REG MSFC-SPEC-3635 REV A-2012 Pyrotechnic System Specification.pdf

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1、CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-SPEC-3635A MSFC-SPEC-3635 National Aeronautics and REVISION A Space Administration EFFECTIVE DATE: 10/22/12 George C. Marshall Space Flight Center Marshall Space Fligh

2、t Center, Alabama 35812 EV30 MSFC TECHNICAL STANDARDS PYROTECHNIC SYSTEM SPECIFICATION MEASUREMENT SYSTEM METRIC Approved for Public Release; Distribution is Unlimited Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical Standard EV30 Title

3、: Pyrotechnic System Specification Document No.: MSFC-SPEC-3635 Revision: A Effective Date: 10/22/12 Page 2 of 56 CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-SPEC-3635A DOCUMENT HISTORY LOG Status (Baseline/ Rev

4、ision/ Canceled) Document Revision Effective Date Description Baseline Baseline 12/5/2011 Baseline Release; document authorized through MPMDS Revision A 10/22/2012 Revision A Release; document authorized through MPDMS. Added IPC J-STD-001E-2010 and ICP J-STD-001ES and removed NASA STD 8739.3 Added N

5、ASA-STD-6012 and removed MIL-STD-889 and MSFC-SPEC-250 Sec 1.0: added caveat to be able to use industry, government, and company specifications in lieu of this specification if approved by the responsible NASA technical authority Sec 3.8: updated compatibility analysis exception Sec 3.9.1.5 revised

6、to title to Shielding and updated verbiage to align with MIL-STD-1576 Sec 3.9.1.6: updated Radio Frequency (RF) power limit at the electroexplosive devices (EED) Sec 3.9.2: updated specification for soldering of electrical connections for Safe and Arm Devices Sec 4.3.2 revised to add caveat for perf

7、orming the subsystem separation test only if results cannot be achieved at another level of testing Sec 4.6: updated pyrotechnic component reviews to initial, pre-production and hardware acceptance Appendix A- updated acronyms to add IPC Provided by IHSNot for ResaleNo reproduction or networking per

8、mitted without license from IHS-,-,-MSFC Technical Standard EV30 Title: Pyrotechnic System Specification Document No.: MSFC-SPEC-3635 Revision: A Effective Date: 10/22/12 Page 3 of 56 CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/m

9、ultiprogram/MSFC-SPEC-3635A Table of Contents 1.0 SCOPE . 7 1.1 Purpose . 7 1.2 Applicability 7 2.0 DOCUMENTS . 8 2.1 Applicable Documents 8 3.0 REQUIREMENTS 10 3.1 Safety 10 3.2 Performance 10 3.3 Environments 10 3.4 Failure Tolerance 11 3.5 Design Life . 11 3.6 Range Safety 11 3.7 Sealing 11 3.8 E

10、lectrical/Electromagnetic . 12 3.9 Pyrotechnic Component Design Requirements 12 3.9.1 Electroexplosive Devices (EEDs) . 12 3.9.1.1 Initiation System . 12 3.9.1.2 Bridgewire . 12 3.9.1.3 Shorting and RF Protection . 13 3.9.1.4 Electrostatic Discharge (ESD) 13 3.9.1.5 Shielding . 13 3.9.1.6 Radio Freq

11、uency Interference (RFI) . 13 3.9.1.7 Lightning . 13 3.9.1.8 Bonding . 13 3.9.1.9 Low Voltage EED . 14 3.9.1.9.1 All-Fire/Sure-Fire 14 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical Standard EV30 Title: Pyrotechnic System Specificatio

12、n Document No.: MSFC-SPEC-3635 Revision: A Effective Date: 10/22/12 Page 4 of 56 CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-SPEC-3635A 3.9.1.9.2 No-Fire 14 3.9.1.10 Semiconductor Bridge Device (SCB)/Thin Film B

13、ridge Device (TFB) . 14 3.9.2 Safe and Arm Devices (S however, only one lot of bulk explosive and tube materials shall be used in one lot of LSC. A tube shall be a length of tubing loaded with explosive material before being reduced to the required configuration. LSC charge holders shall be designed

14、 to permit inspection of the standoff or provide dimensional control of the standoff after installation or both. Provisions shall be made to ensure that no contamination enters the LSC apex area after installation into the charge holder or installation of the charge holder into the next higher assem

