ISO 26871-2012 Space systems - Explosive systems and devices《空间系统 爆炸系统和设备》.pdf

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1、 ISO 2012 Space systems Explosive systems and devices Systmes spaciaux Dispositifs et equipements explosifs INTERNATIONAL STANDARD ISO 26871 First edition 2012-12-01 Reference number ISO 26871:2012(E) ISO 26871:2012(E)ii ISO 2012 All rights reserved COPYRIGHT PROTECTED DOCUMENT ISO 2012 All rights r

2、eserved. Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying and microfilm, without permission in writing from either ISO at the address below or ISOs member body in the country of the req

3、uester. ISO copyright office Case postale 56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.org Web www.iso.org Published in Switzerland ISO 26871:2012(E) ISO 2012 All rights reserved iii Contents Page Foreword iv 1 Scope . 1 2 Normative references 1 3 T erms, def

4、initions, abbr e viat ed t erms and s ymbols . 1 3.1 Terms and definitions . 1 3.2 Abbreviated terms . 5 3.3 Symbols . 7 4 Requirements 7 4.1 General . 7 4.2 Design . 9 4.3 Mission 13 4.4 Functionality 13 4.5 Safety 14 4.6 Survival and operational conditions .15 4.7 Interface requirements .16 4.8 Me

5、chanical, electrical, and thermal requirements 17 4.9 Materials 22 4.10 Non-explosive components and equipment .22 4.11 Explosive components .27 4.12 Explosively actuated devices .39 4.13 Items external to the flight equipment 43 4.14 Verification 43 4.15 Transport, facilities, handling and storage

6、48 4.16 In-service 49 4.17 Product assurance .50 4.18 Deliverables 50 Annex A (normative) Loads and factors of safety relationship .53 Annex B (normative) Factors of safety 54 Annex C (informative) Explosive component colour code 56 Annex D (informative) C omponent qualification t est le v els .57 A

7、nnex E (informative) Product user manual (PUM/UM) DRD .59 Bibliogr aph y .66 ISO 26871:2012(E) Foreword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Standards is normally carri

8、ed out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also take part in the work. I

9、SO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 2. The main task of technical committees is to prepare Internati

10、onal Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting a vote. Attention is drawn to the possibility that some of the el

11、ements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 26871 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2012 All rights

12、reserved INTERNATIONAL ST ANDARD ISO 26871:2012(E) Space systems Explosive systems and devices 1 Scope This International Standard specifies requirements for the use of explosives on spacecraft and other space products, including launch vehicles. It addresses the aspects of design, analysis, verific

13、ation, manufacturing, operations and safety. NOTE Specific requirements for man-rating are not addressed. 2 Normative references The following documents, in whole or in part, are normatively referenced in this document and are indispensable for its application. For dated references, only the edition

14、 cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 14300-1, Space systems Programme management Part 1: Structuring of a project ST/SG/AC.10/1, UN Recommendations on the transport of dangerous goods (Model Regulations) UNO Man

15、ual of Tests and Criteria. United Nations, Fifth Edition, 2010 Mil-std 1576, Electroexplosive Subsystem Safety Requirements and T est Methods for Space Systems, USAF, 1992 3 T erms, d efinitions , abbr e viat ed t erms and s ymbols 3.1 T erms and definiti ons For the purposes of this document, the f

16、ollowing terms and definitions apply. 3.1.1 actuator component that performs the moving function of a mechanism NOTE An actuator can be either an electric motor, or any other mechanical (e.g. spring) or electric component or part providing the torque or force for the motion of the mechanism. 3.1.2 a

17、 l l-f i r e lev e l lowest level of the fire stimulus (including rise time, shape, duration), which results in initiation of a first element (initiator) within a specific reliability and confidence level as determined by test and analysis NOTE 1 The stimulus duration shall be compliant with the sys

18、tem. NOTE 2 It is recommended that the test sequence be carried out at the lowest temperature of the operating range. NOTE 3 The probability of functioning should be equal to or better than 0,999 at the 95 % confidence level. 3.1.3 armed condition that allows the probability of a wanted event to be

