operational flexibility with 6 bays which can be outfitted for a variety of seating or logistics payloads There are also 12 storage lockers under the aisle floor for further logistics Figure D2 SPLM Interior D2 2 Mission Outline The SPLM 1s loaded into the payload bay the same as other payloads It mounts in the forward payload location and connects to the SKYLON data bus and the hydrogen and oxygen feeds to fill the internal fuel cell tanks While 1t is possible to load even large racks after the SPLM has been installed in SKYLON this is time consuming and awkward so it is therefore expected that all logistics will have been loaded prior to integration Once installed any passengers would enter the SPLM The primary access is by the forward payload bay ground door and a corresponding pressurised door in the SPLM There is also a rear door in the SPLM as secondary access path which opens to the rear of the payload bay hence the rear payload ba
35. ogistics in addition to the main payload 35 SKYLON Users Manual Rev 1 1 C3 PAYLOAD INTERFACES The main payload does not connect to the SOFI The impact on the payload provision is to alter the mass and envelope available to the main payload The SOFI has an installed mass of around 750 kg which must be subtracted from the performance given in Section 3 1 1 to obtain the mass available to the main payload The SOFI centre of mass relative to the payload bay centre is X 4 56m Y 0 03 m Z 0 93 m It is the combined centre of mass of the SOFI and main payload which must meet the constraints outlined Section 3 3 3 If a CTB is carried in the pressurised container its centre of mass will be at X 25 25 m Yz 0 m Z 1 83 m The SOFI occupies the rear payload interface and fills the rear 3 metres of the bay The main cross section is unaltered for an RMS removed payload as defined in Section 3 3 1 However the length is reduced and the altered envelope 1s shown in Figure C2 There 1s a small protrusion over the SOFI U section intended to accommodate the main payloa s attachment e g a docking or berthing port without using the main cross section Payload attachment centreline i Figure C2 Payload Envelope with SOFI Installed 36 SKYLON Users Manual Rev 1 1 ANNEX D SKYLON PERSONNEL LOGISTICS MODULE SPLM D1 INTRODUCTION This annex defines the interfaces for the module called the SKYLON
36. outlined here are those expected to be available with SKYLON on entry into service It would not preclude the development of other competing systems performing similar functions SKYLON Users Manual Rev 1 1 2 SKYLON C2 VEHICLE DESCRIPTION 2 1 SKYLON Configuration C2 The SKYLON launch vehicle 1s a winged single stage to orbit space plane powered by the SABRE engine which can operate in either an air breathing or a pure rocket mode The vehicle takes off from an extended runway with the engines in air breathing mode It accelerates to Mach 5 14 and 28 5 km altitude before switching over to the pure rocket mode and climbing to a Low Earth Orbit Once the payload is deployed and operations in orbit are completed the vehicle returns to earth re enters the atmosphere and glides back to a runway landing SKYLON Figure 2 consists of a slender fuselage which contains propellant tankage and a payload bay Its delta wings attached midway along the fuselage carry the SABRE engines in axisymmetric nacelles on the wingtips Figure 2 also defines the direction of the vehicle axes Key features of the SKYLON C2 are given in Table 1 assuming a 15 tonne payload into a 300km circular equatorial orbit from an equatorial launch site Canard Hydrogen Payload Oxygen Hydrogen Foreplanes Tank Bay Tank Tank Auxiliary Propellant Tankage Z Oxygen Payload Sabre Y Tank Container Engine X Figure 2 SKYLON Cutaway View and Axes
37. raft Interface System Volts Watts VI SKYLON Users Manual Rev 1 1 SKYLON USERS MANUAL 1 INTRODUCTION 1 1 Scope This document outlines the performance and payload interfaces for the SKYLON launch system Figure 1 in 1ts C2 configuration This configuration differs from the CI configuration which has been reported in past published work C2 has been mostly created by a direct scaling of C1 with the mass scaled by 1 23 and linear dimensions scaled by 1 08 It 1s intended as a starting point for a major redesign exercise that will revise the SKYLON design to create configuration D1 One area in which the C2 1s not a direct scaling of C1 is the payload bay interfaces