15、bly. 3.9.6 Frangible Devices Frangible devices have a load carrying web, annulus, or fracture plane such as frangible nuts, separation bolts, and frangible joints. Determination and assessment of fracture critical frangible devices shall be in accordance with NASA-STD-5019, Fracture Control Requirem

16、ents for Spaceflight Hardware. Nondestructive evaluation of frangible devices determined to be fracture critical shall be in accordance with NASA-STD-5009, Nondestructive Evaluation Requirements for Fracture Critical Metallic Components. Frangible devices shall be designed for a minimum yield factor

17、 of safety of 1.1 times the limit load and a design ultimate factor of safety of 1.4 times the limit load. Frangible devices shall have an adequate strength to withstand limit loads without loss of operational capability for the life of the device. 3.9.6.1 Frangible Nuts Performance margin for the f

18、rangible nut shall be performed by function of a production nut with a web thickness 120% greater than the maximum web thickness of the production nut using a nominally loaded cartridge or booster charge. If multiple cartridges or booster charges are used Provided by IHSNot for ResaleNo reproduction

19、 or networking permitted without license from IHS-,-,-MSFC Technical Standard EV30 Title: Pyrotechnic System Specification Document No.: MSFC-SPEC-3635 Revision: A Effective Date: 10/22/12 Page 20 of 56 CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.m

20、sfc.nasa.gov/docs/multiprogram/MSFC-SPEC-3635A to achieve redundancy the margin shall be demonstrated by function of a single cartridge or booster charge. This test shall be performed for each production lot of frangible nuts. 3.9.6.2 Separation Bolts If the separation bolt is a propellant actuated

21、device then the bolt shall be designed to withstand an internal static proof pressure of 1.2 times the maximum operating pressure without deformation or leakage and an internal burst pressure of 1.5 times the maximum operating pressure without structural failure. Design margin for a propellant actua

22、ted separation bolt shall be demonstrated by acceptable performance when functioned with a single pressure cartridge loaded to 80% of the design minimum propellant load weight of the pressure cartridge. If the pressure cartridge design precludes down loading the propellant weight to 80% of the desig

23、n minimum propellant weight then the fracture groove of the separation bolt shall be increased to a minimum of 120% of the design maximum thickness of the fracture groove and functioned with a pressure cartridge with a nominal propellant load to meet the margin requirement. Propellant actuated separ

24、ation bolts with a stroking piston shall be capable of withstanding internal pressures generated in operation with the movable part restrained in its initial position (locked shut) without rupture or the release of shrapnel, debris, or hot gases that could compromise crew safety or mission success.

25、Where applicable, this capability shall be demonstrated with redundant charges operating simultaneously. Design margin for a separation bolt loaded with primary and/or secondary explosives shall be demonstrated by acceptable function when the fracture groove of the separation bolt is increased to a

26、minimum of 120% of the design maximum thickness of the fracture groove. The separation bolt shall demonstrate acceptable performance when functioned with 120% of the pyrotechnic load regardless of whether the separation bolt is propellant actuated or actuated with primary and/or secondary explosives

27、. 3.9.6.3 Frangible Joints (FJ) The frangible joint shall completely sever at the fracture plane and contain combustion by-products upon initiation of the internal pyrotechnic components. The frangible joint shall not produce any secondary fragmentation of the frangible joint upon tube expansion. Fr

28、angible joint design margin shall demonstrate acceptable performance when functioned with a mild detonating fuse (MDF) core load of 80% of the minimum design MDF core load. The frangible joint shall demonstrate acceptable performance, contain all pyrotechnic component combustion by-products and prod

29、uce no secondary fragmentation when functioned with a MDF core load of 120% of the design maximum MDF core load. Using MDF with a design nominal core load the maximum Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical Standard EV30 Title:

30、 Pyrotechnic System Specification Document No.: MSFC-SPEC-3635 Revision: A Effective Date: 10/22/12 Page 21 of 56 CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-SPEC-3635A fracture plane groove thickness that resul

31、ts in complete fracture, without tube rupture or secondary fragment generation, shall be determined. 3.9.7 Cartridge Actuated Devices (CAD)/Propellant Actuated Devices (PAD) Cartridge/propellant actuated devices are pyrotechnically actuated devices that have moving parts and are actuated by the pres

32、sure output from one or more separable pressure cartridges. Examples include thrusters, separation nuts, pin-pullers and pin-pushers, cutters, and pyrovalves. Determination and assessment of fracture critical cartridge actuated devices shall be in accordance with NASA-STD-5019. Nondestructive evalua

33、tion of cartridge actuated devices determined to be fracture critical shall be in accordance with NASA-STD-5009. If the CAD/PAD is designed to carry a load then the CAD/PAD shall be designed for a minimum yield factor of safety of 1.1 times the limit load and a design ultimate factor of safety of 1.

