AIR FORCE MIL-HDBK-336-2-1983 SURVIVABILITY AIRCRAFT NONNUCLEAR AIRFRAME-VOLUME 2《机身-第2卷飞机非核生存力》.pdf

1、MIL-HDBK-336-2 21 September 1983 MIILITA.RY HANDBOOK SURVIVABILITY, AIRCRAFT, NONNUCLEAR, AIRFRAME-VOLUME 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-336 -2 MI m 7977770 0050772 5 m MIL-HDBK-336-2 DEPARTMENT OF DEFENSE WASHINGTON 25, D

2、C MIL-HDBK-336-2 . Military Handbook for Military Aircraft Nonnuclear Survivability 1. This standardizaTion handbook was developed by the Department of De- fense with the assistance of the Air Force Wright Aeronautical Laboratories (AJWAL/FIE) in accordance with established procedure. 2. This public

3、ation was approved on for printing and inclusion in the military standardization handbook series. 3. This document provides basic and fundamental information on military aircraft survivability design requirements and assessment methodology. It will provide valuable information and guidance to person

4、nel concerned with the de- . sign and assessment of military aircraft. The handbook is not intended to be referenced in purchase specifications except for informal purposes, nor shall it supersede any specification requirements. 4. Every effort has been made to reflect the latest information on mili

5、- tary aircraft design techniques and assessment methodology. It is the intent to review.this handbook periodically to insure its completeness and currency. Users of this document are encouraged to report any errors discovered and any recommendations for changes or inclusions to Air Force Systems Co

6、mmand, Attn: ASD/ENESS, Wright-Patterson Air Force Base, Ohio 45433. ii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-336 -2 MI U 7777770 0050793 7 U - MIL-HDBK-336-2 FOREWORD 1. This is a four volume bfilitary Handbook. The titles of the

7、four volumes are : a, Volume 1 - Survivability, Aircraft Nonnuclear, General Criteria b. Volume 2 - .Survivability, Aircraft Nonnuclear, Airframe c, Volume 3 - Survivability, Aircraft Nonnuclear, Engine d. Volume 4 - Survivability, Aircraft Nonnuclear, Classified, General Criteria The information co

8、ntained in volumes 1, 2, and 3 is unclassified to permit greater utilization and accessibility to the user. In .areas where classified data is applicable, it has been incorporated inro voluine 4, and is referenced as such in the text of each volume. 2. This handbook has been prepared to provide mili

9、tary planners and industry with the information and guidance needed for the conceptual and detail design of the new aircraft where nonnuclear-survivability enhancement is- to be inte- grated into the system. It is also structured to provide data and guidance for the incorporation of survivability-en

10、hancement features into existing aircraft systems as a retrofit modification. Both fixed and rotary wing aircraft design information are contained in this publication, Figure 1 illustrates the -role of this handbookin.the design process, It is a task-flow diagram of the major elements involved in th

11、e development of new aircraft. The system requirements are initiated by the using command that defines the operational requirements and capabilities desired to perforin specific combt missions. These require- ments are studied by the appropriate service agencies in the form of conceptual (Phase O) d

12、esign analyses. The optimum mission and performance pararheters are defined, along with system/cost effectiveness comparisions of candidate concep- tual design candidates. This is accomplished through an analysis to identify the mission-essential functions that must be performed in order to accompli

13、sh the specific mission obj.ectives. With these functions defined, an analysis is conducted to identify the subsystem-essential functions that must be provided to perform the mission-essential functions. At the same time, an analysis is conducted to identify.the hostile threat systems.to which the a

14、ircraft system may be expected during the conduct of its operational mission, The results of these analyses are then used by the S/V engineer to conduct an evaluation of the various candidate survivability-enhancement techniques that may be used in the design concepts. This design handbook will be t

15、he basic source for identi- fleation f the basic principles and techniques that may be employed, It will algo provide references to other information sources for more detailed and/or specialized data. The results of this analysis are summarized into recommenda- tions for the development. of candidat

16、e conceptual aircraft des thus rejected. The need for lightweight armor led to the development in 1943 of fiberglass bonded into a-laminate and called DoroIL, after Col; G.F, Doriot. Most of the body armor of WW II was Doron Type 2. The introduction and use of flak suits reduced casualties from 6.58

