1、MIL-STD-1270A 15 79777LL 00302L17 2 c - /S-W e- /s-ac MIL-STD- 129 OA (AV) 26 September 1988 Superseding 25 January 1974 MIL-STD- 1290 (AV) MILITARY STANDARD LIGHT FIXED AND ROTARY-WING AIRCRAFT CRASH RESISTANCE AMSC Code NIA FSC 15GP DISTRIBUTION STATEMENT A: Approved for public release; distributi
2、on is unlimited - THIS DOCUMENT CONTAINS y, PAGES. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-127O 15 9 777FF713 0030ZY8 Y 9 MIL-STD-l29OA(AV) DEPARTMENT OF DEFENSE WASHINGTON, DC 20301 Light Fixed and Rotary-wing Aircraft Crash Resistan
3、ce 1, of the Department: of Defense. 2. Beneficial comments (recommendations, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Commander, U.S. Army Aviation Systems Command ATTN: AMSAV-ELSS, 4300 Goodfellow Boulevard, St, Louis, MO 6
4、3120-1798, by using the self addressed Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. This military standard Is approved for use by all Departments and Agencies i Provided by IHSNot for ResaleNo reproduction or networking permitted wi
5、thout license from IHS-,-,-MIL-STD-1290A (AV) T FOREWORD This military standard was prepared by the Safety and Survivability O Technical Area of the Aeronautical Systems Division, Aviation Applied Technology Directorate, US Army Research and Technology Activity (AVSCOM), Fort Eustis, Virginia 23604-
6、5577. A major portion of the document is the product of extensive research in aircraft crash resistance sponsored by this laboratory over the past 23 years. The document is based largely on the design criteria of USARTL TR 79-22 A thru E “Aircraft Crash Survival Design Guide. I iii Provided by IHSNo
7、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-11270A 115 W 47797311 0030250 2 Paragraph 1 l. 1 1.2 2 2.1 2.1. 1 2.1.2 2.2 3. 3.1 3.2 3.3 3.4 3.5 3.6 3.7 3.8 3.9 3.10 3.10.1 3.10.2 3.10.3 3.11 3.12 3.13 3.14 3.15 3.16 3.17 3.18 3.19 3.20 3.21 3.22 3.23 3.24
8、3.25 3.26 3.27 MIL-STD-1290A (AV) C QNTENT S Page 1 1 1 1 1 1 1 2 2 2 2 2 2 2 2 2 2 2 3 3 3 3 3 3 3 3 3 3 3 3 3 4 4 4 4 4 4 4 4 iv Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1270A 15 = 77777L1 0030251 4 Paragraph 3.28 3.29 3.30 . 3.31 3.
9、32 3.33 3.34 4. 4.1 4.2 4.3 4.4 4.5 5. 5.1 5.1.1 5.1.1.1 5.1.1.2 5.1.1.3 5.1.1.4 5.1.2 5.1.2.1 5.1.2.2 5.1.3 5.1.4 5.1.5 5.1.6 5.1.7 5.1.8 5.1.8.1 5.1.8.2 5.2 5.2.1 5.2.1.1 5.2.1.2 5.2.2 5.2.2.1 5.2.2.2 5.2.2.3 5.2.2.4 5.2.2.5 MIL-STD-1290A (AV) Page 4 4 5 5 5 5 5 5 5 5 5 6 6 6 6 7 7 7 7 8 8 8 8 8 8
10、 9 9 9 10 10 10 11 11 11 11 11 11 11 12 12 12 V Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-129OA 15 m 499441L 0030252 b m MIL-STD-1290A (AV) i Page 5.2.3.2 5.2.3.3 5.2.3.4 5.2.3.5 5.3 5.3.1 5.3.2 5.3.2.2 5.3.2.3 5.3.201 5.4 5.5 5.5.1 5.5
11、.1.1 5.5.1.2 5.5.1.4 5.5.1.5 5.5.1.6 5.5.1.7 5.5.1.9 5.5.1.10 5.5.2 5.5.2.1 5.5.2.2 5.5.2.3 5.5.3 5.5.3.1 5.5.3.2 5.5.4 5.5.1.3 5.5.1.8 13 13 13 13 14 14 14 14 14 14 15 15 15 15 18 19 19 19 19 20 20 20 20 20 21 22 22 22 22 23 23 6 NOTES 6.1 Changes from previous issues- 23 FIGURES Figure 1 Aircraft
12、coordinates and attitude directions- 27 2 Roll and pitch attitude envelope- 28 3 Low angle impact design conditions- 29 vi Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1270A 15 I 7997711 0030253 I MIL-STD-1290A (AV) Figure 4 5 6 Tab le I I
13、I III IV 7 8 9 10 A- 1 Rollover, side impact design condition- Rollover, roof impact design condition- Stress-strain properties for padding material for head Pedal geometry to prevent entrapment of feet- Cargo lateral load-displacement requirements- Forward load-displacement for energy-absorbing car
14、go contact- restraint- Frangible bolt attachment- Static tests for self-sealing breakaway valves- TABLES Crash impact design conditions, with landing gear extended Minimum loads for standard hose and hose-end fittings Minimum loads for self-sealing hose and hose end fittings Minimum loads for self-s
15、ealing hose with flanged hose-end fittings APPENDIX Appendix A Test Methods, PAGE 30 31 32 33 34 35 36 39 Page 6 24 25 26 37 vii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3270A 35 7777733 003025Li T W MIL-STD-1290A (AV) 1. SCOPE 1.1 Pur
16、pose. This document establishes minimum crash resistance criteria for implementation in the initial stages of aircraft system design. 1.2 Classification, The requirements of this specification pertain to the following aircraft types: Type I - Light Fixed-Wing Type II - Rotary-wing, including Tilt Pr
17、op/Rotor Aircraft 2. REFERENCED DOCUMENTS 2.1 Government documents. 2.1.1 Specifications, standards, and handbooks.- Unless otherwise specified, the following specifications, standards, and handbooks of the issue listed in that issue of the Department of Defense Index of Specifications and Standards