34、4 times the limit load. These devices shall have an adequate strength to withstand limit loads without loss of operational capability for the life of the device. The CAD/PAD shall be capable of withstanding 1.5 times the specified maximum allowable installation torque without physical damage. CADs/P

35、ADs shall be designed to withstand an internal static proof pressure of 1.2 times the maximum operating pressure without deformation or leakage and an internal burst pressure of 1.5 times the maximum operating pressure without structural failure. Design margin for the CAD/PAD shall demonstrate accep

36、table performance when functioned with a single pressure cartridge loaded to 80% of the design minimum pyrotechnic output charge weight. The CAD/PAD shall demonstrate acceptable performance when actuated with a cartridge loaded with 120% of the design maximum output charge weight. If redundant cartr

37、idges are used the maximum energy test shall be performed with both cartridges loaded to 120% of the design maximum cartridge output charge weight. The initiator shall not be used as the sole source of power for the CAD/PAD unless the design margins for minimum and maximum energy specified herein ha

38、ve been demonstrated. CADs/PADs shall be capable of withstanding internal pressures generated in operation with the movable part restrained in its initial position (locked shut) without rupture or the release of shrapnel, debris, or hot gases that could compromise crew safety or mission success. Whe

39、re applicable, this capability shall be demonstrated with redundant charges operating simultaneously. 3.9.8 Through Bulkhead Initiators (TBI) A hydrostatic leak test, in accordance with ASTM E1003, Standard Test Method for Hydrostatic Leak Testing, Pressure Drop Indication Method, shall be performed

40、 on the TBI body to ensure Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical Standard EV30 Title: Pyrotechnic System Specification Document No.: MSFC-SPEC-3635 Revision: A Effective Date: 10/22/12 Page 22 of 56 CHECK THE MASTER LIST - VE

41、RIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-SPEC-3635A bulkhead integrity prior to loading of explosive or pyrotechnic materials. The leak test shall be performed at 1.2 times the maximum operating pressure. Design margin for transfer ac

42、ross the TBI bulkhead shall be performed either by over loading and under loading the charge weights or by increasing the bulkhead thickness or a combination thereof. For demonstrating margin by charge weight the following is applicable. a. The TBI shall be designed to perform acceptably and demonst

43、rate proper transfer across the bulkhead by loading the donor and acceptor charges to a minimum of 120% of the maximum allowable charge weight in each cavity using the force method. There shall be no leakage through the bulkhead after this test. b. The TBI shall demonstrate proper transfer across th

44、e bulkhead when both the donor and acceptor charges are loaded to a maximum of 80% of the minimum design load weight. For demonstrating margin by the bulkhead thickness the following is applicable. a. The TBI shall demonstrate proper transfer across the bulkhead when the bulkhead thickness is increa

45、sed to 120% of the maximum design thickness and the donor and acceptor charges are loaded to nominal charge weights. b. The TBI shall demonstrate proper transfer when the bulkhead thickness is decreased to 80% of the minimum design thickness and the donor and acceptor charges are loaded to the nomin

46、al charge weights. There shall be no leakage through the bulkhead after this test. If the TBI is used as a pressure retaining device then the bulkhead integrity after firing shall be verified. This test shall be performed for each lot of TBIs utilized in pressure retention applications. 3.9.9 Mechan

47、ically Actuated Devices Mechanically actuated devices used in an inadvertent separation destruct system (ISDS) or autonomous flight safety system (AFSS) shall conform to AFSPCMAN 91-710 and NPR 8715.5. Mechanical initiation shall be accomplished by using percussion primers conforming to JSC/SKD26100

48、132, Performance Specification for National Space Transportation System (NSTS) Use of Percussion Primers. The percussion primers shall be certified to this specification prior to installation into the mechanically actuated device. If the mechanically actuated device is a cutter then the cutter shall

49、 demonstrate margin by cutting 120% of the maximum target material thickness. Appropriate protection should be provided to ensure electrical shorting during and after severance if electrical wires are the target material. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical Standard EV30 Title: