SAE ARP 292C-1998 Environmental Control Systems for Helicopters《真升机环境控制系统》.pdf

《SAE ARP 292C-1998 Environmental Control Systems for Helicopters《真升机环境控制系统》.pdf》由会员分享，可在线阅读，更多相关《SAE ARP 292C-1998 Environmental Control Systems for Helicopters《真升机环境控制系统》.pdf（54页珍藏版）》请在麦多课文档分享上搜索。

1、_ SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirely voluntary, and its applicability and suitability for any particular use, including any patent infringement arising there

2、from, is the sole responsibility of the user.” SAE reviews each technical report at least every five years at which time it may be revised, reaffirmed, stabilized, or cancelled. SAE invites your written comments and suggestions. Copyright 2014 SAE International All rights reserved. No part of this p

3、ublication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE. TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: +1 724-776-497

4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP292C AEROSPACE RECOMMENDED PRACTICE ARP292 REV. C Issued 1954-12 Revised 1998-

5、01 Reaffirmed 2014-12 Superseding ARP292B Environmental Control Systems for Helicopters RATIONALE ARP292C has been reaffirmed to comply with the SAE five-year review policy. TABLE OF CONTENTS1. SCOPE . 41.1 Purpose 42. REFERENCES . 42.1 SAE Publications . 42.2 FAA Publications 52.3 Military Publicat

6、ions . 52.4 Other Publications 63. DESIGN PHILOSOPHY 63.1 Regulations 73.1.1 Commercial Regulations 83.1.2 Military Regulations 93.2 Control and Indication 93.3 Safety. 93.4 Reliability and Maintainability. 113.5 Electrical Power . 113.6 Economics .124. SYSTEM APPROACHES.124.1 Candidate Systems134.1

7、.1 Vapor Cycle ECS .134.1.2 Air Cycle ECS 134.1.3 System Characteristics 20TABLE OF CONTENTS (Continued)4.2 System Integration Aspects .204.3 System Selection .225. SYSTEM DESIGN REQUIREMENTS 235.1 Ventilation 235.1.1 Commercial Helicopter Ventilation Requirements235.1.2 Military Helicopter Ventilat

8、ion Requirements245.1.3 Recirculation of Compartment Air 255.2 Bleed Air Control265.3 Auxiliary Compressors .285.4 Flow Control.285.4.1 Flow Control Mechanization.295.4.2 Flow Sensing .295.4.3 Flow Modulation.295.5 Air Distribution295.5.1 Passenger Compartment Air Distribution (Civil Transport Categ

9、ory).305.5.2 Crew Compartment Air Distribution305.6 Temperature Control 315.6.1 Duct Temperature Control315.6.2 Compartment Temperature Control315.7 Compartment Pressurization315.8 Performance 325.8.1 Cooling.325.8.2 Heating.325.8.3 Humidity .35.8.4 Fresh Airflow 325.9 Acoustic Considerations.335.10

10、 Crew Compartment Control and Indication335.10.1 Operating Controls.335.10.2 Operating Indications .345.10.3 Maintenance Indications 345.10.4 Built-in-Test (BIT) .355.11 Failure Considerations .355.12 Fire Resistance 355.13 Bleed Air Quality 365.14 Ground Test Provisions376. EQUIPMENT DESIGN REQUIRE

11、MENTS376.1 General Design Recommendations .376.1.1 Materials and Processes376.1.2 Environmental Requirements.376.1.3 Component Failure Concept 376.1.4 Rotating Equipment Containment 37SAE INTERNATIONAL ARP292C 2 OF 54TABLE OF CONTENTS (Continued)6.1.5 Rotating Equipment Overspeed Spin.386.1.6 Contam

12、ination386.1.7 Leakage .386.1.8 Proof and Burst Pressure.386.1.9 Bonding and Grounding .396.2 Component Design Recommendations .396.2.1 General Valve Design 396.2.2 Check Valves .406.2.3 Pressure Regulating and/or Shutoff Valves .416.2.4 Heat Exchangers .416.2.5 Air Cycle Machines 426.2.6 Water Sepa

13、rators .436.2.7 Fans and Ejectors 446.2.8 Shaft Driven Compressors.446.2.9 Vapor Cycle Compressors .456.2.10 Pressure Switches .456.2.11 Temperature Switches456.2.12 Temperature Sensors.456.2.13 Precooler Temperature Controls 466.2.14 Bleed Air Ducting .466.2.15 Ground Connections 466.3 Component/Eq

