1、AIAA S-113A-2016 AIAA S-113A-2016 Standard Criteria for Explosive Systems and Devices on Space and Launch Vehicles Sponsored by American Institute of Aeronautics and Astronautics Approved 17 October 2016 Abstract This standard establishes criteria for design, manufacture, and performance certificati
2、on of explosive systems and explosive devices commonly used on launch, upper stage, and space vehicle systems. The requirements contained in this specification are intended to serve as a universal set of tools for use by explosive system manufacturers and users during all phases of development and c
3、ertification. This information may also be used for guidance during preparation of acquisition contracts and program-specific documents, and may be used for explosive system applications unrelated to space vehicles. AIAA S-113A-2016 ii Contents Contents . ii Foreword . iv Introduction v 1 Scope 6 2
4、Tailoring . 6 3 Applicable Documents . 6 4 Vocabulary . 6 4.1 Acronyms and Abbreviated Terms 6 4.2 Terms and Definitions . 8 5 Design Requirements . 12 5.1 General Requirements . 13 5.2 Margin Requirements 20 5.3 System Design Requirements 23 5.4 Component Design Requirements 30 5.5 Operations and M
5、aintenance 41 6 Verification Requirements . 43 6.1 General 43 6.2 Margin Verification 49 6.3 Functional Test Requirements . 53 A.1 Nondestructive Inspections and Test 67 A.2 Destructive and Environmental Tests 90 A.3 AllFire/NoFire Test and Analysis Methods 118 A.4 Seal Effectiveness 126 A.5 Aerospa
6、ce Leak Test Requirements 129 Figures Figure 1 Explosive System Flow Diagram . 13 Figure 2 Acceptable Explosive Transfer Modes . 29 Figure B.1 Representative Thermal Time Constant Test Data (ref. AIAA20035139 Figure 10, Copyright, AIAA) . 74 Figure C.1 Comparison of the Variation in Estimates of the
7、 Standard Deviation 121 Figure C.2 5% and 95% Estimates of the Relative Standard Deviation 122 Figure C.3 Comparison of Confidence Likelihood Ratio vs ASENT . 125 Tables Table 1 Test Tolerances 48 Table A.1 First Element Nondestructive Acceptance Tests 56 Table A.2 Safe and Arm Acceptance Tests . 57
8、 Table A.3 Other Device Nondestructive Acceptance Tests 58 Table A.4 EED, EFI, SCB, EBW, LID Destructive Qualification Tests . 59 Table A.5 Electromechanical S therefore, users are encouraged to consider tailoring these criteria to best fit individual applications. However, the tailored requirements
9、 shall achieve a level of verification equivalent to the baseline described herein. Rationale for each tailored requirement shall be established. If the requirements in this specification are not tailored by a contract, they stand as written. 3 Applicable Documents The following applicable documents
10、 contain provisions that, through reference in this text, constitute provisions of this standard. In the event of conflict between the text of this document and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and
11、regulations unless a specific exemption has been obtained. AIAA-2005-4039 Advanced Applications of Statistical Methods in Testing of Energetic Components and Systems AIAA-2007-5135 Practical Problems and Solutions in Age Trend-Line Analyses for Energetic Components AIAA-2007-5138 Correlation Between
12、 the Accelerated Aging Test (AAT) and Real World Storage Temperature AIAA S-114 Moving Mechanical Assemblies for Space and Launch Vehicles CFR, Title 49 Code of Federal Regulations, Transportation MIL-D-23615 Design and Evaluation of Cartridge Actuated Devices MIL-STD-810 Environmental Engineering C
13、onsiderations and Laboratory Tests RCC 319-14 Flight Termination Systems Commonality Standard 4 Vocabulary 4.1 Acronyms and Abbreviated Terms CAD Cartridge Actuated Device CDC Confined Detonating Cord AIAA S-113A-2016 7 CSC Conical Shaped Charge EBW Exploding Bridgewire Device EED Electro-Explosive
14、Device EFI Exploding Foil Initiator EFP Explosively Formed Projectile EMC Electromagnetic Compatibility EMI Electromagnetic Interference ESD Electrostatic Discharge ET Explosive Train ETA Explosive Transfer Assembly FCDC Flexible Confined Detonating Cord FLSC Flexible Linear Shaped Charge GRMS Root
15、Mean Square Average Acceleration in Units of Gravity HBW Hot Bridgewire Device HE High Explosive HNS Hexanitrostilbene HVD High Voltage Detonator HVI High Voltage Initiator LFU Laser Firing Unit LID Laser Initiated Device LPI Lanyard Pull Initiator LSCA Linear Shaped Charge Assembly MDF Mild Detonat
16、ing Fuse MPE Maximum Predicted Environment MSDS Material Safety Data Sheet NDT Non-Destructive Tests NSI NASA Standard Initiator OTDR Optical Time Domain Reflectometry PAD Propellant Actuated Device RF/I Radio Frequency/Interference S the system includes detonating cord in a ductile metal tube and a
17、 structure containing geometrically controlled stress risers Exploding Bridgewire Device (EBW) high voltage device in which the bridgewire explodes when functioned Exploding Foil Initiator (EFI) high voltage device that generates a supersonic flyer plate when functioned Explosion exothermic chemical