18、 (DoDISS) specified in the solicitation form a part of this standard to the extent specified herein. SPECIFICATIONS MILITARY MIL-H- 25579 Hose Assembly, Tetrafluorethylene, High Temperature, Medium Pressure, General Requirements for MIL-T-27422 Tank, Fuel, Crash-Resistant, Aircraft MIL-H-38360 Hose
19、Assembly, Tetrafluroethylene High Temperature, High Pressure, Hydraulic and Pneumatic Aircraft, General Specification for Hydrocarbon Base, Aircraft Medium Pressure, General Specification General Specification for MIL-S-58095 Seat System: Crash Resistant, Non-Ejection, MIL-H-83282 Hydraulic Fluid, F
20、ire Resistant, Synthetic MIL-H-83796 Hose Assembly, Rubber, Lightweight MIL-S-85510 Seats, Helicopter Cabin, Crashworthy, 2.1.2 Other Government documents, drawings, and publications. The following other Government documents, drawings, and publications form a part of.this standard to the extent spec
21、ified herein. Federal Aviation Administration FAR NO. 25.853 (b) NOPRM 13036 Flammability requirements 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-3290A 15 W 9999433 0030255 3 9 . MIL-STD-129OA (AV) (Copies of specifications, standards,
22、 handbooks, drawings, publications, and other Government documents required by contractors in connection with specific acquisition functions should be obtained from the contracting activity or as directed by the contracting activity.) TECHNICAL REPORT USARTL 79-22 A Aircraft Crash Survival through -
23、22E Design Guide (Application for copies should be addressed to the US Army Aviation Applied Technology Directorate (AVSCOM), ATTN: SAVRT-TY-ASV, Ft Eustis, VA 23604-5577 2.2 Order of precedence. In the event of a conflict between the text of this standard and the references cited herein, the text o
24、f this standard shall take precedence. 3 . DEFINITIONS 3.1 - Abrupt accelerations. Accelerations of short duration, associated with crash impacts, ejection seat shocks, capsule impacts, etc. 3.2 Aircraft crashworthiness. tain 8 protective shell around occupants during a crash and minimize accelerati
25、ons applied to the occupiable portion of the aircraft during crash impacts . The ability of an airframe structure to main- 3.3 Ancillary equipment. Removable emergency survival, personal, or other equipment carried in the aircraft that could constitute a personnel survival hazard if unrestrained dur
26、ing a crash. 3.4 Collapse. 108s of useful load-carrying ability or useful volume. Plastic deformation or fracture of structure to the point of 3,s Deceleration. Acceleration in a direction to cause a decrease in velocity. 3.6 Those rigid and semirigid structural members that could trap or injure the
27、 lower extremities to the extent that ones ability to rapidly escape would be compromised. 3.10.3 Tertiary members. Those rigid and semirigid structural members that could cause injury to flailing upper limbs to an extent that could reduce an occupants ability to operate escape hatches or perform es
28、sential tasks. 3.11 Exit closure. Awindow, door, hatch, canopy, or other device used to close, fill, or occupy an exit opening. 3.12 Failure. Loss of functional capability. 3.13 Fire curtain. A baffle made of fire-resistant material that is used to prevent spilled flammable fluids and/or flames from
29、 reaching ignition sources or occupiable area. 3.14 Fire resistant. Material able to resist flame penetration for 5 minutes when subjected to 2000F flame and still be able to met its intended function(s). O 3.15 Firewall. of 15 minutes without flame penetration. A partition capable of withstanding 2
30、000F flame for a period 3.16 Flammable fluids. Fluids that ignite readily in air, such as hydrocarbon fuels and lubricants. 3.17 Flow diverter. A physical barrier that interrupts or diverts the flow of a liquid. 3.18 Frangible attachment. An attachment possessing a part that is constructed to fail a
31、t a predetermined location and/or load. 3.19 G. The ratio of a particular acceleration (a) to t e acceleration (g) due togravitational attraction at sea level (32.2 ft/sec ), G=a/g. respect to the crash environment, unless otherwise specified, all values of G are those at a point approximately at th
32、e center of the floor of the fuselage. To fllustrate, it is customarily understood that a value of G equal to 5 repre- sents an acceleration of 5 x 32.2, or 161 ft/sec . 9 With 2 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-flIL-STD-LZOA 15 U LL
33、 00302i57 5 MIL-STD-1290A (AV) = (Initial velocity)2 - (Final velocity) 2 3.20 Gav .g 2 x 32.2 x S where Gav velocity Ehange over the distance S, and is expresse multiples of gravitational acceleration (32.2 ft/sec ), is the average acceleration causing the indicated f! in 3.21 Impact area. terrain
