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Space engineering Explosive systems and devices

1. 31 July 2008 Table 4 25 Qualification tests Qualification test ECSS E ST 10 03 ECSS E ST 10 03 Spacecraft Launcher see Note 3 reference sequence component component no fire stimulus NO additional R R physical properties measurement YES 1 R R secondary characteristics measurement NO additional R R functional and performance measurement YES See Note 1 N A N A no damage drop NO additional O R Salt fog NO additional N A R rain NO additional N A R humidity YES 2 O R leakage test YES 3 5 10 13 O O generated shock NO None O O pressure YES 4 N A N A acceleration YES 6 O R sinusoidal vibration YES 7 R R random vibration YES 8 R R acoustic YES 8 N A R shock YES 9 R R corona and arcing YES 11 N A N A thermal vacuum YES 12 O O thermal cycling YES 12 R R EMC ESD for initiator only YES 14 R R life YES 15 O microgravity YES 16 N A N A audible noise YES 17 N A N A radiation NO additional O N A functional and performance measurement YES See Note 2 destructive physical analysis NO additional R Required O Optional N A Not Applicable Note 1 Only possible at the end of the qualification sequence Note 2 See 4 14 4 1e Note 3 See Table for Qualification test in ECSS E ST 10 03 63 ECSS E ST 33 11C E 31 July 2008 4 14 4 3 Acceptance tests a Lot acceptance tests shall be performed b Acceptance test
2. a The properties of the packaged charge shall conform to the requirements of Table 4 8 with the exception of the structural integrity requirements and Table 4 7 and be quantified b Under the conditions in column E of Table 4 8 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 8 Requirements for packaged charge properties A B C D E F Property Unit Maximum Minimum Condition Notes value value Structural N A N A handling and transport integrity loads Detonation TBPM N A Intended operational Yes No mode Deflagration TBPM N A Intended operational Yes No mode 4 11 3 Integral initiator connectors 4 11 3 1 General a The configuration of the connector shall be used only for initiators NOTE This is the integral upper part of the initiator 44 EGS ECSS E ST 33 11C 31 July 2008 The interface shall allow for sealing 4 11 3 2 Electrical initiator connector The connector thread or closing mechanism shall be self locking The connection shall have electrical continuity with a resistance lt 10 mQ The connector shall be able to undergo 50 mating demating cycles without degradation The connection shall be able to undergo specified shocks without degradation 4 11 3 3 Laser initiator connector a The initiator shall incorporate an interface to match t
3. safe during any phase of this cyclic life e The barrier shall be removable or a reconnection shall allow propagation Armed condition when commanded f Remote operation and status indication shall be provided g Local visible unambiguous status indication shall be provided All additional blocks shall be flagged Remove before flight NOTE Safe and arm devices can use initiator simulator resistors 4 10 11 2 Electrically actuated a The electrically actuated safe and arm device shall not have current flow exceeding 2 mA in the disarm or safe command circuit during the arming cycle nor in the arm command circuit during disarm or safing b The electrically actuated safe and arm device shall have a demonstrated cyclic life of 1000 safe to arm to safe transitions or five times the number of transitions predicted during its lifetime whichever is greater without failure or degraded performance 4 10 11 3 Mechanically actuated a The mechanically actuated safe and arm device shall have a demonstrated cyclic life of 300 safe to arm to safe transitions without failure or degraded performance 4 10 11 4 Safing a Safing shall prevent detonation or initiation transfer by 1 the placement of a barrier between the initiator and next explosive element or 2 misalignment of the initiator and the next explosive element b Safing shall disconnect power and return firing lines C Safing shall short the EEDs d
4. 3 2 31 sequential firing application of the firing pulses to initiators separated in time 3 2 32 success simultaneous achievement by all characteristics of required performance 3 2 33 sympathetic firing firing of other explosive devices due to the output of any other 3 2 34 transfer line linear explosive assembly for propagation of deflagration or detonation 3 2 35 through bulkhead initiator TBI initiator for transfer of detonating input to detonating or deflagrating output 3 3 Abbreviated terms For the purpose of this Standard the abbreviated terms from ECSS S ST 00 01 and the following apply Abbreviation Meaning DC direct current DMPL declared materials and processes list DSC differential scanning calorimetry DTA differential thermal analysis EED electro explosive device EMC electromagnetic compatibility EMI electromagnetic interference ESD electrostatic discharge FOSU ultimate design factor of safety FOSY yield design factor of safety GSE ground support equipment MEOP maximum expected operating pressure N A not applicable NC normally closed NO normally open RF radio frequency 14 EGS ECSS E ST 33 11C 31 July 2008 SRS TBI TBPM TBPC TGA VTS 3 4 Symbols lt gt a E Soe 6 shock response spectrum through bulkhead initiator to be provided by manufacturer to be provided by customer thermo gravimetry analysis vacuum thermal stability at standard surface gravity 9 80665 m s d
5. EGS ECSS E ST 33 11C 31 July 2008 4 11 6 Gas generators a and conform to the figures where shown The properties of gas generators given in Table 4 16 shall be quantified Under the conditions in column E of Table 4 16 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 16 Common requirements for gas generator operation A B C D E F Property Unit Maximum Minimum Condition Notes value value Bonding resistance mQ 10 N A To next level assembly Leak rate scc He s 10 N A Ap 0 1 MPa before and after firing at initiator interface Structural integrity MPa TBPM in conformance with ECCS E 32 10 applies on MEOP Temperatures a Auto ignition C N A TBPM b Non operating C TBPM TBPM c Operating C TBPM TBPM Duration TBPM d Storage C TBPM TBPM Duration TBPM e Transport C TBPM TBPM Duration TBPM Generated a Pressure MPa TBPM TBPM Only the known and relevant output parameter shall be provided b Heat J TBPM TBPM Only the known and relevant output parameter shall be provided c Nr of mating de TBPM TBPC With without change of mating cycles seals d Generated Shock g ms TBPM N A Time history and TBPC sampling rate Test configuration TBPC Life time Year TBPM N A For transport stor
6. including but not limited to direct indirect special or consequential damages arising out of resulting from or in any way connected to the use of this Standard whether or not based upon warranty business agreement tort or otherwise whether or not injury was sustained by persons or property or otherwise and whether or not loss was sustained from or arose out of the results of the item or any services that may be provided by ECSS Published by ESA Requirements and Standards Division ESTEC P O Box 299 2200 AG Noordwijk The Netherlands Copyright 2008 by the European Space Agency for the members of ECSS EGS ECSS E ST 33 11C 31 July 2008 Change log ECSS E 30 Part 6A First issue 25 April 2000 ECSS E 33 11A Second issue 17 April 2008 Changes to the previous version are e the use of the more accurate term explosive rather than pyrotechnics in relation to the subject components and systems e the emphasis on reliability coupled with confidence level for performance properties e the inclusion of detailed requirements for the different types of explosive device e and the emphasis on the requirement for properties of components to be agreed with the end user before commitment to purchase ECSS E 33 11B Never issued ECSS E ST 33 11C 31 July 2008 Third issue Editorial changes ECSS E ST 33 11C E 31 July 2008 Table of contents E 9 CN ern EEN 10
7. mating cycles Life time Year N A TBPC For transport storage and operation 4 11 4 2 Transfer line assembly a The properties of transfer line assembly given in Table 4 10 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 10 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum 46 EGS ECSS E ST 33 11C 31 July 2008 Table 4 10 Requirements for transfer line assembly properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Propagation m s TBPM TBPM velocity 2 Deflagrating lines a Pressure MPa TBPM TBPM b Heat J TBPM TBPM 3 Detonating lines a Shock GPa TBPM TBPM Standard material transmission capability b Flyer mm TBPM TBPM Flyer thickness characteristics diameter material and jitter c Flyer velocity m s TBPM TBPM Best estimate d Ignition gap mm TBPM TBPM By initiator type TBPM 4 End to end mm TBPM TBPM transmission gap 5 Electrical mQ TBPM N A From end to end continuity 6 Leak rate scc He s 10 N A Ap 0 1 MPa before together with firing interfaces 7 Leak tightness scc He s 10 N A Ap 0 1 MPa after together with firing ends interfaces implemented in the specified interface No debris 8 Organic mg m 2 N A See ECSS Q
8. 3 Terms definitions and abbreviated terms ccsseecessssssssssesseeeeeeeeeeeeeeeeeees 11 3 1 Terms defined in other standarcde ene 11 3 2 Terms specific to the present standard ccccccceeeeeeeeeeeeseeceeeeeeeeeeeeeeeneeeeeeeeeenens 11 3 3 Abbreviated terms nei a a aa ar a 14 34 HEEN aeta REEE SE EAE EE EAEE 15 RT E nn nnnnnnnnnn nnn mnnnnnnnnnn nnmnnn nnnm 16 GW DE E 16 Aah e E 16 e ea elen E 17 e D E g EE 17 Ace AAQVIGEAL EE 17 4 2 2 Reliability and confidence c cscccectiiechattin teeta 17 4 2 3 Pertomance see eecccec cece cceccceeececeeceeeeeeeeecceeeeeeeceeeeeesesneeeeeceeesseeeseesseeeenas 18 4 2 4 Wanted and unwanted response ccccccccecesseeeeeeeeeeeeeseeeseeeeeeeeeeeeenees 18 A275 DIMENSIONING DE 18 AD MISSION EE 21 AeA FUNCUONAINY eueseac sates sete cea eee nana seca eae meeerered es emcee as 21 E E 22 451 SAT EE 22 4 5 2 Prevention of unintentional function ccccccccccecceeeceeeeeeeeeeeeeeeeeeeeeeeeteeess 22 4 6 Survival and operational condtons 24 4 7 Interface requirements E 24 Mitel e E 24 GE e erte Io EE 24 C Ga Tai C1 0 eee 25 ATA E A EE 25 4 8 Mechanical electrical and thermal requirements nnnnnneeeeeeeeeeeen nener eene enn ernennen 25 ECSS E ST 33 11C E 31 July 2008 4 9 4 10 4 12 4 13 4 8 1 Oe ET le EE 25 4 8 2 Electrical eee c cece cece cccecceecceecceeeceeeeeeeceeeeeeeeeeeeceeceeeceeeeceeeeeeseeeesenesene
9. 57 DC WI 57 Items external to the flight equipment cece ceeeeee cece ee eeeeeeneeeeeeeeeeseeeneeneneeeeees 58 nk e GSE erro e a r anaes tautedest accents causaacenaecceaneseae 58 413 2 E UI nt cscccstceinti teenie il aro Gis ee 58 4 13 3 Launch site 22 ce ccc ceecceecceeeceececeeeceeeeeeeeececeeeeeeeseeseeeseeeeessesenesseeseenenaaes 59 ECSS E ST 33 11C E 31 July 2008 4 14 STIG AO ee 59 4 14 1 CGS EE 59 Ee EE 59 e Nr We EE 60 4 14 4 Qualification and lot acceptance eee eee eeeeeeeeeeetee eee eeeaeeeteeeeeeeeeeee 62 4 15 Transport facilities handling ANd storage A 64 415 1 EE eege 64 AN Mrans OI cin sete e aeea sain a ae oes 65 AMO let 65 E Aand ME 66 416 Oe eege 66 4 16 1 E Me ue 66 4 16 2 Launch site procedures xc sccissccceicvcniadesnedssotdenereteaeaeetedtereianipena tenia omens 67 4 16 3 rel e EE 67 d De ge iad 680 5s EE 67 GK We E 67 417 2 tee ee ee eee 67 BAZ E E 67 Annex A informative Component qualification test levels s sseeeeeees 68 Annex B informative List of deliverable documents cccceeeeeeeeeeeeeeeeeeeeeeeees 71 Figures Figure 4 1 Margin and reliability relatonsbm AA 21 Tables Table 4 1 Values for explosive factor 2 2 cccccceeeeeeeeeeeceeeeeeeeeeseeeeeeeeeeeeeeseeseeeeeeeneeeeeseeeseees 20 Table 4 2 Explosive component colour code vccsctscicccntststionneceeiecs aint ENN EeNeCEed ee egeN 26 Table 4 3 Common requirements for initiator cartridge d
10. NOTE Specified stimulus e g nature range of values C The explosive system shall ensure that the correct stimulus arrives at the specified place at the specified time d The explosive system shall prevent the stimulus reaching the initiator at any other time e Unwanted function or malfunction shall be prevented f The firing sequence simultaneous or sequential shall cause no anomaly 21 EGS ECSS E ST 33 11C 31 July 2008 4 5 Safety NOTE This applies to secondary characteristics as well as for explosive functions Explosive systems shall be single fault tolerant Explosive systems shall be two fault tolerant if premature initiation causes a catastrophic failure If loss of function is safety critical or catastrophic the explosive system shall avoid single point failures and include at least two initiators Provision shall be made within the explosive system to protect its components against unwanted operation or degradation 4 5 1 General The system including software and procedures shall be fail safe For a catastrophic risk the explosive system shall be Fail Safe Fail Safe or Fail Operational Fail Safe The response of any explosive device to conditions outside the conditions specified shall be reported by the manufacturer to the end user The explosive subsystem shall only respond to commands intended for that explosive subsystem 4 5 2 Prevention of unintentional func
11. Safing should ground the shorted EEDs through a resistance agreed with the end user e Safing shall have resistor s with a resistance exceeding 10 kQ if these resistor s remain connected to the firing circuit in the arm position NOTE Clause 4 1 2a applies 4 10 11 5 Arming a Arming shall enable detonation or initiation transfer by 37 EGS ECSS E ST 33 11C 31 July 2008 1 the removal of a barrier between the initiator and next explosive element or 2 alignment of the initiator and the next explosive element b Arming shall 1 connect firing power lines and return lines to EEDs 2 remove the short from the EEDs 3 disconnect the EEDs from the ground c During transition from safe to arm each electrical switch shall disconnect before connecting to the next circuit NOTE Clause 4 1 2 applies 4 10 11 6 Status indicators a The device shall 1 provide remote status indications 2 provide local status indications 3 indicate Arm status with a black A on a red background or a red A 4 indicate a Safe status with a white S on a green background or a green S b The status indications shall be unambiguous c Visibility of the status indicators when installed on the spacecraft or launcher shall be ensured 4 10 11 7 Initiator Simulator resistors a Application of operational voltages for at least 20 seconds shall not degrade the Safe and Arm performance or cause in
12. and D of the component the reliability demonstration shall be used to justify design margins including the influence of ageing temperature and explosive batch NOTE 1 See Figure 4 1 NOTE 2_ R is the estimated reliability R and R are the limits according to the confidence level required 20 ECSS E ST 33 11C E 31 July 2008 Probability distribution Required Performance Statistical distribution of the performance Phase C D Performance 7 R reliability 7 Figure 4 1 Margin and reliability relationship 4 2 5 4 Motorization a ECSS E ST 33 01 Clause Functional dimensioning motorization shall apply to explosively actuated devices 4 3 Mission a The use of explosive functions including those for flight termination and range safety during all phases of the mission shall be specified b The environmental conditions life cycle and the functions being activated shall be specified NOTE E g ground storage transport launcher ignition staging and safety functions payload separation motor ignition solar array antenna boom or cover release propulsion system branch opening or closing de orbiting c Mission related requirements placed on the explosive system shall be specified 4 4 Functionality a The timing of each function of the explosive system shall be specified b The explosive system shall react only to a specified stimulus and be insensitive to all others
13. sometimes prohibits use of these features All materials including explosive substances shall be compatible with those materials with which they can come into contact NOTE1 Outgassing can occur during e g polymerization degradation of polymers NOTE 2 Selection of materials and processes are done in conformance with ECSS E ST 32 08 ECSS ST Q 70 and ECSS ST Q 70 71 NOTE3 Explosive systems use materials e g explosives propellants powder binders cleaning agents cements that can be toxic 31 EGS ECSS E ST 33 11C 31 July 2008 corrosive highly reactive flammable and dangerous with direct contact Continued exposure to the expected environmental conditions shall not cause degradation or increased sensitivity in excess of agreed limits Any sealing system used to prevent degradation shall be demonstrated to be effective No cracking shall be allowed due to shock loads NOTE Materials can become brittle at low temperatures Age sensitive materials shall only be used where degradation causes no loss of explosive system performance beyond limits agreed with the end user The nature and condition of age sensitive materials shall be identified and documented in the DMPL The nature and condition of explosive materials shall be identified and documented in the DMPL Explosives that can react in response to normal environmental stimuli shall only be used in agreement with the end user The properties
14. suitable for the number of connection cycles necessary to cover integration test and use be suitable for use with flight hardware be scoop proof be lockable NOTE E g sub D connector bayonet or triple start thread type Safe and arm device 4 10 11 1 General Electrically actuated safe and arm devices should be used a b A safe and arm device shall 1 Sp oy GT es e a 10 11 12 be used in applications where unplanned initiation of the explosive system can cause injury death or severe damage to property prevent the mounting of initiators in armed position provide means of remote arming provide means of remote safing provide safing without passing through the armed position prevent manual arming provide manual safing and prevent unwanted return to arm remain in the selected position under all conditions except when intentionally activated prevent remaining in any state between safe and arm arm within a time interval agreed with the end user not require a force or torque to safe exceeding a value agreed with the customer if actuated remotely safe within a time interval agreed with the end user 36 EGS ECSS E ST 33 11C 31 July 2008 c It shall not be possible to arm the safe and arm device in case an initiator has been activated with the safe and arm device in safe position d The safe and arm device shall be capable of being manually positioned to
15. to each interface NOTE This is to prevent activation or damage by external loads and environmental conditions When closed each interface shall establish stable continuity of properties between the joined elements 24 ECSS E ST 33 11C E 31 July 2008 NOTE This is to prevent disturbance of or being disturbed by external loads and environmental conditions d Each interface shall sustain without degradation in both coupled and separated states 1 the assembly and dismantling duty cycle and 2 the operational and environmental conditions of the application 4 7 3 Internal a Each element in the explosive system shall be compatible with its neighbour b Each element shall provide outputs at each interface with margins over the input requirements of the next element or the explosive system output requirements NOTE E g electrical mechanical thermal and optical outputs 4 7 4 External a The explosive system shall be compatible with the requirements of all other subsystems on board external loading and environmental conditions b In case 4 7 4a is not met it shall either be agreed with the end user to change the on board system requirements or be agreed with the end user to provide protection against the environmental conditions or to reduce the external loads on the explosive system 4 8 Mechanical electrical and thermal requirements 4 8 1 Mechanical 4 8 1 1 Inertial properties
16. 1 4 7 Explosive delays a The properties of explosive delays given in Table 4 15 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 15 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 15 Requirements for explosive delay properties A B C D E F Property Unit Maximum Minimum Condition Notes value value Delay type TBPM TBPM With or without gas generation Delay time ms TBPM TBPM Mean value standard deviation at temperatures Temperature C TBPM TBPM Temperature range to be sensitivity provided Initiation TBPM TBPM To be provided mechanical e g percussion electrical thermal detonation Output TBPM TBPM To be provided pressure versus time calorific energy detonation Leak rate scc He s 10 6 TBPM Ap 0 1 MPa before firing Leak rate scc He s TBPM N A Ap 0 1 MPa after firing Temperatures a Auto ignition C TBPM TBPM b Non operating C TBPM TBPM c Operating C TBPM TBPM d Storage C TBPM TBPM e Transport SC TBPM TBPM Life time Year TBPM N A During transport storage and mission 4 11 5 Safe and arm devices containing explosive a Clause 4 10 11 shall apply b Only secondary explosive with less or equal sensitivity to Hexogen shall be used 52
17. 31 July 2008 4 12 2 Separation nuts and separation bolts a The properties of the separation nut and bolt given in Table 4 18 shall be quantified and conform to the figures where shown b Re settable separation nuts shall include a means of verifying that the nut is properly reset before and after its mating bolt or stud installation and torquing c The pre load shall be specified d The pre load shall exceed the maximum expected amplitude of the dynamic tension in the bolt and effects of thermal variations e Under the conditions in column E of Table 4 18 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 18 Requirements for separation nut and separation bolt properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Screw pre load Screw properties to be tension provided a By Pure tension kN TBPM TBPM b By torque kN TBPM TBPM 2 Load capabilities Worst case temperatures a Axial load kN TBPM TBPM b Transverse load kN TBPM TBPM c Bending moment Nm TBPM TBPM d Torsion Nm TBPM TBPM 3 Stiffness Worst case temperatures a Axial N m TBPM TBPM b Transverse N m TBPM TBPM c Bending moment Nm rad_ TBPM TBPM d Torsion Nm rad TBPM 55 EGS ECSS E ST 33 11C 31 July 2008
18. 4 12 3 Pullers a The properties of the puller given in Table 4 19 shall be quantified and conform to the figures where shown The puller shall be capable to withdraw the pin under maximum shear and bending loads The retractable pin shall not rebound Under the conditions in column E of Table 4 19 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 19 Requirements for puller properties A C D E F Property Unit Maximum Minimum Condition Notes value value 1 Pin Preloads N A a Axial TBPM N A b Shear TBPM N A c Bending moment Nm TBPM N A 2 Traction force TBPM TBPM Minimum at end of stroke 3 Pulling stroke mm TBPM TBPM 4 12 4 Pusher a The properties of the pusher given in Table 4 20 shall be quantified and conform to the figures where shown b Pushers shall be able to withstand the expected loads during operation NOTE These loads comprise e g compression and shear and bending moment Under the conditions in column E of Table 4 20 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 20 Requirements for pusher properties A C D E F Property Unit Maximum Minimum Condition Notes value value 1 Rod axial load kN TBPM N A 2 Push force N TBPM TBP
19. 9 EGS ECSS E ST 33 11C 31 July 2008 Table 4 13 Requirements for expanding tube device properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Cutting capabilities a Structure TBPM TBPM TBPM Associated with material thicknesses properties e g ductility position of the elongation strain rate cutting area b Cut Structure kN TBPC TBPC Associated with material loads during properties e g ductility cutting elongation strain rate plasticity c Type of impulse Ns TBPM TBPC Radial or axial 2 Explosives g TBPM TBPM Associated with tube Quantity and type materials properties 3 Redundancy TBPM 4 Expanding tube m TBPM N A Number and size of unsupported windows for the length expanding tube assembly 5 Cutting conditions a Response time ms TBPM TBPM Between first input and completion of cutting b Generated Shock g ms TBPM N A Time history and TBPC sampling rate Test configuration TBPC 6 Device leak rate scc He s 10 N A Ap 0 1 MPa before firing 7 Device leak rate scc He s 10 N A Ap 0 1 MPa after firing 8 Particle TBPC N A Test method TBPC generation 9 Temperatures a Auto ignition C N A TBPM b Non operating C TBPM TBPM c Operational C TBPM TBPM d Storage C TBPM TBPM e Transport C TBPM TBPM 10 Life time Ye
20. ECSS E ST 33 11C 31 July 2008 EUROPEAN COOPERATION FOR SPACE STANDARDIZATION Space engineering Explosive systems and devices ECSS Secretariat ESA ESTEC Requirements amp Standards Division Noordwijk The Netherlands ECSS E ST 33 11C E 31 July 2008 Foreword This Standard is one of the series of ECSS Standards intended to be applied together for the management engineering and product assurance in space projects and applications ECSS is a cooperative effort of the European Space Agency national space agencies and European industry associations for the purpose of developing and maintaining common standards Requirements in this Standard are defined in terms of what shall be accomplished rather than in terms of how to organize and perform the necessary work This allows existing organizational structures and methods to be applied where they are effective and for the structures and methods to evolve as necessary without rewriting the standards This Standard has been prepared by the ECSS E ST 33 11 Working Group reviewed by the ECSS Executive Secretariat and approved by the ECSS Technical Authority Disclaimer ECSS does not provide any warranty whatsoever whether expressed implied or statutory including but not limited to any warranty of merchantability or fitness for a particular purpose or any warranty that the contents of the item are error free In no respect shall ECSS incur any liability for any damages
21. M Minimum at end of stroke 3 Pushing stroke mm TBPM TBPM 56 EGS ECSS E ST 33 11C 31 July 2008 4 12 5 Cutters a The properties of the cutter given in Table 4 21 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 21 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 21 Requirements for cutter properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Cutting capabilities At worst case temperatures a dimensions mm _ TBPM N A associated with material properties b ultimate strength MPa TBPM TBPM c tension load kN N A TBPM 2 Mass of generated mg TBPM N A Total mass associated particles with load and load carrier properties 3 Dimensions of mm _ TBPM TBPM Range of size associated generated particles with load and load carrier properties 4 12 6 Valves a The properties of the valve given in Table 4 22 shall be quantified and conform to the figures where shown b After firing the valve piston shall remain in its actuated position c The type of valve NO or NC shall be marked on the device d The flow direction shall be marked on the device e Under the conditions in column E of Table 4 22 the properties in column A expre
22. Results of the checks specified in 4 16 2a shall be recorded Information shall be provided of hardware and software provisions for the monitoring and command of explosive functions and show changes from one stage to the next RF links wiring connectors and pin functions shall be specified to check the source and destination Diagrams or photographs of consoles and installations shall be provided Confirmation shall be provided that no unwanted responses or drifts have occurred 66 EGS ECSS E ST 33 11C 31 July 2008 4 16 2 Launch site procedures a Only planned and approved activities which follow approved procedures shall be undertaken The activities specified in 4 16 2a shall include contingency actions Rehearsals shall be performed 4 16 3 Monitoring a Confirmation of operation shall be made available immediately 4 17 Product assurance 4 17 1 General a The explosive functions on a vehicle shall be treated together as a single subsystem All explosive devices shall be treated as critical items 4 17 2 Dependability a The explosive system shall be in conformance with all dependability requirements ECSS Q ST 30 Clauses 6 7 8 and 9 Age sensitive parts and materials shall be identified 4 17 3 Safety a The properties of the subsystem and all activities shall meet the safety requirements defined in ECSS Q ST 40 Immediately before every electrical or optical connection
23. ST 70 01 contamination of surfaces 9 Radius of m N A TBPM Bending curvature 10 Nr Of times one TBPM TBPC Bending can bend 11 Twist angle rad m TBPM N A 12 Tension daN TBPM N A 13 Overall mass g m TBPM N A Linear mass of flexible part g m ends g 14 Explosive mass g m TBPM N A Linear mass of flexible part g m ends g 47 ECSS E ST 33 11C E 31 July 2008 4 11 4 3 Through bulkhead transfer devices a The properties of through bulkhead transfer devices given in Table 4 11 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 11 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 11 Requirements for through bulkhead transfer device properties A B C D E F g Property Unit Maximum Minimum Condition Notes value value Output a Pressure MPa TBPM TBPM In TBPM cm3 at 20 C b Energy J TBPM TBPM TBPM c Leak rate scc He s 10 6 N A Ap 0 1 MPa before firing Barrier tightness scc He s 10 5 N A Ap 0 1 MPa before leak rate firing Barrier tightness scc He s_ 10 3 N A Ap 0 1 MPa after leak rate firing Structural MPa TBPM TBPM barrier resistance integrity after firing 4 11 4 4 Shaped charges a The properties of shaped charges given in Table 4 12 shall be
24. a The supplier shall provide before and after firing the customer with the following information of the component 1 the mass 2 the centre of mass 3 the inertial properties and 4 the numerical model upon request of the end user 25 EGS ECSS E ST 33 11C 31 July 2008 4 8 1 2 Main fixings a Each element of the explosive system shall be provided with an interface compatible with the methods of attachment to the structure or appendage agreed with the customer 4 8 1 3 Modularity of the system The explosive system shall be assembled from modular components The capability shall be provided to test the components separately It shall be ensured that attachment installation repair and replacement can be done without affecting the surrounding equipment 4 8 1 4 Avoidance of confusion a It shall be ensured that components intended for different applications cannot be confused Inert components dummies and test models used for test purposes shall be visibly different from live items with the colour code in Table 4 2 NOTE This is to prevent confusion and to ensure incorrect items are not used for flight or qualification Table 4 2 Explosive component colour code Colours related to component behaviour Detonation yellow orange Deflagration brown light Inert red orange bright Colours related to the state or purpose of component red bright Safe
25. acilities and equipment shall be in accordance with ECSS E ST 10 02 b Uncontrolled modifications to equipment or procedures shall be prohibited 58 EGS ECSS E ST 33 11C 31 July 2008 4 13 3 Launch site a The launch site shall provide specified transport handling and storage facilities for explosive components and systems The status of explosive safety barriers shall be monitored when the space vehicle induces a catastrophic risk NOTE The space vehicle comprises e g the launcher satellite spacecraft Provisions shall be made to make visible the status of explosive safety barriers Any indicators used to show the status of the explosive devices and the barriers shall be clear and unambiguous Periods of sensitivity to external environment shall be notified to the authorities NOTE Example of external environment is EMI Provisions shall be made for access to safe and arm devices for manual disarming 4 14 Verification 4 14 1 General a Following exposure to the conditions specified in Clause 4 14 3 explosive devices and systems shall meet the performance requirements specified in the appropriate Clauses 4 10 4 11 and 4 12 when measured in conformance with the requirements of Clause 4 14 3 4 14 2 Inspection Inspection shall be performed in conformance with ECSS Q ST 20 Non destructive inspection shall be used to demonstrate specified assembly and condition of every explosive compone
26. age and 53 ES ECSS E ST 33 11C 31 July 2008 4 12 Explosively actuated devices 4 12 1 General a For any explosively actuated device which incorporates initiation and explosive charges the requirements of Clause 4 11 shall apply b No released part shall cause damage c The requirements of Table 4 17 shall apply d Under the conditions in column E of Table 4 17 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 17 General requirements for explosively actuated device properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Leak rate scc He s TBPC N A At Ap 0 1 MPa before firing 2 Leak rate for Pai 2 5 10 2 at 10 Pa during firing spacecraft 3 Leak rate scc He s TBPC N A At Ap 0 1 MPa after firing 4 Temperatures a Non operating C TBPM TBPM b Operating C TBPM TBPM duration TBPM c Storage C TBPM TBPM duration TBPM d Transport C TBPM TBPM duration TBPM 5 Functional delay ms TBPM TBPM 6 Nr of assemblies TBPM TBPC To the maximum load of disassemblies TBPM TBPC the device attachments 7 Generated Shock g ms TBPM N A Time history and TBPC sampling rate Test configuration TBPC 8 Life time Year TBPM N A During transport storage and mission 54 EGS ECSS E ST 33 11C
27. and disconnection it shall be confirmed that no conductor is live and that no power can flow or be interrupted across the interfaces Immediately before every connection and disconnection it shall be confirmed that operator and parts are grounded to a common ground 67 EGS ECSS E ST 33 11C 31 July 2008 Annex A informative Component qualification test levels Table A 1 provides test levels that can be used for the qualification of components Table A 2 provides the pyroshock that can be used for launchers and satellites 68 ECSS E ST 33 11C E 31 July 2008 Table A 1 Component qualification test levels Environment Ariane 5 ESC Satellite see A5 SG 1 X 40 Section Number Cold 80 C 10 hours 5 2 120 C 48 hours Dry heat 110 C 5 hours 5 3 120 C 48 hours Damp heat 2x24h 20 C to 35 C _100 RH 5 4 N A badi cycles in damp Tan 21 C 1h to 33 C 1h 100 RH N A Thermal Vacuum 0 1 MPa to 106 MPa in 30s at 80 C N A Rain Equipment sprinkled 50mm h 30 face N A Salt Fog 24h with salt fog 24h without 5 9 N A 4 min axis 6 2 3 axis 1 sweep Per axis Per axis 5 Hz 16 Hz 10 mm peak to peak 5 Hz 25Hz 11 mm 16 Hz 30 Hz 10 g peak 1 3 25 Hz 100Hz 25 g peak 2 oct min oct min 30 Hz 70 Hz 22 5 g peak 70 Hz 200 Hz 50g peak 2 oct min 200 Hz 2000 Hz 22 5g peak Test temperature 80 C 110 C Sine Vibrations T
28. ar TBPM N A 50 EGS ECSS E ST 33 11C 31 July 2008 4 11 4 6 Distribution boxes a The properties of distribution boxes given in Table 4 14 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 14 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 14 Requirements for distribution box properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Input Output a Number TBPM TBPM b Interface type TBPM TBPM Design TBPM 2 Explosives a Quantity and g TBPM TBPM type b Response TBPM TBPM e g detonating deflagrating 3 Redundancy TBPM 4 Response time ms TBPM TBPM Between first input and all outputs a Generated o Ims TBPM N A Time history and TBPC Shock sampling rate Test configuration TBPC b Device leak rate sccHe s 10 N A Ap 0 1 MPa before firing c Device leak rate sccHe s 10 N A Ap 0 1 MPa after firing 5 Temperatures a Auto ignition C TBPM TBPM b Non operating C TBPM TBPM c Operating C TBPM TBPM d Storage C TBPM TBPM e Transport SC TBPM TBPM 6 Life time Year TBPM N A During transport storage and mission 51 EGS ECSS E ST 33 11C 31 July 2008 4 1