19、above an agreed limit ISO 2012 All rights reserved 1 ISO 26871:2012(E) 3.1.4 c a r t r id g e 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. 3.1.5 catastrop

20、hic failure failure resulting in loss of life, loss of mission or loss of launch capability 3.1.6 c h a r ge explosive loaded in a cartridge, detonator or separate container for use in a explosive device 3.1.7 component smallest functional item in a explosive subsystem 3.1.8 d e f lag ra t i o n rea

21、ction of combustion through a substance at subsonic velocity in the reacting substance 3.1.9 detonation chemical decomposition propagating through the explosive at a supersonic velocity such that a shock wave is generated 3.1.10 detonator first element whose output is a high-order detonation NOTE De

22、tonators are generally used to effect detonation transfers within explosive trains. 3.1.11 dud explosive charge or component that fails to fire or function upon receipt of the prescribed initiating stimulus, after an external effect (human failure, manufacturing failure, environmental, chemical, age

23、ing, etc.) 3.1.12 electro-explosive device explosive cartridge that is electrically actuated 3.1.13 end user person who, or organization that, actually uses a product NOTE The end user is not necessarily the owner or buyer. 3.1.14 explosive US e n e r g e t i c m a t er i a l GB material which is ca

24、pable of undergoing an explosion when subjected to heat, impact, friction, detonation or other suitable initiation 3.1.15 explosive actuator mechanism that converts the products of explosion into useful mechanical work 3.1.16 explosive component any discrete item containing an explosive substance2 I

25、SO 2012 All rights reserved ISO 26871:2012(E) 3.1.17 explosive function any function that uses energy released from explosive substances for its operation 3.1.18 explosive system collection of all the explosive trains on the spacecraft or launcher system, and the interface aspects of any on-board co

26、mputers, launch operation equipment, ground support and test equipment and all software associated with explosive functions 3.1.19 explosive train series of explosive components, including initiating and igniting elements, explosive transfer assembly and explosive actuator, arranged to realise the p

27、yro effect required 3.1.20 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. 3.1.21 g a s g en er a t o r explosive device that produces a volume of gas or exothermic output

28、 or both EXAMPLE Pyrotechnic igniters for solid propulsion applications, gas generator for inflatable structures. 3.1.22 initiator first explosive element in an explosive train which, upon receipt of the proper mechanical, optical or electrical impulse, produces a deflagrating or detonating action N

29、OTE 1 The initiator is divided into three categories: 1) igniter, a first element whose output is hot gases and hot particles (igniters may be initiators for solid or liquid propellant); 2) squib, a first element whose output is primarily gas and heat (squibs may be initiators for gas generators and

30、 igniters or may be cartridges for actuated devices); 3) detonator, a first element whose output is a high-order detonation (detonators are generally used to effect detonation transfers within explosive trains). NOTE 2 The deflagrating or detonating action is transmitted to the elements following in

31、 the train. NOTE 3 Initiators can be electrically (EEDs), optically or mechanically actuated. 3.1.23 launcher launch vehicle system used to transport a payload into orbit 3.1.24 lifetime period over which any properties are required to be within defined limits 3.1.25 lot b at c h group of components

32、 produced in homogeneous groups and under uniform conditions 3.1.26 lot acceptance demonstration by measurement or test that a lot of items meet its requirements ISO 2012 All rights reserved 3 ISO 26871:2012(E) 3.1.27 no -f i r e lev e l maximal level of input energy with an ignition stimulus (inclu

33、ding nominal rise time and shape as required by the system, but with a 5 min extended duration), to a first element (initiator) at which initiation will not occur within a specific reliability and confidence level as determined by test and analysis NOTE 1 It is recommended that the test sequence be

34、carried out at the hottest temperature of the operating range. NOTE 2 The probability of functioning should be less than or equal to 0,001 at the 95 % confidence level. NOTE 3 A first element tested at this level shall remain safe and functional and shall guarantee the level of performances required

35、 after the no-fire level test. 3.1.28 operational envelope set of conditions in which the device or system meets its requirements 3.1.29 p a c k a g e d c h a r g e explosive material in a closed container 3.1.30 primary explosive substance or mixture of substances used to initiate a detonation or b

