NAVY MIL-STD-1290 A-1988 LIGHT FIXED AND ROTARY-WING AIRCRAFT CRASH RESISTANCE [Superseded By AIR FORCE JSSG 2010-7 VALID NOTICE 1 AIR FORCE JSSG 2010-7]《轻型固定和旋转翼飞机坠毁阻力 取代空军JSSG-20.pdf
《NAVY MIL-STD-1290 A-1988 LIGHT FIXED AND ROTARY-WING AIRCRAFT CRASH RESISTANCE [Superseded By AIR FORCE JSSG 2010-7 VALID NOTICE 1 AIR FORCE JSSG 2010-7]《轻型固定和旋转翼飞机坠毁阻力 取代空军JSSG-20.pdf》由会员分享,可在线阅读,更多相关《NAVY MIL-STD-1290 A-1988 LIGHT FIXED AND ROTARY-WING AIRCRAFT CRASH RESISTANCE [Superseded By AIR FORCE JSSG 2010-7 VALID NOTICE 1 AIR FORCE JSSG 2010-7]《轻型固定和旋转翼飞机坠毁阻力 取代空军JSSG-20.pdf(46页珍藏版)》请在麦多课文档分享上搜索。
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
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