18、 reaction resulting in a sudden conversion of potential energy into kinetic energy, heat, light, sound, and gas Explosive material which is capable of undergoing an explosion Explosive Train (ET) series of explosive components that transfer explosive signal from the first element to the final explos
19、ively actuated device Explosive Transfer Assembly (ETA) series of explosive components used to transfer the explosive signal from the first element to the explosively actuated device Explosively Actuated Device device that converts explosive energy into mechanical work Explosively Formed Projectile
20、(EFP) variant on the conical shaped charge in which the concave metallic liner is formed into a slug when detonated First Element initial element of an explosive system that converts electrical, optical, or mechanical energy to explosive energy Flexible Confined Detonating Cord (FCDC) CDC whose over
21、-wrap material allows for flexure of the cord for ease in handling and installation AIAA S-113A-2016 10 Flexible Linear Shaped Charge (FLSC) LSC with a ductile metal sheath which may be conformed to installation envelope High Explosive any chemical material in which the fuel and oxidizer are contain
22、ed in the same molecule, the decomposition of which is a detonation Hot Bridgewire Device low voltage EED Interrupter similar to S initiator of choice for all NASA applications No Damage an energetic device still meets design and performance requirements after being exposed to a test or environment,
23、 e.g. ESD Percussion method of initiating an explosive reaction by intentional sudden pinching, crushing or otherwise compressing explosive materials, as between a blunt firing pin and an anvil Primary Explosive extremely sensitive explosive material that will detonate in response to normal environm
24、ental stimuli Procuring Authority organization(s) imposing requirements of this document Propellant deflagrating explosive material whose output is essentially gaseous Pyrotechnics mixtures of fuels and oxidizers that can deflagrate Receptor see Acceptor Refurbish to replace components or elements i
25、n an explosive device or system to maintain reliability or extend service life AIAA S-113A-2016 11 Repair to perform work on a non-compliant device which renders it useable but not fully compliant with specification and/or drawing requirements Rework to perform work on a defective device which rende
26、rs it useable and fully compliant with specification and/or drawing requirements Lead explosive charge contained in a can or in pellet form used within a device to transfer a detonation from one point to another Safe and Arm Device (S b. have a stainless steel shell or suitable electrically conducti
27、ve finish; c. complete the shell-to-shell keyway engagement connection before the pins connect; and d. provide for 360 degree shield termination to the back-shell. 5.3.5.2.11.2 Pin Assignment The circuit assignments and isolation of pins within any electro-explosive system circuit connector shall be
28、 such that any single short circuit occurring as a result of a bent pin or contamination will not result in more than 10 milliamps applied to any EED. There shall be only one wire per pin, and in no case shall a connector pin be used as a terminal or tie-point for multiple connections. AIAA S-113A-2
29、016 26 Spare pins are prohibited in connectors that are part of firing output circuitry. Connectors that source power to an EED shall be of the recessed-socket type and connectors containing circuits that lead to the EED should be of the scoop-proof pin type. 5.3.5.2.11.3 Locking Connectors shall be
30、 selected so that they are not subject to de-mating when exposed to the maximum qualification environments. 5.3.5.2.11.4 Mismating Firing circuit connectors shall not be capable of being mismated. 5.3.5.2.11.5 Separate Connectors Where redundant circuits are required to meet fault tolerance requirem
31、ents, separate output connectors shall be used. 5.3.5.2.12 Firing Switches and Relays Electromechanical and solid state switches and relays shall be capable of delivering the maximum firing circuit current for a time interval at least 10 times the duration of the maximum firing pulse. These switches
32、 and relays shall be capable of sustaining the post-fire short circuit current without exceeding any steady state or transient limits of the solid state or electromechanical device used. The use of a solid-state device to provide isolation between the firing circuit and ground/structure requires spe
33、cific approval from the procuring authority. Relays that are series inhibits shall be mounted on axes to minimize the potential of vibration or shock activating more than one of the relays simultaneously. 5.3.5.2.13 Insulation Resistance All current carrying components and conductors shall be electr