29. can never be tested in advance Particular care is needed in their development qualification procurement and use Explosive components are not governed by the institutional component control organisations The content and phasing of deliverable documents are identified in each of the top level discipline standards of each ECSS branch A list of deliverable documents specific to this standard is provided in informative Annex B 16 EGS ECSS E ST 33 11C 31 July 2008 4 1 2 Properties a 4 2 Design The two states of the properties of the explosive system before firing and after firing shall be identified and listed For every explosive component the function primary stimulus unwanted stimuli and secondary characteristics shall be identified and quantified Only qualified and lot accepted items shall be used in flight systems The properties of clause a shall remain stable over time before firing and after firing when subject to external loads or environmental conditions within the qualification values 4 2 1 General In case of redundancy no component shall adversely affect its substitute The system lay out should facilitate the replacement of subsystems or components Parts of the explosive system and devices identified as critical on the basis of a RAMS analysis shall be replaceable Replaceable parts shall be listed in the User s Manual of the explosive system and devices 4 2 2 Reliability and confi
30. containers shall protect the component from the mission Definition of containers shall be in conformance with UNO regulations ST SG AC 10 1 Rev 14 Manual of Tests and criteria NOTE It is good practice to pack explosive components individually to prevent changes in humidity and electrostatic charge Containers shall not be exposed to environments exceeding those specified NOTE It is good practice to use thermal and shock sensors Identification label shall be marked before delivery in a permanent way on each deliverable Containers shall be marked with the following information 1 Equipment name and part number Contents and quantity Mass gross and net in kilograms Contract number Supplier name and address EXPLOSIVE label with Hazard and compatibility classifications Gt S pio aR Fe Zo Following label Open only in clean room area by qualified operators if necessary Container shall indicate the orientation to be kept maintained 4 15 3 Facilities No explosive component shall be stored with other types of equipment The nature of and precautions required for all explosive components and systems shall be communicated to facility providers and authorities Storage of explosive devices shall be performed in conformance with ECSS Q ST 20 All explosive devices shall be stored in temperature and humidity controlled secure storage areas except when required for controlled spacecraft activities Record
31. d with the customer and suppliers d The circuits shall be verified by test or analysis to meet the requirements on reliability and on the prevention of unintentional function NOTE See clauses 4 2 2 and 4 5 2 4 8 2 3 Power system overload a The power supply shall ensure that the power subsystem is not overloaded before during or after the actuation of any explosive device even in case of a single point failure together with a short circuit both pin to pin and pin to ground 27 EGS ECSS E ST 33 11C 31 July 2008 4 8 2 4 Electromagnetic compatibility EMC a The explosive system power command and control electrical circuitry shall limit the generation of electromagnetic fields or conducted noise to a level at least 20 dB below the no fire power rating b The explosive system shall provide shielding to the same levels noted above when exposed to externally generated electromagnetic fields Control circuits shall limit the power level at any barrier to at least 20 dB below the minimum activation power 4 8 2 5 Electrostatic discharge a Explosive systems and components shall 1 survive 2 not be degraded by specified electrostatic discharges 3 be tested to verify survivability b Protective features shall be provided to 1 prevent initiation 2 prevent change of state of barriers 3 prevent parasitic paths 4 be tested to verify effectiveness c Electrostatic discharge to ground through the exp
32. ded twisted pair line or coaxial cable All connections between conductors shall be made by soldering crimping or connectors NOTE For soldering see ECSS Q ST 70 08 For crimping ECSS Q ST 70 26 For connectors see clause 4 10 1 4 10 3 Shielding a b The firing circuit including the initiator shall be shielded Isolators shall provide 20 dB attenuation at the specified electromagnetic frequencies Cable shielding shall provide 90 optical coverage Double layer cable shielding should be used For all other elements shielding there should be shielding at 100 optical coverage NOTE For example no gaps or discontinuities full shielding at the back faces of the connectors no apertures in any container housing elements of the firing circuit Shields shall not be used for current carrying NOTE Shields can be multiple point grounded to the structure 4 10 4 Faraday cap a b Faraday caps shall be used The Faraday cap shall prevent EEDs to be initiated by electromagnetic fields 33 EGS ECSS E ST 33 11C 31 July 2008 4 10 5 Safety cap a b Safety caps shall be used The safety cap shall contain the products of initiation of an explosive device It shall not be possible to install an explosive device with the safety cap mounted 4 10 6 Power a The explosive system shall make use of the available voltage and current supplies from the power subsystem to produce powe
33. dence a The explosive system shall achieve the specified properties within defined levels of reliability and confidence agreed with the customer NOTE1 All components are contributors NOTE2 This standard specifies the properties of particular concern The reliability of components shall be equal to or better than 0 999 with a confidence level equal to or better than 95 The probability of unwanted functioning of components shall be equal to or less than 0 001 with a confidence level equal to or better than 95 The performance characteristics of components at any level of assembly shall be specified at the specified level of reliability and confidence see 4 2 2b in conformance with ISO 16269 6 2005 The safety characteristics of items at any level of assembly shall be specified at the specified level of reliability and confidence see 4 2 2c It shall be agreed with the customer which performance characteristics shall be declared as mean values with associated standard deviation see 4 2 28 Manufacturer shall provide justification of the validity of the statistical methods for customer approval 17 EGS ECSS E ST 33 11C 31 July 2008 4 2 3 Performance a Except as specified in 4 2 3b all performance shall be quantified by measurement versus time of initial transitional and final values of the specified properties NOTE Specified properties are listed in clauses 4 11 and 4 12 The time interva
34. e 4 19 Requirements for puller properties E 56 Table 4 20 Requirements for pusher propertios ek 56 Table 4 21 Requirements for Cutter propertes E 57 Table 4 22 Requirements for valve properties eeeeeeeeeeeeeeeeeeeeeeneeeeeeeeeeeteeaaaeeeeeeeeeeeenaaa 58 Table 4 23 Safety E 61 Table 4 24 Reliability methods siisccscetcsectesissisceeteecinensiieatsieartdensnxeasaiseneeeeettencdiersideesietessmnersen 61 Table 4 25 Qualification tests scccccnccccrvccennccaviceesnarigtucdanneidenedennscetennagaunteenndechertaneatnaagtncirmeantae 63 Table 4 26 Acceptance tests 64 Table A 1 Component qualification test levels ccccccccccceeecsseeeenneeeeeeeesssssesesaeeeeeeesnseeeees 69 Table A 2 Pyroshocks for launcher and satellites cccccceeeceeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeeees 70 Table B 1 List of deliverable documents to be used in context of this standard An 71 ECSS E ST 33 11C E 31 July 2008 Introduction As any explosive item used for flight can function only once it can never be fully tested before its crucial mission operation The required confidence can only be established indirectly by the testing of identical items Test results and theoretical justification are essential for demonstration of fulfilment of the requirements The requirement for repeatability shows that product assurance plays a crucial role in support of technical aspects The need for statistics requires that the explosive components
35. e explosive system shall survive the specified sequence of conditions without malfunctioning or degrading beyond the specified limits The explosive system shall operate between the extremes of the ranges and combinations of specified conditions The limits used for the qualification of elements and interfaces shall conform to the specified reliability and confidence The end user shall specify the characteristics of the expected environment The end user shall specify the explosive system constraints The explosive system shall limit the mechanical electrical and thermal effects of its operation within limits agreed with the end user to avoid disturbance or damage to other sensitive elements on the space vehicle NOTE1 Examples of disturbance are shock electrical short circuits and magnetic fields NOTE2 For verification and tests see 4 14 4 7 Interface requirements 4 7 1 Overview The nature of the interfaces is geometry including the analysis of the dimensions for all phases of life NOTE E g assembly transport and flight mechanical including induced loads static and dynamic fluids including venting thermal loads electrical including ensuring electrical continuity and EMC materials including ensuring compatibility 4 7 2 Functional a Each interface shall 1 ensure no assembly errors can be made 2 prevent damage during assembly or dismantling Whilst separated protection shall be provided
36. ent or 1W power for five minutes The firing probability when subjected to the no fire current or no fire power for five minutes shall be less than 0 001 at 95 confidence level After exposure to the no fire current or no fire power the EED shall be capable to function in conformance with its requirements The properties of the 1W 1A No Fire initiator given in Table 4 4 shall be quantified and conform to the figures where shown Under the conditions in column E of Table 4 4 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 4 Requirements for low voltage initiator properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 DC insulation MQ N A 2 gt 250V gt 60s resistance 2 Breakdown kV 11 N A voltage 3 ESD survival kV N A 25 500 pF and 5000 ohms for pin to pin test 500 pF and 0 ohm for pin to case test 4 Dielectric uA 500 N A 200 V AC 60 s strength 5 All fire current A TBPM TBPM 99 9 of the units function with a confidence level of 95 specified conditions 6 All fire power Ww TBPM TBPM 99 9 of the units function with a confidence level of 95 specified conditions 7 Response time ms TBPM N A for all fire current or power 8 No fire A N A 1 lt 0 1 of the units function with a curr
37. ent confidence level of 95 5 minutes at specified conditions 9 No fire power W N A 1 lt 0 1 of the units function with a confidence level of 95 5 minutes at specified conditions 10 Bridge wire Q TBPM TBPM 10 mA eis resistance Number of applications TBPM 42 EGS ECSS E ST 33 11C 31 July 2008 4 11 2 3 High voltage initiators a The properties of the high voltage initiator given in Table 4 5 shall be quantified and conform to the figures where shown Under the conditions in column E of Table 4 5 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 5 Requirements for high voltage initiator properties A B C D E F Property Unit Maximum Minimum Condition Notes value value All fire voltage V TBPM TBPM 99 9 of the units function with a confidence level of 95 No fire voltage V TBPM TBPM lt 0 1 of the units function with a confidence level of 95 5 minutes test temperature TBPM Operating V gt 500 voltage 4 11 2 4 Laser initiators a The properties of the laser initiator given in Table 4 6 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 6 the properties in column A expressed in the units specified in column B shal