34、during a crash. In helicopters, rotor-blade impact on other portions o the aircraft must also be considered. That part of an aircraft which encounters an object or 3.22 Incapacitated. to injury, Unable to extricate oneself from a crashed aircraft due 3.23 Load limiter. value, a deformation distance
35、without significant elastic rebound. A device to limit the loads in a structure to a preselected These devices absorb energy by providing a resistive force applied over 3.24 Major impact. forces are experienced and the most damage is sustained by the fuselage. major impact might not be the initial i
36、mpact. Impact which occurs when the majority of the decelerative The 3,25 Occupant acceleration environment. The direction, rate of onset, magni- tude, and duration of impact acceleration sustained by an occupant, tolerance to impact accelerations is defined in USARTL TR 79-22B. Human 3.26 Postcrash
37、 hazard. The threat to occupant survival posed by fire, smoke, toxic gases, drowning, exposure, etc., following the impact sequence, 3.27 Rate of onset. The instantaneous rate of change of acceleration, i,e., 3 ds dt3 - where s and t denote distance and time. calculated as average rate of change of
38、acceleration over some finite length of time ie., This parameter is more commonly a/ t, where a denotes acceleration. 3,28 Retention strength, The strength of the linkages restraining occupants, cargo, or equipment. 3.29 Self-sealing breakaway valve. A fluid-carrying line or tank connection which wi
39、ll separate at a predetermined load and seal at both ends with a minimum loss of fluid. 3,3Q Static strength. structural failure, often expressed in terms of ultimate static load factors, The maximum static load which can be sustained without 4 Provided by IHSNot for ResaleNo reproduction or network
40、ing permitted without license from IHS-,-,-MIL-STD-1290A (AV) 3.31 Strike envelope. within the flailing envelope of extended body parts. The area surrounding a restrained occupant which is 3.32 Structural deformation. The bending, displacing, tearing and/or collapse of aircraft structure that occurs
41、 during a crash. 3.33 Structural integrity. The ability of a structure to sustain crash loads without collapse, failure, or deformation of sufficient magnitude to cause injury to personnel, 3.34 Survivable accident. An accident in which the forces transmitted to the occupant through the seat and res
42、traint system do not exceed the limits of human tolerance to abrupt accelerations and in which the structure in the occupants immediate environment remains substantially intact to the extent that a livable volume is provided for the occupants throughout the crash sequence. 4. GENERAL REQUIREMENTS 4.
43、1 System crash resistance. Aircraft systems covered by this standard shall be designed to prevent occupant fatalities and to minimize the number and severity of injuries during crash impacts of the severity given in 4.2 while minimizing, to the maximum extent practical, aircraft damage. This shall b
44、e achieved by selecting the most effective mix of the crash resistance factors cited in 4.3 and by applying the requirements of Section 5. The designer must exercise judgement in choosing the extent of compliance with each factor based on consideration of c.omponent capabilities. For example, the in
45、dividual energy attenuation provided by the landing gear, structure and seats may be adjusted to achieve the desired system crash response by using a system analysis approach. 4.2 Design impact conditions. Design impact velocity changes which represent compromise crashworthiness levels derived from
46、consideration of crash statistics, human tolerance5 and system cost, weight and performance are presented in Table I, are defined in more detail in 5.1.1 through 5.1.7. 4.3 General crash survivability design factors. Probability of occupant sur- vival during crash impacts will be enhanced by inclusi
47、on of the following general crash survivability design factors during the initial design stages of the aircraft system: a. Airframe protective shell b. High mass .component, equipment and cargo retention strength c. Occupant acceleration environment d. Occupant environment hazards e. Postcrash hazar
48、ds USARTL TR 79-228 through E shall be used as a guide in the incorporation of these general crash survivability design factors. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1290A 15 9999933 0030Z59 9 W MIL-STD-129OA (AV) TABLE I. Crash impact design conditions, with landing gear exte
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