NAVY MIL-E-18927 E-1983 ENVIRONMENTAL CONTROL SYSTEMS AIRCRAFT GENERAL REQUIREMENTS FOR《飞机环境控制系统的一般要求》.pdf

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1、MIL-E-18927E(AS)18 August 1983SUPERSEDINGMIL-E-18927D(AS)29 December 1961MILITARY SPECIFICATIONENVIRONMENTAL CONTROL SYSTEMS, AIRCRAFT,GENERAL REQUIREMENTS FORThis specification is approved for use by the Naval Air Systems Command,Department of the Navy, and is available for use by all Departments a

2、ndAgencies of the Department of Defense.1. SCOPE1.1 Scope. This specification establishes the general requirementsfor design and performance of aircraft Environmental Control Systems (ECS)required for occupied spaces and equipment. It includes pressurization,heating, cooling, ventilating, mositure c

3、ontrol, bleed air system, ram airsupply, pressure and anti-G suit systems, defogging, defrosting, anti-icing,rain removal, electronic/electrical equipment environment, boundary layercontrol and related systems.Beneficial comments (recommendations, additions, deletions) andany pertinent data which ma

4、y be of use in improving this document should beaddressed to: Commanding Officer, Naval Air Engineering Center, EngineeringSpecifications and Standards Department (ESSD), (Code 93), Lakehurst, NJ 08733by using the self-addressed Standardization Document Improvement Proposal (DDForm 1426) appearing a

5、t the end of this document or by letter.FSC 1660Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-18927E(AS)2. APPLICABLE DOCUMENTS2.1 Government documents.2.1.1 Specifications, standards, and handbooks. Unless otherwisespecified. the following s

6、pecifications, standards, and handbooks of the issuelisted in that issue of the Department of Defense Index of Specifications andStandards (DoDISS) specified in the solicitation form a part of thisspecification to the extent specified herein.SPECIFICATIONSFederalQQ-C-320QQ-P-416QQ-Z-325Chromium Plat

7、ing (Electrodeposited)Plating, Cadmium (ElectrodepositedZinc Coating, Electrodeposited, Requirements forMilitarySurface Treatments and Inorganic Coatings forMIL-S-5002Metal Surfaces.MIL-I-5099 indicator; Cabin Air Pressure, 1-7/8 Inch Dial,Type MA-1Valves, Safety, Cabin Air, GeneralSpecifications fo

8、rMIL-V-5379MIL-E-5400 Electronic Equipment, Aerospace, General Specifications forMIL-B-5484MIL-T-5842Heater, Aircraft, Combustion TypeTransparent Areas, Anti-Icing, Defrosting, andDefoqging Systems, General Specification forMIL-2-6051 Electromagnetic Compatibility Requirements,SystemsSound and Therm

9、al Insulation for Aircraft;General Specifications for Installation ofMIL-S-6144MIL-P-6855 Rubber; Synthetic, Sheet, Strips, Molded orExtruded ShapesPump Assembly; Fuel, Electrically Driven,Aircraft HeaterMIL-P-6992MIL-E-7080 Electrical Equipment; Aircraft, Selection andInstallation ofMIL-I-7171MIL-F

10、-7179Insulation Blanket; Thermal AcousticalFinishes and Coatings: Protection of AerospaceWeapons Systems, Structures, and Parts, GeneralSpecifications forGages, Pressure, Engine and Utility, AircraftDesign and Installation of Anit-G Suit PressureSystems in Jet Propelled AircraftInterchangeability an

11、d Replaceability ofComponent Parts for Aircraft and MissilesMIL-G-7734MIL-D-7890MIL-I-85002Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-18927E(AS)MIL-A-8625MIL-I-8670MIL-I-8673MIL-D-8706MIL-H-8796MIL-D-8804MIL-D-8806MIL-T-8879MIL-R-9345MIL-T

12、-18606MIL-T-18607MIL-T-23103MIL-A-23121 Cockpit Capsule System; General Specification forMIL-O-27210MIL-C-38999MIL-B-81365MIL-R-81367MIL-B-81592MIL-C-83488STANDARDSMilitaryMIL-STD-143MIL-STD-210MIL-STD-454MIL-STD-461Anodic Coatings, for Aluminum and AluminumAlloysInstallation of Fixed Guns and Assoc

13、iatedEquipment in Naval AircraftInstallation and Test of Aircraft FlexibleWeapons SystemsData and Test, Engineering: ContractRequirements for Aircraft Weapons SystemsHose, Air Duct, Flexible, AircraftDe-Icing System, Pneumatic Boots, Aircraft,General Specification forAcoustical Noise Level in Aircra

14、ft, GeneralSpecification forScrew Threads, Controlled Radius Root withIncreased Minor Diameter; General SpecificationforRegulator, Air Pressure, Aircraft Cabin,General Specification forTest Procedures for Aircraft EnvironmentalSystemsThermal Anti-icing Equipment, Wing-and EmpennageThermal Performanc