38. est temperature ambient 4 min axis 6 9 6 min axis 3 axes 20 Hz 0 0913 2 Hz 20 Hz 50 Hz 3 dB oct 20 Hz 150Hz 6 dB oct 50 Hz 600 Hz 2 g Hz 150 Hz 4 g Hz 600 Hz 2000 Hz 3 dB oct 350 Hz 4 9 Hz Random Vibrations 350 Hz 700 Hz tbd dB oct 700 Hz 3 g Hz 700 Hz 2000 Hz 10 7 dB oct 2000 Hz 0 1 g Hz Test temperature 80 C 110 C Test temperature ambient Y sinus 50g 11ms 2 sinus 50g 11ms Medium shocks Test temperature ambient 6 5 Test temperature ambient SRS _ Z1 level Appendix SRS _ Z4 level Pyroshocks Test temperature ambient 6 6 Test temperature ambient N A 30 krad Radiations Test temperature ambient Firing Tests conditions __ 80 C and 110 C 120 C and 120 C Note that the information within the brackets refers to the section number within A5 SG 1 X 40 69 ECSS E ST 33 11C E 31 July 2008 Table A 2 Pyroshocks for launcher and satellites Severity code Z1 Z4 Amplitude at 1 000 Hz 9 000 300 Amplitude at 2 000 Hz 17 500 1 000 Amplitude at 3 000 Hz 35 000 1750 Amplitude at 3 500 Hz 35 000 2 300 Amplitude at 4 000 Hz 35 000 3 000 Amplitude at 25 000 Hz 35 000 3 000 Tolerances for the amplitudes are 40 and 50 70 ECSS E ST 33 11C E 31 July 2008 Annex B informative List of deliverable documents Table B 1 List of deliverable documents to be used in cont
39. etonator and packaged charge ee d 41 Table 4 4 Requirements for low voltage initiator properties ceeeeeeeeeeeeeeeeeteeeeeeeeteeeeeees 42 Table 4 5 Requirements for high voltage initiator Gropertes eee eee ee eeeettnteeeeeeeeeeeeeeee 43 Table 4 6 Requirements for laser initiator properties 0 eee cece eeeeee eter ee eeeeeaaaeeeeeeeeeeeeee 43 Table 4 7 Requirements for mechanical initiator properties eee eeeeeeeeeeeeeeeeeentteeeeeeeeeeeee 44 Table 4 8 Requirements for packaged charge properties ssssseeseseerereeenetesttrrssrrrrreernene 44 Table 4 9 General requirements for transfer device Dropertes 46 Table 4 10 Requirements for transfer line assembly Droperties 47 Table 4 11 Requirements for through bulkhead transfer device properties nsssseneesne 48 ECSS E ST 33 11C E 31 July 2008 Table 4 12 Requirements for shaped charge properties A 49 Table 4 13 Requirements for expanding tube device Droperties ee eeeeeteeeeeeeeeeeeeteee 50 Table 4 14 Requirements for distribution box properties cc eeeeeeeeeeeeeeeeeeeeeeeeeetteeeteees 51 Table 4 15 Requirements for explosive delay properties AA 52 Table 4 16 Common requirements for gas generator cceeeceeeeeeeeeeeeeeeeeeeeeeeeeeeeeetaeeeeeees 53 Table 4 17 General requirements for explosively actuated device properties 0cee 54 Table 4 18 Requirements for separation nut and separation bolt properties ee 55 Tabl
40. ext of this standard Design justification file Verification matrix Risk management plan Verification control document Design reliability qualification plan Verification report Design reliability qualification justification reports Inspection reports User manual Acceptance test plan Declared materials list Configuration Item data list Declared mechanical part list Declared processes list Qualification list As built configuration list End item data package EIDP Certificate of conformity Mechanical thermal electrical ICDs 71 EGS ECSS E ST 33 11C 31 July 2008 Bibliography ECSS S ST 00 ECSS E ST 20 07 ECSS E ST 32 08 ECSS Q ST 70 ECSS Q ST 70 08 ECSS Q ST 70 26 ECSS Q ST 70 71 ECSS system Description implementation and general requirements Space engineering Electromagnetic compatibility Space engineering Materials Space product assurance Materials mechanical parts and processes Space product assurance Manual soldering of high reliability electrical connections Space product assurance Crimping of high reliability electrical connections Space product assurance Data for selection of space materials and processes 72
41. f this Standard the terms and definitions from ECSS S ST 00 01 apply in particular for the following terms lifetime 3 2 Terms specific to the present standard 3 2 1 all fire stimulus with a probability of functioning equal to or better than 0 999 at 95 confidence level 3 2 2 armed condition that allows the probability of a wanted event to be above an agreed limit 3 2 3 cartridge explosive device designed to produce pressure for performing a mechanical function NOTE A cartridge is called an initiator if it is the first or only explosive element in an explosive train 3 2 4 catastrophic failure failure resulting in loss of life or life threatening or permanently disabling injury or occupational illness or loss of an element of an interfacing manned flight system or loss of mission or loss of launch site facilities or long term detrimental environmental effects 3 2 5 charge explosive loaded in a cartridge detonator or separate container for use in an explosive device 11 EGS ECSS E ST 33 11C 31 July 2008 3 2 6 component smallest functional item in an explosive subsystem 3 2 7 deflagration reaction of combustion through a substance at subsonic velocity in the reacting substance 3 2 8 detonation chemical decomposition propagating through the explosive at a supersonic velocity such that a shock wave is generated 3 2 9 detonator initiator for high explosives 3 2 10 electro explosive device e
42. ge properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 AC leakage mA TBPM TBPM current 2 Bonding mQ 10 N A To next level assembly resistance 3 Thermal Vit TBPM TBPM response 4 Leak rate scc He s 106 N A Ap 0 1 MPa before and after firing 5 Structural MPa TBPM in conformance with integrity ECCS E 32 10 applies on MEOP 6 Temperatures a Auto ignition SC N A TBPM b Non operating C TBPM TBPM c Operating C TBPM TBPM Duration TBPM d Storage SC TBPM TBPM Duration TBPM e Transport C TBPM TBPM Duration TBPM 7 Generated a Pressure MPa TBPM TBPM TBPM Only the known and relevant output parameter shall be provided b Heat J TBPM TBPM TBPM Only the known and relevant output parameter shall be provided c Light lm TBPM TBPM TBPM Only the known and relevant output parameter shall be provided d Shock pressure GPa TBPM TBPM TBPM Only the known and relevant output parameter shall be provided 8 Probability of 99 8 95 confidence ignition of a reference charge 9 Nr of mating TBPM TBPC With without change de mating of seals cycles 10 Life time Year TBPM N A For transport storage and operation 41 EGS ECSS E ST 33 11C 31 July 2008 4 11 2 2 a 1W 1A No Fire initiators The minimum no fire rating shall be 1A curr
43. green 26 EGS ECSS E ST 33 11C 31 July 2008 4 8 1 5 Accessibility a Access shall be provided throughout the space vehicle integration 1 to the initiators safe test and arm plugs for connection 2 for measurements of properties 3 to all elements for inspection b Access shall be safe and convenient as agreed with the customer 4 8 2 Electrical 4 8 2 1 General a The explosive system firing sources shall have their own power distribution points b The explosive system shall provide power pulses to initiators at the times required by the application CG The power pulse shape amplitude and duration shall be as specified in the initiator input requirements d It shall be demonstrated by test that 4 8 2 1c is met e If the firing source circuit takes power from the host vehicle either The return side shall not be grounded on the payload side of the interface and be isolated from payload structure by at least 10 KQ measured at least 1 5 times the bus voltage or Isolation converters shall be used to provide at least 10 kQ isolation between payload return circuit and host vehicle return circuit when measured at least 1 5 times the bus voltage 4 8 2 2 Circuit independence a EEDs shall not be connected in series or in parallel with each other b A separate command shall activate each component for launch vehicles c In case 4 8 2 2a is not met the alternative circuit shall be justified and agree
44. hall 1 be independent of the firing circuits 2 use separate non interchangeable connectors 4 8 2 9 Insulation resistance a The explosive system shall neither function nor degrade as a result of the potential difference between the firing circuits and the shielding or the ground within specified limits 4 8 2 10 Dielectric strength a The explosive system shall neither function nor degrade as a result of leakage current of electrical firing circuits to ground 4 8 2 11 Sensitivity to RF energy a When exposed to RF conditions the induced power shall not exceed a level which is 1 20 dB below the no fire power 2 20 dB below the RF sensitivity threshold NOTE If no RF limit is known the DC limit can be used b When exposed to RF conditions the explosive system shall not be degraded 4 8 2 12 Magnetic cleanliness a The maximum level of residual magnetism shall be agreed with the end user NOTE Reduced levels can be achieved by the choice of suitable materials b The supplier shall provide the customer with the magnetic properties of the components 29 EGS ECSS E ST 33 11C 31 July 2008 c The explosive system shall not generate magnetic fields exceeding the Electromagnetic interference safety margins defined in ECSS E ST 20 4 8 2 13 Lightning a Explosive systems shall preclude activation due to electrical potential differences generated within the explosive system by exposure to l
45. he information provided by the model e g ageing temperature or batch influences non accuracy of the mathematical model non correlated behaviour NOTE2 While going through the design refinement loops Km can be progressively reduced down to 1 0 after the demonstration of satisfactory 19 EGS ECSS E ST 33 11C 31 July 2008 correlation between model and test measurements A specific project factor Kr shall be 1 defined according to programme maturity and the uncertainty in the programme level requirement 2 justified 3 applied NOTE1 Ke is generally defined by the project and can be reduced during the development NOTE 2_ Kp can also cover a growth potential for some further development An Explosive factor Ke shall be applied for uncertainties on the behaviour of explosive materials in the mission profile NOTE1 E g ageing and temperature influence batch influence material compatibility NOTE 2 Typical values are given in Table 4 1 NOTE3 Ageing programme and manufacturing qualification process e g batch influence wear of manufacturing tool can be used to reduce the Ke factor NOTE4 Dimensioning are done at the worst temperature of the qualification envelope Table 4 1 Values for explosive factor Explosive materials Ke Pyrotechnic compositions 21 1 Propellants e g NC NC NG composite 21 2 HE pure gt 1 1 HE composite 21 2 For Phases C
46. he interfaces on the fibre optic connector and the adapter which is used to join the two items The connector interface shall not be used for any purpose other than explosive devices The connector thread or closing mechanism shall be self locking The connection shall have electrical continuity with a resistance lt 10 mQ The connector shall be able to undergo 50 mating de mating cycles while meeting its requirements 4 11 4 Transfer devices 4 11 4 1 General a The properties of transfer devices shall conform to the general requirements of Table 4 9 and be quantified Under the conditions in column E of Table 4 9 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum 45 EGS ECSS E ST 33 11C 31 July 2008 Table 4 9 General requirements for transfer device properties A B C D E F Property Unit Maximum Minimum Condition Notes value value Critical diameter mm N A TBPM information about explosive to be provided Temperatures a Auto ignition C N A TBPM b Non operating C TBPM TBPM c Operating C TBPM TBPM Duration TBPM d Storage C TBPM TBPM Duration TBPM e Transport C TBPM TBPM Duration TBPM Probability of 99 8 95 confidence Ignition of a reference charge Nr of mating de TPBM TBPC With without change of seals