17、 wounds per 1,000-man sorties to 2.29 wounds per 1,000-man sorties in 1943-44. None of the armor of this period was effective against API bullets, however. The aluminum nylon M12 vest was developed as an improvement over Doron and was field-tested in Korea, An all-nylon vest consisting of 12 layers

18、of 2 x 2-inch basketweave nylon also developed was. attractive because of its flexibility and effectiveness against mortar and shell fragments. Flat plate armored glass was incorporated into the windshields of combat aircraft as an added protection for the crew. Self-seal- ing fuel bladders and line

19、s were developed for bomber and fighter aircraft during World War II and were credited with saving many of these systems. Some attention was also directed to the suppression of fuel fires in bomber aircraft. Balsa wood was installed around some of the voids in wing fuel tanks Eo prevent fuel leakage

20、 fires in those areas. The British experimented with fire extinguishing systems in the fuel tank areas of some of their multiengine aircraft. Consider- able research on specific problems of aircraft protection and vulnerability was conducted during the war, with particular attention being directed t

21、o penetration of materials-by bullets and fragments, and the effect of blast on aircraft struc- tures. In 1948, the First Working Conference on Aircraft Vulnerability was held the U.3. Army Ballistic Research Laboratory at the Aberdeen Proving Grounds, .b$ryland. The participants were recognized exp

22、erts from the Air Force Air Material Command, the Army Ballistic Research Laboratory, Johns Hopkins Univer- sity Applied Physics Laboratory, University of Chicago Ordnance Research, General Electric- Engine Company, New Mexico School of Mines, the Navy Ordnance Explosive Group, and the Rand Corporat

23、ion. The purpose of this meeting was to define the problem of military aircraft vulnerability and to identify the technology re- quired to develop design improvements, Unfortunately, the excellent beginning 6 4.3.2.7 4.3.2.8 4.3.3 4 . 3 3 . 1 4.3.3.2 4.3.3.3 4.3.3.4 4.3.4 4.3.5 MIL-HDBK-336-2 TABLE

24、OF CONTENTS Page SCOPE . 1-1 General 1-1 Application . 1-1 REFERENCED DOC.NTS . 2-1 General . 2-1 Reference by Volume . 2-1 Reference by subject 2-5 Reference by number . 2-16 DEFINITIONS General . GENERAL SURVIVABILITY ENHANCEMENT METHODS . General . Minimized Detection Passive Countermeasures . Ra

25、dar cross-section (RCS) signature . Radar cross-section determination . Echo patterns . .Echo reduction Radar Range Signal.Strength Levels Infrared (IR) signature . Visual signature . Lighting systemsc Aural signature Other detection signatures . Active mission countermeasures . Threat detection RF

26、passive warning and identification RC active warning . IR/optical/ultraviolet (UV) warning Systems for . location of active threat transmitters . ECM/onboard- . RF noise jamming RF deception ja.ing . Infrared jamming Active optical countermeasures . Communications countermeasures . IFF countermeasur

27、es Fuze countermeasures Electronic countermeasures/expendab.le . Chaff . Aerosols Optical and infrared decoys Lethal defense Tactics/performance . Radar cross-section passive scurce reduction Adaptive power management Active expendable countermeasures . 3-1 3-1 4-1 4-1 4-3 4-4 4-5 4-5 4-7 4-8 4-10 4

28、-10 4-10 4-11 4-12 4-12 4-12 4-13 4-13 4-13 4-13 4-14 4-14 4-14 4-14 4-14 4-15 4-k5 4-15 44-5 4-15 4-15 4-15 4-15 4-16 4-16 4-17 4-17 4-17 viii Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-336 -2 NI m 7777770 0050777 B m . MIL-HDBK-336-2

29、TABLE OF CONTENTS (Continued) Sect ion B 4.3.6 4.4 4.4.1 4.4.2 4.4.3 4.4.4 4.4.5 4.4.6 4,4.6.1 4.4.6.2 4.4.7 4.4.8 4.4.9 4.4.10 4.4.10.1 4.4.11 4.5 4.5.1 4;5.1,1 4.5.1.2 4.5.2 4.5.3 4.5.4 5 . 5.1 5.2 5.2.1 5.2.1.1 5.2.1.2 5.2.1.3 5.2.1.3.1 5.2.1.3.2 5.2.1.4 5.2.1.5 5.2.2 5.2.2.1 5.2.2.2,l 32.2.3 5.2