These have been revised in light of a series of market and future application studies and this User Manual reflects the results of this redesign Thus this document represents a starting point for user requirements for the DI design and does not necessarily represent the final user interfaces It follows that this document should not be used for the detailed design of hardware intended for production gt ii 4 y 4 m M gt e A he gt d J 4 paa oi pa Figure 1 SKYLON C2 in Flight e g Richard Varvill and Alan Bond The SKYLON Spaceplane Journal of the British Interplanetary Society Volume 57 pp 22 32 2004 SKYLON Users Manual Rev 1 1 1 2 Purpose The purposes of this Users Manual are threefold They are 1 to provid
38. rance require for Clearance required for deploved payloads deployed payloads 1 1 I 1 1 1 1 I 1 1 1 1 1 1 1 1 1 1 1 1 1 1 ps he 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 1 I 1 1 I 1 1 Z Rear payload 799 Peon ga glosa x attachment centreline attachment centreline i Direction Figure 13 Payload Envelope and Attachment Geometry 12 SKYLON Users Manual Rev 1 1 3 3 2 Attachment Interface The payload 1s mechanically attached to SKYLON by three trunnions 1n a plane one keel trunnion taking loads along the X and Y axes and two sill trunnions taking loads along the X and Z axes The position and dimensions of the trunnion hold down are shown in Figure 14 The trunnions fitted to the payloads which correspond to these hold downs are defined by Figure 15 Payload Envelope ee pr oe ee oe 2450 to centreline NN SOS IN Y AX M NN NS K i l Payload Envelope Dimensionsin millimetres for reference only 792 to f centreline Sill Attachment Keel Attachment Figure 14 Payload Attachment Location and Dimensions 50 150 80 Y Sill Trunnion 255 305 Dimensions in millimetres Keel Trunnion Material Titanium or Inconel 718 VO Figure 15 Payload Trunnions The sill attachment can be opened during the flight to release the sill trunnions and allow the payload to be extr
39. rform the final orbit insertion manoeuvres In this mission profile the vehicle flies an ascent trajectory which places it into an orbit that will allow a minimum of 5 minutes above an altitude of 135 km and achieve a flight path angle no steeper than minus 3 degrees at the re entry interface of 120 km The nominal transfer orbit to satisfy these constraints has been determined as follows Apogee 157 km radius of apogee 6532 km Perigee minus 2000 km radius of perigee 4375 km Velocity at apogee 6966 m s Deployment is started 30 minutes after MECO When the vehicle 1s above 135 km a minimum deployment altitude determined by aerothermal constraints the payload bay doors are opened and the payload 1s deploved SKYLON then proceeds to separate from the payload which is now independent and closes the payload bay doors After 2 3 minutes the payload fires its engine in order to raise 1t to its operational orbit SKYLON then re enters as with an orbital mission and lands at a site about 10 000 km downrange from its launch site The vehicle may then be towed back to its base The suborbital deployment seguence with design values for seguencing 1s given in Figure 11 EVENT Pitch Open payload Deploy Close bay Orientation Payload orbit manoeuvre bay payload avoidance and insertion burn manoeuvre separation a Determined KA zi Ali Figure 11 Suborbital Deployment Seguence and Timing The total payload mass that may be
40. rning hydrogen fuel with pre cooled compressed air When nominal performance has been verified the brakes are released and the vehicle begins its take off roll The vehicle takes off from the runway in the same manner as a high performance jet aircraft with a take off speed close to Mach 0 5 Following take off the vehicle jettisons around 3 tonnes of water which would have been required by the boiling water braking system for a rejected take off should a malfunction have occurred After take off the vehicle climbs and accelerates on its predetermined trajectory for 694 seconds approx 11 minutes by which time it has reached an altitude of 28 5 km and a speed of Mach 5 14 The vehicle is now 620 km downrange from the launch site SKYLON now switches to pure rocket propulsion burning liquid hydrogen and liquid oxygen in the common combustion chambers The vehicle now climbs rapidly and performs a gravity turn in order to inject into an 80 by 300 km transfer orbit after a further 285 seconds 4 4 minutes at which time main engine cut off occurs Figure 4 shows a nominal ascent profile 90 MECO 80 70 60 50 40 Altitude km 30 Airbreathing Rocket Transition 20 10 O 400 600 800 1000 Flight Time seconds O ho O O Figure 4 Ascent Trajectory SKYLON then jettisons main tank residual propellant and continues on a ballistic trajectory for a further 44 minutes until it reaches apogee at 300 km altitude at whic