15、e Evaluation, AirborneElectronic Equipment and Systems, GeneralRequirement forAircrew Environmental, Escape and SurvivalOxygen, Aviators Breathing, Liquid and GasConnectors, Electrical, Circular, Miniature,High Density, Quick Disconnect EnvironmentResistant, Removable Crimp Contacts, GeneralSpecific

16、ation forBleed Air Systems, General Specification forRain Removal System, Aircraft Windshield, JetAir BlastBleed Air Systems, Load Analysis of, Method forCoating, Aluminum, ION Vapor Deposited.Standards and Specifications, Order ofPrecedence for the Selection ofClimatic Extremes for Military Equipme

17、ntStandard General Requirements for ElectronicEquipmentElectromagnetic Emission SusceptibilityRequirements for the Control of electromagnetic Interface3Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-18927E(AS)MIL-STD-470MIL-STD-704MIL-STD-785M

18、IL-STD-800MIL-STD-810MIL-STD-882MIL-STD-889MIL-STD-1247MIL-STD-1472MIL-STD-2072MS-16051MS-16052MS-33561MS-33562MS-33565MS-33656MS-33740Maintainability Program Requirements (forSystems and Equipments)Aircraft, Electric Power, CharacteristicsReliability Program for Systems and EquipmentDevelopment and

19、 ProductionProcedure for Carbon Monoxide Detection andControl in AircraftEnvironmental Test MethodsSystem Safety Program RequirementsDissimilar MetalsMarking, Functions and Hazard Designations ofHose, Pipe and Tube Lines for Aircraft, Spaceand Missile SystemsHuman Engineering Design Criteria for Mil

20、itarySystems, Equipment and FacilitiesSurvivability, Aircraft, Establishment andConduct of Programs forCoupling, Ground Cooling, Combat Type AircraftAir Inlet, Combat Aircraft, Ground CoolingConnection, Aircraft Ground Air Conditioning,5Inch, Minimum RequirementsConnection, Aircraft Ground Air Condi

21、tioning, 8Inch, Minimum RequirementsConnections Ground Leakage Test, PressurizedCabin, AircraftsFitting End, Standard Dimensions for FlaredTube Connection and Gasket SealNipple, Pneumatic Starting, 3 inch ID, outlinedimensions ofHANDBOOKSMilitaryMIL-HDBK-221 Fire Protection Design Handbook for U.S.

22、NavyAircraft Powered by Turbine Engines(Copies of specifications, standards, handbooks, drawings, and publicationsrequired by manufacturers in connection with specific acquisition functions should be obtained from the contracting activity or as directed by thecontracting officer.)2.1.2 Other Governm

23、ent documents, drawings and publications. Thefollowing other Government documents, drawings, and publications form a part ofthis specification to the extent specified herein.Air Force-Navy AeronauticalAN-929 Cap Assembly, Pressure Seal, Flared Tube Fitting4Provided by IHSNot for ResaleNo reproductio

24、n or networking permitted without license from IHS-,-,-MIL-E-18927E(AS)Air ForceAFOSH Standard 161-8 Permissible Exposure Limits forChemical SubstancesPUBLICATIONSMilitaryMIL-BUL-5442.2 Other Publications.this specification to the extentdocuments which are indicated asList of Specifications and Stan

25、dards (BookForm)The following document(s) form a part ofspecified herein. The issues of theDOD adopted shall be the issue listed in thecurrent DODISS and the supplement thereto, if applicable.Society of Automotive Engineers (SAE), Inc. Aerospace Recommended PracticeARP699C-High Temperature Pneumatic

26、 Duct Systems for Aircraft(Application for copies should be addressed to the Society of AutomotiveEngineers, Inc., 400 Commonwealth Drive, Warrendale, PA 15096.)Technical society and technical association specifications and standards aregenerally available for reference from libraries. They are also

27、 distributedamong technical groups and using Federal agencies.3. REQUIREMENTS3.1 System components. The environmental control system shallinclude all instruments, controls, valves, ducting, filters, water separators,dehydrators, compressors, refrigeration units, heaters, dust separators heatexchange

28、rs, pumps, fluid 1ines, and such other equipment necessary to providethe required environmental control system performance for all operatingconditions of the aircraft. .3.2 Design conditions.3.2.1 Design atmospheric conditions.3.2.1.1 Operations. The design ambient conditions of the atmosphereunder

29、which equipment shall remain operational shall be in accordance with theoperations criteria of MIL-STD-210, Ground and World-Wide Air Environments.3.2.1.2 Performance. The design ambient conditions of the atmosphere formeeting the performance requirements of this specification shall be inaccordance

30、with the 10 percent risk criteria of MIL-STD-210, Ground andWorld-wide Air Environments. If a 10 percent risk criteria is not availablefor a given parameter, the highest risk factor provided shall be used.5Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-

31、,-,-MIL-E-18927E(AS)3.2.1.3 Ground operation humidity. For joint occurence of hightemperature and high humidity, the 1 percent curve of figure 1 shall be usedin conjunction with 3.2.1.1 and the 10 percent curve of figure 1 shall be usedin conjunction with 3.2.1.2.3.2.2 Electrical equipment. Electric