30、.3 5.2.3.1 5.2,3.1.1 5.2.3.2 5.3 5.3.1 5.3.1.1 5,.2.2.2 “*2.2.2.T;1 Aircraft RF system integration Ballistic laser protection methods Isolation . Damage tolerance . Ballistic resistance Delayed failure . Leakage suppression . Redundancy.separation . Leakage suppression/control; Leakage control Fire/

31、explosion suppression Fail-safe response . Masking/geometry . Armor Protection against high explosive threats . Laser protection methods System operational factors Reparability/maintainability Design criteria procedure Documentation Safety Logistics Reliability . SYSTEM SURVIVABILITY ENHANCEMENT DES

32、IGN General . Configuration design,. Minimized detection Radar cross section . Infrared signatures . Visual detection General provisions. . Rotary wing aircraft . Aural signatures Other detection signa tu res.,.; Passive protection Redundancy/separation . Component concentration and shielding . Shie

33、lding Concentration . Hazardous material . placement/containment Configuration design repairability/maintainability Battle damage repair design concept . Preliminary design Threat aspects and damage mechanisms S.ructures General design considerations . Material selection Page 4-17 4-19 4-19 4-19 4-1

34、9 4-19 4-20 4-20 4-20 4-20 4-20 4-21 4-22 4-22 4-22 4-23 4-25 4-25 4-26 4-26 4-30 4-30 4-30 . 5-1 5-1 5-3 5-3 5-3 5-3 5-4 5-4 5-5 5-5 5-6 5-6 5-6 5-9 5-9 5-10 5-12 5-12 5-12 5-13 5-13 5-15 5-15 5-16 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL

35、-HDBK-336 -2 MI m 9799970 0050800 O m Section 5.3.1.2 5.3.1.2.1 5.3.1.4 5.3.1.5 5.3.2 5.3.2.2 5.3.2.3 5.3.2.4 5.3.2.4.1 5.3.2.4.2 0 5.3.2.462.1 5.3.2.4.2.2 5.3.2.4.2.3 5.3.2.4.3 5.3.2.4.3.1 5.3.2.4.3.2 5.3.2.4.3.3 5.3.2.4.3.4 5.3.2.4.3.5 5,3.3 5.4 5.4.1 5.4.1.1 5.4.1.1.1 5,4.1.1.2 5.4.1.1.2.1 5;4.1.

36、1.2.2 5.4.1.1.2.3 5.4.1.1.2.4 5.4.1.1.2.5 5.4.1.1.2.5.1 5.4.1.1.2.5.2 5.4.1.1.2.5.3 5a4a1.1.2o5.4 5.4.1.2 5.4.1.2.1 5.4.1.2.2 5.3.1.3 5.4.1.4 5.4.1.4.1 5.4.1.4.2 5.4.1.4.3 5.4.1.5 5.4.1.5.1 5.4.1.5.1.1 ,5.4.1.5.2 5.4.1.5.2.1 5.3.1.3 5.3.2.1 5.4.1.5.2.2. MIL-HDBK-336-2 TABLE OF CONTENTS (Continued) C

37、onstruction configuration . Design guide . General design repairability/maintaitability . Crashworthiness interrelationships . Material causing secondary hazards . Typical design mthods . Thin skin/stringer construction Sandwich construction Sculptured plate construction Composites . Filaments Lamin

38、a and laminate fabrication Organic matrix composites Metal matrix composites Fiber volume fraction Design concepts and applications . Aircraft applications. structural . Hybrid struture . Selective reinforcement Helicopter applications Propulsion system application HEL protecion . Personnel stations

39、 . Personnel ballistic protection techniques Personnel injury factors . Human vulnerability Secondary weapon effects . Smoke Toxic products . Protection methods Chemical fire hazards . Explosion-suppression systems Pure Air . Toxicities High-thermal conditions . Loss of pressurization . PerBonnel st

40、ation placement /arrangement Multiple crewmembers -a Crashworthiness Control and displays . Secondary hazards External blast wave effect on transparencies . Internal blast effect on transparencies Other secondary hazard considerations Personnel armor Airframe armor . Su.ary Aircrew seat armor Design