47. ightning b Explosive systems should preclude degradation by exposure to lightning NOTE For description of lightning see ECSS E ST 20 07 4 8 3 Thermal 4 8 3 1 Sensitivity a Explosive systems and components shall 1 survive to defined thermal loads in terms of intensity duration and cycling 2 not be degraded by defined thermal loads in terms of intensity duration and cycling 3 be tested to verify survivability b Protective features shall 1 be provided to prevent unintended initiation 2 be provided to prevent loss of performance 3 be tested to verify effectiveness Build up of heat shall be prevented d All thermally sensitive components shall be shielded or otherwise protected from the environment e Explosive systems and components shall not ignite at temperatures at least 30 C higher than the maximum expected environmental temperature NOTE This is to ensure no auto ignition or cook off 4 8 3 2 Heat generation a The explosive system shall not generate heat causing temperatures which exceed the specified limits 4 8 4 Status check 4 8 4 1 General a The explosive system shall provide for 1 measurements of electrical or optical properties during the integration of any circuit before and after firing without inducing firing unintentional status changes or degradation 30 EGS ECSS E ST 33 11C 31 July 2008 2 the indication of at least the status of the pre arm and select barrie
48. itiation of explosives 4 10 12 Initiator harness connector a The initiator harness connector shall conform to the interface requirements of the integral connector of the initiator b The initiator harness connector shall not be used for other purposes on the space vehicle 4 10 13 Initiator test substitute a Any initiator test substitute shall be representative with respect to properties which affect the results of the test 38 EGS ECSS E ST 33 11C 31 July 2008 4 11 Explosive components 4 11 1 General 4 11 1 1 Applicability a Clauses from 4 11 1 2 until 4 11 6 shall apply to explosive components which cannot be fully tested before flight For other elements of the system which can be fully tested before flight the equipment environmental test conditions of the end user shall apply NOTE The requirements for explosive components are given below as measurements to be made after specific preconditioning and under survival and operational conditions identified in 4 6 4 11 1 2 Identification Identification marking shall be in conformance with ECSS M ST 40 For launchers colour coding shall be used on components to indicate behaviour Each component containing explosives shall be visibly and permanently marked with 1 a unique identification 2 coding to indicate behaviour Identification should include Manufacturer Part number Lot number Serial number Manufacturing date Colour codi
49. l be able to withstand the maximum expected operational loads times a factor FOSU 18 EGS ECSS E ST 33 11C 31 July 2008 The factor FOSU shall be in conformance with Tables 4 3 in ECSS E ST 32 10 depending on the material used Deformation of any component shall not 1 reduce its specified performance 2 affect any part of the spacecraft system 3 cause leakage The factor FOSY shall be in conformance with Table 4 3 in ECSS E ST 32 10 depending on the material used 4 2 5 3 Explosive charge sizing a For phases A and B of the component the methodology for dimensioning explosive devices shall be justified A margin policy factor Kup shall be 1 defined 2 justified 3 applied NOTE1 This factor used to give confidence to the design covers not exhaustive list e The lack of knowledge on the failure modes and associated criteria e The lack of knowledge on the effect of interaction of loadings e The non tested zones NOTE 2 Justification can be performed based on relevant historical practice analytical or experimental means Kur can have different values according to the explosive behaviour When modelling is performed a model factor Km shall be 1 defined 2 justified 3 applied during simulations and analysis NOTE1 A model factor Km is applied in cases where uncertainty exists in the model in terms of predicted response and loads It encompasses the lack of confidence in t
50. l be between the values in column C maximum and column D minimum Table 4 6 Requirements for laser initiator properties A B C D E F Property Unit Maximum Minimum Condition Notes value value All fire power W mm TBPM TBPM 99 9 of the units function density with a confidence level of 95 No fire power W mm TBPM TBPC lt 0 1 of the units function Factor of safety for density with a confidence level of spurious lights 95 5 minutes at specified TBPC conditions wavelength TBPM Pulse width ms N A TBPM Wave length nm TBPM TBPM Depending on optical source solid laser laser diode 43 ECSS E ST 33 11C EGS 31 July 2008 4 11 2 5 Mechanical initiators a The properties of the mechanical initiator given in Table 4 7 shall be quantified and conform to the figures where shown b Under the conditions in column E of Table 4 7 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum Table 4 7 Requirements for mechanical initiator properties A B C D E F Property Unit Maximum Minimum Condition Notes value value All fire energy J TBPM TBPM 99 9 of the units function with a confidence level of 95 No fire energy J lt 0 1x minimum TBPM 0 1 of the units function with all fire energy a confidence level of 95 Test energy J N A TBPM 4 11 2 6 Packaged charges
51. l specified in a shall be measured between either a clear reproducible initiation event and the attainment of the performance value or the initiation event and 90 of the measured performance value For performance that cannot be quantified based on measurements an acceptance procedure shall be agreed with the customer The basis of the time shall be specified and justified 4 2 4 Wanted and unwanted response a For wanted response the response of any component when subjected to the specified minimum probable stimulus shall be demonstrated to be more than the specified lower limit agreed between customer and supplier For unwanted response the response of any component when subjected to the specified maximum possible disturbance shall be demonstrated to be less than the specified upper limit agreed between customer and supplier NOTE This applies to safety and failure 4 2 5 Dimensioning 4 2 5 1 Strength a The explosive system shall sustain before during and after firing 1 the internal loads due to operation and 2 the external loads defined by the end user NOTE These loads represent the sum of preload static dynamic thermal and any other load seen in service 4 2 5 2 Integrity a The explosive system shall maintain its integrity and position during its lifetime Components that are intended not to rupture during operation when installed into their explosive system interfaces shal
52. losive elements shall be prevented d Build up of electrostatic charges shall be prevented e Measures to satisfy requirement 4 8 2 5d shall not violate single point grounding requirements f All ESD sensitive components shall be identified and listed g Unplanned electrostatic discharges shall be avoided 4 8 2 6 Voltage drop a The voltage drop in the electrical circuit shall be incorporated in the provision of the required firing pulse 4 8 2 7 Electrical bonding a The resistance to electrical ground shall not exceed the specified value NOTE See requirements on Electrical bonding in ECSS E 20 07 b The metallic parts of the explosive components shall be bonded by direct contact The shielding of the firing circuits shall be bonded at least at both ends 28 EGS ECSS E ST 33 11C 31 July 2008 4 8 2 8 Isolation a Every electrical firing circuit and monitoring circuit shall be electrically independent b The explosive system shall isolate the function to prevent power drain or parasitic paths before and after firing c Provision shall be made to isolate power lines and return lines of the explosive system from electrical ground NOTE This is to prevent continued drain on the power system after firing when e g short circuit to ground can occur d Provisions for redundancy shall not prevent fulfilment of the requirement 4 8 2 8a e Safe and arm device control and check out circuits s
53. ng should be in conformance with Table 4 2 4 11 1 3 Contamination a The following types of contamination shall be prevented 1 from environment to the components 2 from components to the environment 3 related to the innocuousness of component during and after functioning NOTE Contamination can be prevented e g by the use of approved materials in conformance with ECSS Q ST 70 71 and by design to contain products of the operation of explosive components In case clause 4 11 1 3a cannot be met a component shall not be accepted unless the limits of the amount and type of contamination are identified by the manufacturer and agreed with the end user 39 EGS ECSS E ST 33 11C 31 July 2008 4 11 1 4 After functioning a After functioning no explosive component shall cause 1 any disturbance beyond limits agreed with the end user 2 contamination beyond limits agreed with the end user 4 11 2 initiators cartridges detonators and packaged charges 4 11 2 1 General a The properties of initiators given in Table 4 3 shall be quantified and conform to the figures where shown Under the conditions in column E of Table 4 3 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum 40 EGS ECSS E ST 33 11C 31 July 2008 Table 4 3 Common requirements for initiator cartridge detonator and packaged char
54. nt NOTE E g X Ray or N Ray Resolution shall be better than the dimension of the smallest feature to be checked NOTE To be able to detect e g micro cracks It shall be demonstrated by inspection of all fired components that the internal dimensions surfaces and material properties have not been degraded beyond specified limits NOTE Erosion corrosion and burning due to the functioning can cause failure or leakage 59 EGS ECSS E ST 33 11C 31 July 2008 4 14 3 Tests 4 14 3 1 Test specification a Test specification shall be performed in conformance with ECSS E ST 10 03 b The test conditions for explosive components and systems shall be derived from the operational conditions and constraints NOTE E g ground flight in orbit c Qualification and lot acceptance tests shall be in conformance with clause 4 14 4 d Acceptance tests shall be done at identical limit conditions and levels whatever the application to ensure valid reference to previous results and to reduce the numbers of tested items 4 14 3 2 Test operations a Test operation shall be performed in conformance with ECSS E ST 10 03 4 14 3 3 Test results a Test results shall be performed in conformance with ECSS E ST 10 03 4 14 3 4 Essential confirmation a For every test connection to the correct initiator shall be checked and recorded 4 14 3 5 Routing tests a It shall be demonstrated that the correct stimulus arrives at the co
55. of the explosives shall be reported and shall be compared with the mission requirements Degradation of the explosives shall not exceed agreed limits Degradation of explosive characteristics shall be determined by test NOTE Test methods can be DTA DSC TGA VTS 4 10 Non explosive components and equipment 4 10 1 Connectors a b There shall be only one connection per pin The requirements of clause 4 7 2 shall apply to non explosive components and equipment Mis mating of connectors shall be impossible NOTE E g by geometry lay out dimensions or harness length The insert polarization and contact arrangement of the connectors used in the explosive system shall not be used elsewhere on the space vehicle Source circuits shall be terminated by female contacts Spare or un terminated contacts shall not exist Prime and redundant circuits for the same function shall not pass through the same connector Electrical connectors shall provide continuous shielding in all directions 32 EGS ECSS E ST 33 11C i 31 July 2008 Electrical connectors shall provide continuous shielding during 1 engagement before the pins connect 2 disengagement after the pins disconnect Connector savers shall be used NOTE This is to prevent the receptacle and contacts from wear and damage 4 10 2 Wiring a Electrical supply for each initiator optical source and Safe and arm device shall be by a separate shiel