34、ically insulated from each other and system ground. The insulation resistance between all insulated parts shall be greater than 2 megohms for low-voltage EEDs or 20 megohms for high-voltage EEDs. 5.3.5.2.14 Post-Fire Short Circuit Protection Electro-explosive systems shall include positive protectio
35、n from line-to-line and line-to-ground shorts that may develop within a fired EED. The system shall be designed to open firing switches after firing in a specified time, incorporated with current limiting serial resistor, or shall incorporate an EED with a specified minimum open circuit resistance a
36、fter firing. 5.3.5.2.15 Safe and Arm Plug Device Firing circuits that use arming plugs shall be designed to electrically interrupt the EED side of the firing circuit. They shall provide for the ESD protection of the EED with the arm plug removed. This protection may be achieved by installing a safe
37、plug in the arm plug receptacle or by intrinsic design of the firing circuits. If a safe plug is not required, a suitable conductive cap shall cover the arm plug receptacle. Arm and safe plugs or caps shall be designed to be positively identifiable by color, shape and name. The natural (unpainted) b
38、ody color of the arm plug is required. The safe plug or cap should be green and shall have a red “REMOVE BEFORE FLIGHT“ streamer attached. They shall be marked “ARM and “SAFE,” respectively. AIAA S-113A-2016 27 The design of the device and the firing circuit shall ensure easy access for plug install
39、ation and removal during assembly and checkout in all pre-launch and post-launch facilities. Monitor and control circuits shall not be routed through safe plugs. 5.3.5.3 Low Energy Electrical System Low energy electrical systems, which have a power source based on either battery, dedicated power bus
40、, or a capacitor, shall be designed such that the amplitude and duration of the firing current or voltage meet the margin requirements of Section 5.2. Maximum system output shall be less than maximum level at which the device is verified to perform acceptably. During system power on and power off ch
41、ecks, during all switching operations, during system exposure to range electromagnetic/RF energy, and considering bent pins in connectors, the maximum voltage/current applied to the EED shall be verified to be limited to no more than 10 milliamps. Electrical circuit designs used for power, command,
42、and control of the ignition system should be fail-safe and have validated an ability to prevent premature EED activation. The circuitry should preclude narrow band high-amplitude energy pulses near EED ignition thresholds during all switching operations. Measurements during switching operations shou
43、ld be made as part of system validation. 5.3.5.4 High Energy Electrical System This type of initiation system uses a capacitive discharge source with voltage greater than 500 V to initiate EBW devices and EFI devices. For this type of system, minimum system capacitor energy shall meet the margin req
44、uirements of Section 5.2; maximum system capacitor energy shall be less than maximum level at which the device is verified to perform acceptably. Peak current and rise time associated with the laboratory firing setup shall be within 25% of those for the flight/operational system. Power, command, and
45、 control circuits of the initiation system shall be failsafe and shall have a validated ability to prevent premature device initiation. A safety device shall provide a positive interruption of the capacitor charging circuit and the trigger circuit. In addition, a redundant provision capable of gradu
46、ally discharging the firing system capacitor circuit shall be provided. Devices in these systems shall not function when subjected to a 500 V input from a 0.1 F -0% +20% capacitor, across input electrical conductors of the EED. Devices in these systems shall not function when subjected to a 500 VDC
47、applied across input electrical conductors for 5 minutes minimum. Devices in these systems shall not function when subjected to 250 VAC applied across input electrical conductors for 5 minutes minimum. 5.3.5.5 Optical This type of initiation system uses laser energy to initiate the LID. The minimum
48、system energy level shall meet the requirements of Section 5.2; maximum system output shall be less than maximum level at which the device is verified to perform acceptably. The laser used in the system shall produce a pulse intensity and duration at least as great as that used to determine the devi
49、ce threshold level. The optical interface with the fiber optic cable shall be designed to minimize the alignment loss and to protect against dust and moisture contamination. Each lot of fiber shall be lot accepted to verify light transmission during and following exposure to environments. The fiber optic cable attaching to the LID shall be capable of surviving the same environmental exposures as the device itself. AIAA S-113A-2016 28 Power, command, and control circuits of the initiation system shall be fail-safe and shall have a validated ability to prevent prem