41、 factors . Operation inter fer en ce. Page 5-17 5-18 5-18 5-20 5-26 5-26 5-26 5-27 5-28 5-28 5-28 5-29 5-29 5-29 5-29 5-32 5-32 5-33 5-34 5-35 5-37 5-37 5-41 5-41 5-41 5-42 . 5-46 5-46 5-50 5-50 5-52 5-53 5-53 5-53 5-53 5-53 5-53 5-54 5-59 5-9- 5-56 5-56 5-56 5-59 5-61 5-61 5-65 5-67 5-67 5-68 X Pro

42、vided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-HDBK-336-2 TABLE OF CONTENTS (Continued) Section 5.4.1.5.2.3 5.4.1.5.2.4 5.4.1.5.3 5.4.1.5.3.1 5.4.1.5.3.2 5.4.1.5.3.3 5.4.2 5.4.3 5.5 5.5.1 5.5.1.1 5.5.1.2 5.5.1.2.1 5.5.1.2.1.1 5.5.1.2.1.2 5.5.1.3 5.

43、5.1.3.1 5.5.1.3.2 5.5.2 5.5.2.1 5.5.2.2 5.5.2.3 5.5.3 5.5.3.1 5.5.3.1.1 5.5.3.1.2 5.5.3.1.3 5.5.3.1.4 5.5.3.1.5 5.5.3.1.6 5.5.3.2 5.5.3.2.1 5.5.3.2.2 5.5.3.2.3 5.5.3.3 5.5.3.3.1 5.5.3.3.2 5.5.3.3.2.1 5.5.3.3.2.1.1 $.5.3.2.1.2 i 58.5.3.4 5.5.3.5 5.5.3.5.1 5.5,3.5.1.1 5.5.3.5.1.2.1 5.5.3.5.1.2.2 5.5.3

44、.5.1.2.3 5.5b3.5.1.2 Experimental sea . Current types . Body armor . Low-performance aircraft Types of body armor . Available design information . Personnel HEL protection Personnel stations reliability/maintainbility Hydrocarbon fuel characteristics Flash point and autogenous ignition . Flammabilit

45、y Fuel systems Flammability limits . Lean limit Gunfire . Dynamic factors . Primary responses . Fuel system secondary weapons effects . Failure modes,. Combat failure modes Weapon effects Secondary damage mechanisms . System layout/design . Tankage arrangement . Fuel management systems . Fuel gaging

46、 systems . Fuel flow management Tank geometry/cosure . Critcal element protection Ballistic mask . Hydrodynamic ram protection . Structural response . Honeycomb construction Peak pressure . Self-sealing . Cell cons.ruction . Cell design criteria Fuel cell backb0a.d . High-modulus backboards . Blast

47、protection Additionai concepts . Ullage protection Reticulazed polyurethane foam (Reference 261). Voided foal explosion suppression concept . Fifty percent void Model assumption Hydrocarbons combustion . Dynamic model . Fully packed foam explosion protection concept InLegral wing fuel tank design Pa

48、ge . 5.68 5-68 5-72 5-74 5-75 5-75 5-75 5-80 5-83 5-83 5-85 5-85 5-86 5-86 5-88 5-88 5-94 5-P4 5-94 5-94 5-95 5-96 5-96 5-98 5- 10 1 5-10 1 5- 10 1 5-10 1 5-103 5- 103 5-10 3 5-104 5-106 5- 10 6 5-106 5-1 13 5-1 13 5-114 5-115 5-116 5-1 16 5-116 5-1 16 5-118 5- 120 5-120 5-121 5-1 2 1 5-121 5-123 xi

49、 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-” MIL-HDBK-336 -2 MI m 7779770 0050802 4 W . MIL-HDBK-336-2 TABLE OF CONTENTS (Continued) Sect ion 5.5 3.5.1. 2.6 Smallintercommunicating holes 5 5.3.5.1. 2.7 Large intercommunicating holes . 5L5.3.5.1.2.8 Current design,.,. 5.5.3.5.1.2.9 Theoretical model .5.5.3.5.1. 2.10 Best overall performance . 5.5.3.5.1.2.11 Integral ty