56. ovisions of this ECSS Standard For dated references subsequent amendments to or revision of any of these publications do not apply However parties to agreements based on this ECSS Standard are encouraged to investigate the possibility of applying the more recent editions of the normative documents indicated below For undated references the latest edition of the publication referred to applies ECSS S ST 00 01 ECSS E ST 10 02 ECSS E ST 10 03 ECSS E ST 20 ECSS E ST 32 10 ECSS E ST 33 01 ECSS Q ST 20 ECSS Q ST 30 ECSS Q ST 40 ECSS Q ST 70 01 ECSS M ST 40 ISO 16269 6 2005 ST SG AC 10 1 Rev 14 UNECE publication ECSS system Glossary of terms Space engineering Verification Space engineering Testing Space engineering Electrical and electronic Space engineering Reliability based mechanical factors of safety Space engineering Mechanisms Space product assurance Quality assurance Space product assurance Dependability Space product assurance Safety Space product assurance Contamination and cleanliness control Space management Configuration and information management Statistical interpretation of data Part 6 Determination of a statistical tolerance interval First edition 2005 04 01 Recommendation on the Transport of Dangerous Goods 10 ECSS E ST 33 11C E 31 July 2008 3 Terms definitions and abbreviated terms 3 1 Terms defined in other standards For the purpose o
57. ptical initiators the safe plug shall be capable of absorbing or redirecting n times the maximum power the laser can generate with n defined by the end user C The safe plug shall be 1 2 3 4 10 9 compatible with the safe and arm connector receptacle suitable for use with flight hardware suitable for the number of connection cycles necessary to cover integration test and use scoop proof lockable NOTE E g sub D connector bayonet or triple start thread type visibly identified carrying a Remove before Flight banner Arming plug a The arming plug shall 1 provide electrical continuity between the supply and firing circuits with electrical properties in any line agreed with the customer NOTE Electrical properties include resistance isolation bonding and faraday protection be compatible with the safe and arm connector be scoop proof be lockable NOTE E g sub D connector bayonet or triple start thread type be visibly identified 35 EGS ECSS E ST 33 11C 31 July 2008 4 10 10 Test plug 4 10 11 a 1 The test plug shall provide electrical access to the firing circuits with electrical properties in any line agreed with the end user NOTE Electrical properties include resistance isolation bonding and faraday protection be compatible with the safe and arm connector not carry any potential or current at the time of insertion or removal be
58. quantified and conform to the figures where shown b Under the conditions in column E of Table 4 12 the property in column A in the units in column B shall be between the values in column C maximum and column D minimum 48 ES ECSS E ST 33 11C 31 July 2008 Table 4 12 Requirements for shaped charge properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Cutting capabilities a Structure mm TBPM N A associated with material thickness properties b Structure loads MPa TBPM TBPM c Cutting delay ms TBPM TBPM 2 Debris contamin ation induced 3 Temperatures a Auto ignition C b Survival Non C TBPM TBPM operating c Operational C TBPM TBPM operating d Storage C TBPM TBPM e Transport S TBPM TBPM 4 Life time Year TBPM N A during transport storage and mission 4 11 4 5 Expanding tube devices a The properties of expanding tube devices given in Table 4 13 shall be quantified and conform to the figures where shown NOTE These devices include separation systems based on e detonation shock and deformation e inflation pressure generated e combination of the above Under the conditions in column E of Table 4 13 the properties in column A expressed in the units specified in column B shall be between the values in column C maximum and column D minimum 4
59. r pulses of suitable size duration and timing for each of the functions The firing pulse requirements in Table 4 4 row 5 and Table 4 6 row 1 shall apply for EEDs and laser initiators respectively The power provided at the power distribution points shall be such that the requirements of 4 8 2 6 allowing for losses are met 4 10 7 Safe and arm connector a A connector shall be provided on the exterior surface of the space vehicle for use with manually inserted plugs to enable 1 isolation 2 coupling of any explosive system 3 testing of any explosive system Provision shall be made for access to the interface Requirements for access shall be communicated to the customer and facilities authorities The safe and arm connector shall be visibly identifiable The safe and arm connector shall be qualified for the number of specified connection cycles NOTE E g to cover integration test and use The receptacle shall meet the requirements of clause 4 10 1 NOTE Sub D connector self locking bayonet or triple start thread type can be used A connector saver shall be used NOTE This is to prevent the receptacle and contacts from wear and damage 34 EGS ECSS E ST 33 11C 31 July 2008 4 10 8 Safe plug a For electrical initiators the safe plug shall 1 short circuit each initiator 2 ground each shorted initiator circuit 3 short circuit each firing circuit 4 ground each firing circuit b For o
60. rop height m mass of drop weight kg standard deviation Ampere Volt 15 ECSS E ST 33 11C E 31 July 2008 4 Requirements 4 1 General 4 1 1 Overview Being generally applicable the requirements stated in this section apply throughout and are not repeated in the sections relating to specific topics Explosive systems and devices use energetic materials explosives propellants powder initiated by mechanical electrical thermal or optical stimuli for unique single shot functions e g solid booster initiation structure cutting stage distancing pressurized venting stage neutralisation valve opening or closing release of solar arrays antennas booms covers and instruments The properties of the initiator govern the major part of the behaviour of the system The requirements for initiators and their derivatives such as cartridges and detonators are defined in specific requirements related to the specific types Properties of explosive components and systems which cannot be covered by requirements for the initiators alone are defined in specific requirements relating to the types of actuator Other components of the explosive system which can be tested and do not need specific requirements are subject to the general technical and product assurance requirements Detailed aspects of these components are included where they have a significant influence on the success of the system Single shot items
61. rrect initiator and no other b Records shall be kept of the routing test 4 14 3 6 End to end tests a Functional tests shall be performed in conformance with ECSS E ST 10 03 b Only planned and approved activities shall be performed in conformance with approved procedures c Firing tests shall not be performed until a successful rehearsal has been completed 4 14 3 7 Safety tests a Safety tests shall be performed on unpacked articles in conformance with Table 4 23 60 EGS ECSS E ST 33 11C 31 July 2008 Table 4 23 Safety tests Recommended Reference tests TEST Method sequence Launcher Spacecraft Slow cook off UNO Manual of tests and criteria test 7 h R N A External Fire UNO Manual of tests and criteria test 7 g R N A pele ee E TBPC R O 12 m Drop test UNO Manual of tests and criteria test 4 b R N A Mechanical Shock TBPC O N A rte ECSS E clause Lightning Szen O N A Requirements for the space system R Required O Optional N A Not Applicable 4 14 3 8 Lifetime demonstration a Lifetime tests or analysis shall be done to establish changes over time in performance and susceptibility b If accelerated aging is used it shall be justified 4 14 3 9 Reliability tests a For any component performances shall be declared in terms of reliability confidence level test and analysis methods b The methods given in Table 4 24
62. rs during the mission The functionality shall be provided to verify the status of the barriers protecting the initiator before inserting the arming plug Check out circuits shall not allow current flow or electrostatic discharge causing unintentional effects in the explosive system NOTE This applies also after any single failure Any checking out of the status of electrical initiators shall limit the check out current to 102x the no fire xcurrent on the bridge wire Any checking out of the status of optical initiators shall limit check out energy to 10 x the no fire power density at the fire wavelength on the optical interface if the fire wavelength is used The checking out power or current or optical wavelength or frequency shall cause no unintentional effects or hazards also after any single failure Any checking out of the insulation resistance of the explosive system shall limit the voltage to 50 VDC Provision shall be made for an immediate warning signal to be given for any unplanned change of status of any explosive system control or check out device NOTE E g thermal control requirements or material temperature limits 4 8 4 2 initiator status 4 9 Materials a Provision shall be made for on ground checking the status of initiators Provision shall be made for access to the interface Requirements for access shall be communicated to the end user and facilities authorities NOTE Range safety
63. s of all environmental conditions in locations where explosive components or systems are stored or handled shall be maintained and be available for review NOTE E g environmental conditions such as thermal humidity 65 EGS ECSS E ST 33 11C 31 July 2008 The location of every live or fired explosive component or subsystem shall be known and identifiable at any time 4 15 4 Handling a 4 16 In service All handling shall be done by certified personnel in conformance with ECSS Q ST 20 NOTE Handling includes testing measuring installing All handling shall be done in conformance with specified procedures Personnel and equipment shall be grounded to a common ground Only approved tools aids and test equipment shall be used for explosive devices Consistent coherent and complete records shall be maintained of components or systems which have a direct effect upon the system including test activities and measurements during any upon the break in activities Restoration of the original accepted condition shall be required The correctness of all connections shall be confirmed and a record of all connections shall be maintained Site safety regulations provisions and procedures shall be checked for adequacy for explosive activities 4 16 1 Information feedback a Checks shall be made to assure the consistency of information between different equipment at different stages in the launch preparation