41. s door i Starboard side Figure 23 Payload Bay Access Doors 4 3 Launch and Landing Sequence Figure 24 details the sequence of events from payload integration to take off which nominally takes a little under 4 hours and if needed from landing to payload removal which takes a little over 2 hours These times do not include the time required for the SKYLON turnaround which will depend upon how it is operated but is expected to be typically in the order of a day After SKYLON is fuelled there is a 240 minute window before the flight attempt must be abandoned and the vehicle de fuelled This is the time taken for the propellant in the tanks to reach boiling point This hold capability allows enough time for a second opportunity to fly to any given orbit plane should the first opportunity be missed for any reason 21 SKYLON Users Manual Rev 1 1 ACTIVITY TIME mins 7 Preflight preparation 000 Payload installation 045 Close doors 050 Flight ready 060 Hanger flight checks 070 low to takeoff apron 095 Install on takeoff apron 105 Nitrogen burge 115 g Tank chill down 125 Propellant loading 159 Phasing Hold 1 0 Final flight check 171 Take off 1 2 Landing 000 Runway safe ing 010 low to hanger 040 Install in hanger 0 0 Hanger safe ing 080 Open doors 085 I Remove payload 130 Ma Post flight servicing Figure 24 Launch and Landing Sequence and Timeline SKYLON Users Manual Rev 1 1
42. sign outlined in this annex is conceptual in order to illustrate the connection requirements of SKYLON s complimentary systems In practice whatever ends up as the international standard will have to be used this 1s at least the case for the SPLM However compromises over the functionality incorporated in the USIS will impact on what the complimentary systems can do A2 USIS DESCRIPTION A2 1 Operation Types USIS has four types of connection function which are defined in Table Al These have upward compatibility where for example an integrated level interface can be integrated to a docking or berthing level interface or a docking system can be berthed to a berthing level interface This 25 SKYLON Users Manual Rev 1 1 backward compatibility has proved an important factor in maintaining the operational flexibility of the various support systems which use the USIS Integrated permanent Or breakable Berthing manipulator Below 01 m s Hard Docking free flying spacecraft 10 degrees in all axis As hard docking with active 150 mm and Soft Docking control to reduce impact loads Below 01 m sec 10 degrees in all axis Table Al USIS Functional Levels The USIS has both pressurised and unpressurised variants Only one side of USIS needs to be active for berthing or docking operations as the USIS can be implemented as a passive only connection When the four function levels are combined with pressurisation options and t
43. t can be drawn simultaneously is 20 A for reference this corresponds to a nominal power of 560 watts The constraint on the total energy available to the payload over the mission remains as for a single payload The connector also provides the payload with a 5 line parallel command status alert bus Each signal has an output voltage of 28 V 4 V of 2 seconds duration This provides a 4 bit signal with even parity checking Four of the commands are reserved these are 1000 1 Abort Alert the SKYLON has initiated an abort manoeuvre 0100 1 Door Opening Alert the payload bay door will open in 30 seconds 0010 1 Door Closing Alert the payload bay door will close in 30 seconds 0001 1 Deployment Alert the payload will be deploved in 30 seconds The actions of other commands are defined by the payload The payload is required to provide a resistive load greater than 100 ohms which is immune to single point failure The payload 1s also required to fully protect the circuit against any overload or voltage overshoot induced by its circuits 16 SKYLON Users Manual Rev 1 1 Parity Bit Power Return x Ki A 4 N i Z a A S HA BIE hu AAA gt h 28V Power A ka M s E i it N Forward Pavload Interface Rear Interface mirrors Ground Figure 18 Keel Trunnion Pin Connections 3 5 2 Data Bus Connection There is provision for the pavload to connect to the SKXLON data bus at both the front and r