32、al equipment environment factorsare specified in MIL-E-7080.3.2.3 Electronic equipment. The environment factors for electronicequipment used in the design of environmental control systems shall be inaccordance with MIL-E-5400.3.2.4 Transparencies. The atmospheric conditions specified inMIL-T-5842 sh

33、all govern the design of defogging and defrosting systems for alltransparencies.3.2.5conditionsanti-icing3.2.6continuousconditionsIcinq conditions for wings and empennage. The atmosphericspecified in MIL-T-l86O7 shall govern the design of the thermalsystems and MIL-D-8804 for pneumatic boot de-icing

34、 systems.Transient operating conditions. The ECS shall be capable ofoperations and meet performance requirements during all transientsuch as rapidly changing altitudes extremes of temperature,accelerations or other conditions which could be encountered during take-off,flight, landing the aircraft, a

35、nd during ground conditions when engines arerunning.3.2.7 System sizing. The ECS shall be sized to provide the requiredheating and cooling capacity during all anticipated ground and flightoperations. The cooling provisions for electronic equipment shall provide foran electronic heat dissipation load

36、 25 percent greater than the equipment heatload of the first production aircraft. Enough clearance in the aircraft shallbe provided to allow the ECS to enlarge to accommodate an additional 25 percentgrowth in electronic heat load (50 percent greater than that of the firstproduction aircraft).3.3 Sel

37、ection of materials, parts, and processes. The materials,parts and processes used shall be selected primarily to accomplish thedesignated performance requirements. Specifications and standards for allmaterials, parts and processes shall be selected in accordance withMIL-STD-143 and MIL-BUL-544. Thes

38、e specifications and standards shall bepresented for review and acceptance by the procuring activity (see 6.2.2).3,3.1 Materials. All parts of the systems shall be made of corrosionresisting material or shall be suitably protected against corrosion internallyand externally. The use of dissimilar met

39、als in contact with each other shallbe suitably protected against galvanic corrosion. Dissimilar metals aredefined in MIL-STD-889.3.3.1.1 Magnesium. Magnesium and Magnesium alloys shall not be used.6Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL

40、-E-18927E7Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.3.1.2MIL-E-18927E(AS)19-9 DL steel. 19-9 DL stainless steel shall not be used.3.3.1.3 Non-specification material. Materials for which no federal, military, or industry specification exists,

41、the contractor shall developspecifications covering technical requirements and test methods thereof andacceptance criteria for review and acceptance by the procuring activity (see6.2.2).3.3.2 Parts.3.3.2.1 Standard parts. Standard parts (MS, AN or JAN) shall be usedwhenever they are suitable for the

42、 purpose and shall be identified on thedrawings by their part numbers. 3.3.2.2 Interchangeability. All parts having the same manufacturerspart number shall be functionally and dimensionally interchangeable as definedin MIL-I-8500.3.3.33.3.3.1processes.Protective treatment.3.3.3.1.1 Painting. Exposed

43、 corrosion and heat resisting steel parts needriot be painted. Finishes and coatings for all other exposed metal surfacesshall be Type I in accordance with MIL-F-7179.3.3.3.1.2 Aluminum anodizing. All aluminum and aluminum-alloy parts shallbe anodized in accordance with MIL-A-8625, Type II. Parts wh

44、ich cannot beanodized shall receive chemical conversion treatment in accordance withMIL-S-5002.3.3.3.1.3 Steel plating. All steel parts shall be plated. The parts whichreach temperature detrimental to plating shall not be plated.3.3,3.1.4 Chromium plating. Chromium plating shall be in accordance wit

45、hQQ-C-320. plating shall be applied directly on steel and at a rate notgreater than 0.0005 inches per hour.3.3.3.1.5 Zinc plating. Zinc plating shall be in accordance withQQ-Z-325. Zinc plating shall not be used on parts the temperature of whichmay exceed 600F (315C) in service.3.3.3.1.6 Cadmium pla

46、ting. Cadmium plating shall be electro-deposited inaccordance with QQ-P-416, Type II, class 2, except cadmium plating shall notbe used on parts the temperature of which exceeds 450F (232C) in service.3.3.3.1.7 Corrosion-Resistant Steel (CRS). Corrosion resistant parts need not be plated unless requi

47、red for dissimilar metal interface or functionalreasons. They shall be passivated in accordance with MIL-S-5002.8Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-E-18927E(AS)3.3.3.1.8 Aluminum plating. Aluminum plating on steel by ION Vapor Deposi

48、t(IVD) shall be in accordance with MIL-C-83488.3.3.3.2 Threads. Machine screw threads shall be in accordance withMIL-T-8879.3.4 Performance requirements.3.4.1 Pressurization. The pressurization systems for occupied anddesignated equipment compartments shall automatically maintain the nominalpressure

49、 schedules detailed herein. Aircraft with operating ceiling greaterthan 20,000 feet shall be pressurized.3.401.1 Fighter and attack aircraft. The cabins of fighter and attackaircraft shall be pressurized as shown in figure 2.3.4.1.1.1 Pressure change rate. The rate of pressure change during normaloperations shall be not greater than 0.2 psi/see for decreasing pressure and0.2 psi/see for increasing pressure under all operat