64. s shall be in conformance with Table 4 26 c Lot acceptance tests results shall confirm that the hardware conforms to the qualified product Table 4 26 Acceptance tests Acceptance test ECSS E ST 10 03 ECSS E ST 10 03 Spacecraft Launcher see Note 3 reference sequence component component physical properties YES 1 R R Secondary characteristics NO additional R R functional and performance YES See Note 1 N A N A leak YES 2 4 7 10 R R pressure YES 3 N A N A random vibration YES 5 O O acoustic YES 5 N A N A generated shock YES 6 N A N A thermal vacuum YES 8 O N A thermal cycling YES 8 O N A burn in YES 9 N A N A microgravity YES 11 N A N A audible noise YES 12 N A N A functional and performance YES See Note 2 O O destructive physical analysis NO additional O O R Required O Optional N A Not Applicable Note 1 Only possible at the end of the acceptance sequence Note 2 See 4 14 4 1 e Note 3 See Table for Acceptance test in ECSS E ST 10 03 4 15 Transport facilities handling and storage 4 15 1 General a Specified transport handling and facilities for explosive subsystems and devices shall be provided 64 EGS ECSS E ST 33 11C 31 July 2008 4 15 2 Transport a h Devices containing explosives shall be transported in conformance with ST SG AC 10 1 Rev 14 The transport classification should be 1 4 S The
65. senentness 27 48 3 Thermale ireen nen Ea AE aE E EEEa aE EEEa EE 30 4 8 4 Status CHOGCK issciissetesdecasanciissaccnsncesincesdacuisaniedaesctsanaiaueeenbccesnaianddtiesamedanoendas 30 EN 31 Non explosive components and equipment eseeeeeeeeeeeeeeeeeeeeeeneeeeeeeeeeeeneeneees 32 4101 GOMMOCIONS s cciscentsencscinciarssamntestahniateniaiaieminindtennigameeianadatnetiadiaasas 32 ANOS DEE ee 33 4 10 3 STUNNING BEE 33 4104A Faraday CAD eege eege 33 4 10 5 Safety e E 34 Gef We UE 34 4 10 7 Safe and arm connector E 34 4 10 8 Safe plug WEE 35 410 9 Arming plug EE 35 410 10 EK d UD 36 4 10 11 Safe and arm te E 36 4 10 12 Initiator harness connector ssseeeseeeeeeeeriiirtttteeeertrrrrrnsssssttrnnnnnanantnennn nna 38 4 10 13 Initiator test SUDS INU eenegen EE aeteenamianieeserertndariananaineseneiehaeeees 38 Explosive lee TT 39 AAA TEE 39 4 11 2 initiators cartridges detonators and packaged charges 40 4 11 3 Integral initiator CONNECHOIS cceeeeecnee ee eeeeeeeeeeee eens renee eeeeeeeeeeeneneeeeeeaes 44 AAT NEE 45 4 11 5 Safe and arm devices containing explosive ceeceeeeeeeeeeeeteeeeeeeeneeeeeeee 52 4 11 6 Gas GSMSP ANON ere AE 53 Explosively actuated GEIER saccscicicsscseseeveasisecediceasadensnncesed ese taenesaveccheanieadinecaishensens 54 SEN 54 4 12 2 Separation nuts and separation Dote 55 AN TIET 56 4124 PUSNOD i sccctcectdseial ndn nan E Eaa ENEA EREE E EE EEES 56 412 5 ug inr e a E a a E E E
66. shall be used for the component listed in the same row Table 4 24 Reliability methods Component Method Initiator Bruceton or Neyer Cutter Release nut Valve Pusher Puller Severe method TBI Severe method Shaped charge Probit or severe method Expanding tube Probit or severe method Transmission lines Bruceton or Neyer or Severe method 61 EGS ECSS E ST 33 11C 31 July 2008 4 14 4 Qualification and lot acceptance 4 14 4 1 General a Qualification and acceptance of explosive components and systems shall be in conformance with ECSS Q ST 20 For qualification each device shall meet the requirements specified in the appropriate table of clauses 4 11 and 4 12 after exposure to the complete sequence of conditions specified in Table 4 25 For lot acceptance each device shall meet the requirements specified in the appropriate table of clauses 4 11 and 4 12 after exposure to the selected conditions specified in Table 4 26 For lifetime each device shall meet the requirements specified in the appropriate table of clauses 4 11 and 4 12 after exposure to the complete sequence of conditions specified in Table 4 25 Dynamic leak measurement shall be made under vacuum 4 14 4 2 Qualification tests a Qualification tests shall be performed in conformance with Table 4 25 NOTE Typical values are given in Annex A 62 EGS ECSS E ST 33 11C
67. ssed in the units specified in column B shall be between the values in column C maximum and column D minimum 57 ECSS E ST 33 11C E 31 July 2008 Table 4 22 Requirements for valve properties A B C D E F Property Unit Maximum Minimum Condition Notes value value 1 Valve capabilities Associated with fluid properties a MEOP MPa TBPM TBPM in fluid circuit b Pressure drop MPa TBPM TBPM in fluid circuit c Valve passage mm TBPM in fluid circuit diameter nominal d Fluid circuit leak rate scc He s 10 6 TBPM At Ap 0 1 MPa before Before and after and after firing functioning e Internal leak rate scc He s TBPC TBPM TBPM During functioning Blow by 2 Mass of generated mg TBPM N A in fluid circuit particles 3 Dimensions of mm TBPM TBPM in fluid circuit generated particles 4 13 Items external to the flight equipment 4 13 1 GSE a Verification of GSE shall be performed in conformance with ECSS E ST 10 02 b Ground support equipment shall provide support and protection within specified limits including ESD and EMI c Test equipment shall be energy limited in conformance with 4 8 4 NOTE E g electrical optical d The status indication of the explosive system shall be provided e Changes in the status indications shall be provided f Status and status changes shall be recorded 4 13 2 Test equipment a Integration and test f
68. tion 4 5 2 1 General The firing pulse shall be prevented from reaching any explosive initiator at any time except the correct instant by means of switchable barriers NOTE For example e Firing pulse detonating shock electrical pulse and light pulse e Switchable barriers electrical mechanical plugs and pins Provision shall be made to prevent firing in response to radio frequency lightning magnetic field and electrostatic discharge NOTE See the requirements on Lightning environment and the Detailed requirements for verification at system level Lightning in ECSS E ST 20 07 If the explosive system contains two or more barriers then at least two of these barriers shall 1 be independent 2 not be subject to common cause failure 3 each provide complete disconnection of the firing circuit 22 EGS ECSS E ST 33 11C 31 July 2008 For explosive systems involving a potential catastrophic risk the barrier close to the source of the risk shall be a mechanical barrier The primary and redundant EEDs shall not be activated through the same electrical firing circuit Stray circuits or coupling which can result in unintentional firing shall be avoided 4 5 2 2 Safe and arm device pre arm function The pre arm function shall be the fourth last in a sequence of functions The pre arm function shall be independent and respond only to a unique action The pre arm function shall remain in i
69. ts switched state after operation until the fire function has reverted to its initial state The pre arm function may include the select function NOTE A safe and arm device is not always included 4 5 2 3 Select function The select function shall be the third last in a sequence of functions The select function shall select the explosive devices The select function shall be independent and respond only to a unique command The select function shall be used to control only one explosive function It shall revert to its initial state after the fire command within an interval agreed with the customer 4 5 2 4 Arm function The arm function shall be the second last action in the sequence The arm function shall be independent and respond only to a unique command The arm function shall be used to control only one explosive function The functionality shall be provided to restore its initial disarm state after the arm command within an interval agreed with the customer 4 5 2 5 Fire function The fire function shall be the last action in the sequence The fire function may be used to activate several of explosive devices The fire function shall be independent and respond only to a unique command The fire function shall revert to its initial state after the firing command within an interval agreed with the customer 23 EGS ECSS E ST 33 11C 31 July 2008 4 6 Survival and operational conditions a Th
70. used in the explosive system be tested and characterized extensively The variability in components requires that manufacturers prove to customers that delivered items are identical to those qualified The failure or unintentional operation of an explosive item can be catastrophic for the whole mission and life threatening Specific requirements can exist for the items associated with it As all explosives where ever used are to be treated similarly the same requirements regulations practices and standards need to be applied which will help to avoid human error In case there is sufficient data to establish the reliability and confidence level for any given performance against any given condition this should be done Subsequently all margins should be converted into standard deviations and be incorporated into the reliability and confidence analysis ECSS E ST 33 11C E 31 July 2008 1 Scope This Standard defines the requirements for the use of explosives on all spacecraft and other space products including launch vehicles It addresses the aspects of design analysis verification manufacturing operations and safety This standard may be tailored for the specific characteristics and constraints of a space project in conformance with ECSS S ST 00 EGS ECSS E ST 33 11C 31 July 2008 2 Normative references The following normative documents contain provisions which through reference in this text constitute pr
71. utput or both NOTE E g pyrotechnic igniters for solid propulsion applications gas generator for inflatable structures 3 2 21 initiator first explosive element in an explosive train that upon receipt of the proper mechanical optical or electrical impulse produces a deflagrating or detonating action NOTE1 The deflagrating or detonating action is transmitted to the following elements in the train NOTE 2 _Initiators can be electrically actuated EEDs optically actuated or mechanically actuated 3 2 22 limit testing testing to establish the limit of a performance characteristic of a component 3 2 23 lot group of components produced in homogeneous groups and under uniform conditions NOTE A batch is the same as a lot 3 2 24 lot acceptance demonstration by measurement or test that a lot of items meets requirements 3 2 25 no fire stimulus with a probability of functioning equal to or less than 0 001 at 95 confidence level 3 2 26 operational envelope set of conditions in which the device or system shall meet its requirements 3 2 27 packaged charge explosive material in a closed container 3 2 28 qualification envelope positive margin over the conditions of the operational envelope 13 ECSS E ST 33 11C E 31 July 2008 3 2 29 safe condition that renders the probability of an unwanted event below an agreed limit 3 2 30 secondary characteristic any characteristic other than the function
72. xplosive cartridge that is electrically actuated 3 2 11 end user person who or organization that actually uses a product NOTE1 The end user need not be the owner or buyer NOTE 2 In the context of this standard the end user is generally the first level customer 3 2 12 explosive actuator mechanism that converts the products of explosion into useful mechanical work 3 2 13 explosive train series of explosive components including the initiator explosive transfer assembly and explosive actuator 3 2 14 explosive component any discrete item containing an explosive substance 3 2 15 explosive function any function that uses energy released from explosive substances for its operation 3 2 16 explosive system collection of all the explosive trains on the spacecraft or launcher system and the interface aspects of any on board computers launch operation equipment ground support and test equipment and all software associated with explosive functions 3 2 17 extreme envelope positive margin over the conditions of the qualification envelope NOTE The device or system design is based on the conditions that define the extreme envelope 12 EGS ECSS E ST 33 11C 31 July 2008 3 2 18 end of life point in time when no characteristic has any further significant effect 3 2 19 fail operational the mission is possible after a failure 3 2 20 gas generators explosive devices that produce a volume of gas or exothermic o

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