44. trical power and data connections The locations of these functions are shown in Figure A3 Separation spring Bolt hole Bolt hole Striker plate Clamp mechanism Berthing alignment guide Berthing alignment vane Clamp mechanism Striker plate Bolt hole Bolt hole 2 Oring seals Separation spring Separation spring Bolt hole 28V Power in Bolt hole 28 V Power Out OV Return OV Return OV Ground OY Ground Y Data in Data Out Clamp mechanism Berthing alignment vane Berthing alignment guide Clamp mechanism oe Striker plate Bolt hole Bolt hole Separation spring Figure A3 The Location of USIS Ring Functions A2 3 Active Clamps All variants of the USIS which require in orbit active connections i e not using the bolt option make the final connection with four equi spaced clamp mechanisms Four clamps are sufficient but if both sides are active USIS variants both sets can be activated If the full corridor defined in section A2 5 is required both sets of clamps need to be closed as they intrude into the areas when open In berthing operations these clamps act as the capture latches In docking operations they are activated to make the final structural connection after capture has been achieved by the pin cone connection A2 4 Pin Cone Docking Connection A pin and cone mechanism is fitted when a docking function is required involving additional alignment and capture mechanism The pin
45. y ground access door Once all passengers are on board the SKYLON would be then towed to the refuelling apron to begin the flight Missions can be up to 2 days with a further 2 days capability for contingency Missions to orbiting facilities are possible with a full active USIS docking port in the roof which can also be used for berthing if appropriate This port is orientated with 15 degrees rotation to the SKYLON axes so that two SPLM equipped SKYLON s can dock with each other for in orbit rescue of passencers Return and landing follows the standard SKYLON re entry D3 PAYLOAD PROVISIONS D3 1 Mass Capability The SPLM has an unladen mass of 7800 kg which includes the Captain hydrogen and oxygen for the fuel cells and some of the life support consumables The difference between this mass and the mass capability defined in section 3 1 is what 1s available for passengers and logistics 38 SKYLON Users Manual Rev 1 1 D3 2 Under Floor CTB Provisions The main logistics provision 1s designed to house ISS standard Cargo Transfer Bags CTB and takes the form of 12 lockers under the aisle floor Each houses a triple CTB or a combination of double single and half CTBS up to a mass of 80kg in each locker D3 3 Cabin Bays The cabin has 6 bays which are configured to house a variety of payload types The bay s dimensions are shown in Figure D3 DIMENSIONS IN MILLIMETERS 1655 E RACK FORWARD ATTACHMENT
46. y the complimentary Infrastructure elements to SKYLON This acts as a universal physical interface between all medium and large space systems whether manned or unmanned This docking standard will become the standard in orbit connection system even if it is not planned as such None of the existing three docking and berthing systems used on the International Space Station look like becoming international standards As things stand Russia seems to plan on continuing the use of the Soyuz pin cone system while the USA and Europe seem agreed on a new system variously known as Low Impact Docking System Advanced Docking System and International Docking Berthing Standard This may be an emerging international standard with reference to USA and Europe at the moment for a docking port but while the detailed interfaces of this new system have not been published what 1s known of it suggests that 1t has serious limitations which conseguently makes 1t unsuitable as a long term standard Of the many deficiencies in functionality the most important are the hatch size which at 800 mm is too small for many of the items such as eguipment racks which need to pass through and the lack of extendibility to integrated connections Therefore a new interface has been designed for SKYLON applications called the Universal Space Interface System USIS It is shown in its fullest form in Figure Al Figure Al The Universal Space Interface System USIS The USIS de
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