36、urning reaction NOTE In their intended role, these materials are sensitive to a range of thermal, mechanical and electrical stimuli, including exposures during processing. 3.1.31 pyrotechnic device device or assembly containing, or actuated by, propellants or explosives, with the exception of large

37、rocket motors NOTE Initiators, ignitors, detonators, squibs, safe and arm devices, booster cartridges, pressure cartridges, separation bolts and nuts, pin pullers, linear separation systems, shaped charges, explosive guillotines, pyrovalves, detonation transfer assemblies (mild detonating fuse, conf

38、ined detonating cord, confined detonating fuse, shielded mild detonating cord, etc.), through-bulkhead initiators, mortars, thrusters, explosive circuit interrupters, and other similar items. 3.1.32 qu a l i f ic at ion e nve lop e positive margin over the conditions of the operational envelope 3.1.

39、33 safe condition that renders the probability of an unwanted event below an agreed limit 3.1.34 scoop-proof connector connector shell design in which the male contacts are recessed into the connector body to prevent mismating damage to pins (especially in blind mating applications) 3.1.35 secondary

40、 characteristic any characteristic other than the function 3.1.36 secondary explosive substance or mixture which will detonate when initiated by a shock wave, but which normally does not detonate when heated or ignited4 ISO 2012 All rights reserved ISO 26871:2012(E) 3.1.37 s eq u e n t ia l f ir ing

41、 application of the firing pulses to initiators separated in time 3.1.38 spacecraft satellite or other orbiting vehicle with self-propulsion 3.1.39 space vehicle any satellite or launch vehicle 3.1.40 success simultaneous achievement by all characteristics of required performance 3.1.41 s y m pa t h

42、 e t i c f ir ing firing of other explosive devices due to the output of any other 3.1.42 transfer line linear explosive assembly for propagation of deflagration or detonation 3.1.43 t hro ug h - b ulk h ea d ini t ia to r TBI device for transfer of detonating input to detonating or deflagrating out

43、put across a hermetically sealed barrier 3.1.44 user manual document provided by the supplier to describe all the appropriate rules of operations 3.2 A bbr e viat ed t erms AIT Assembly, integration and test AIV Assembly, integration and verification A/N As necessary CDR Critical design review DC Di

44、rect current DKP Design key point documentation DMPL Declared materials and processes list DRB Delivery review board DRD Document requirements definition DSC Differential scanning calorimetric DTA Differential thermal analysis EED Electro-explosive device EMC Electromagnetic compatibility ISO 2012 A

45、ll rights reserved 5 ISO 26871:2012(E) EMI Electromagnetic interference ESD Electrostatic discharge FMECA Failure modes, effects and criticality analysis FTA Fault tree analysis FOSU Ultimate design factor of safety FOSY Yield design factor of safety GSE Ground support equipment ICD Interface contro

46、l document MEOP Maximum expected operating pressure MRR Manufacturing readiness review N/A Not applicable NC Normally closed NO Normally open PDR Preliminary design review PUM User manual R Reliability RAMS Reliability, availability, maintainability, safety RF Radio frequency RFP Request for proposa

47、l S/C Spacecraft SRS Shock response spectrum TBI Through-bulkhead initiator TBPM To be provided by manufacturer TBPU To be provided by user TGA Thermo-gravimetric analysis TRR Test readiness review UM User manual UNO United Nations Organization VDC Voltage direct current VTS Vacuum thermal stability

48、6 ISO 2012 All rights reserved ISO 26871:2012(E) 3.3 S ymbols A Ampere F Force F D Inertial resistance force F L Deliverable output force g Standard surface gravity (9,806 65 m/s 2 ) h Drop height (m) He Helium I F Inertial force I T Inertial torque K E Explosive factor K LD Local design factor K M

49、Model factor KMP Margin policy factor K P Project factor KO Kick-off K P Project factor M Mass of drop weight (kg) scc Square centimetre cubic T Torque T D Inertial resistance torque T L Deliverable output torque V Volt Standard deviation 4 Requirements 4.1 General 4.1.1 Back gr ound inform ation Since an 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 testing identical items. Test results and theoretical