14、uipment Installation 476.3.1 Component/Equipment Installation - Safety.476.3.2 Component/Equipment Installation - Performance 487. ENVIRONMENT .507.1 Ambient Conditions507.1.1 Performance Standards .507.1.2 Operational Conditions 517.2 Installation Environment.53FIGURE 1 Vapor Cycle System Configura

15、tions.14FIGURE 2 Air Cycle System ACM Configurations.15FIGURE 3 Air Cycle System Water Separator Configurations 17FIGURE 4 Air Cycle Integral Recirculation System Configurations.19FIGURE 5 Design Temperatures for Equipment Performance 51FIGURE 6 Design Humidity for Equipment Performance 52FIGURE 7 J

16、oint Values of High Temperature and High Humidity54TABLE 1 Part 27 and Part 29 Applicable Requirements . 8TABLE 2 NATO Standardization Agreements .46SAE INTERNATIONAL ARP292C 3 OF 541. SCOPE:This ARP discusses design philosophy, system and equipment requirements, environmental conditions, and design

17、 considerations for helicopter environmental control systems (ECS). The helicopter ECS comprises that arrangement of equipment, controls, and indicators which supply and distribute dehumidified conditioned air for ventilation, cooling and heating of the occupied compartments, and cooling of the avio

18、nics. The principal features of the system are:a. A controlled fresh air supplyb. A means for cooling (air or vapor cycle units and heat exchangers)c. A means for removing excess moisture from the air supplyd. A means for heatinge. A temperature control systemf. A conditioned air distribution system

19、The ARP is applicable to both civil and military helicopters where an ECS is specified; however, certain requirements peculiar to military applications, such as nuclear, biological and chemical (NBC) protection, are not covered. The integration of NBC protection into aircraft ECS is discussed in AIR

20、4362.1.1 Purpose:The purpose of this ARP is to provide the guidelines and requirements for analysis, design, and installation of helicopter ECS.2. REFERENCES:2.1 SAE Publications:Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001.ARP85 Air Conditioning Systems for Subsonic Airplan

21、esARP86 Heater, Airplane, Engine Exhaust Gas to Air Heat Exchange TypeARP89 Aircraft Compartment Automatic Temperature Control EquipmentARP699 High Temperature Pneumatic Duct Systems for AircraftARP731 General Requirements for Application of Vapor Cycle Refrigeration Systems for AircraftAIR860 Aircr

22、aft Electrical Heating SystemsARP986 Guide for Qualification of Aircraft Air ValvesAIR1539 Environmental Control System ContaminationARP1796 Engine Bleed Air Systems for AircraftAIR1812 Environmental Control Systems Life Cycle CostAIR1826 Acoustic EnvironmentAS4073 Air Cycle Air Conditioning Systems

23、 for Military Air VehiclesAIR4362 NBC Consideration for ECS DesignSAE INTERNATIONAL ARP292C 4 OF 542.1 (Continued):ARP4418 Procedure for Sampling and Measurement of Engine Generated Contaminants in Bleed Air Supplies From Aircraft Engines Under Normal Operating ConditionsAS8040 Heater, Aircraft, Int

24、ernal Combustion Heat Exchanger Type2.2 FAA Publications:Available from Federal Aviation Administration, 800 Independence Avenue, SW, Washington, DC 20591.Federal Aviation Administration, Federal Aviation Regulations, Part 27 Airworthiness Standards: Normal Category RotorcraftFederal Aviation Admini

25、stration, Federal Aviation Regulation, Part 29 Airworthiness Standards: Transport Category RotorcraftFederal Aviation Administration, Federal Aviation Regulations, Parts 121-139 Certification and OperationsFederal Aviation Administration, Advisory Circular AC20-1352.3 Military Publications:Available

26、 from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.AFGS 87145 Environmental Control, Airborne, General Design SpecificationMIL-E-18927 Environmental Control Systems, Aircraft, General Requirements forMIL-B-81365 Bleed Air Systems, General Specifica

27、tionMIL-STD-210 Climatic Extremes for Military EquipmentMIL-STD-810 Environmental Test Methods for Aerospace and Ground EquipmentMIL-STD-1472 Human Engineering Design Criteria for Military Systems, Equipment, and FacilitiesMS33562 Connection, Aircraft Ground Air ConditioningNaval Air Systems Command

28、 SD-24K, Vol. II, General Specification for Design and Construction of Aircraft Weapon Systems, Volume II - Rotary Wing AircraftAir Force Office of Safety and Health (AFOSH) Standard 161-8 Permissible Exposure Limits for Chemical SubstancesSAE INTERNATIONAL ARP292C 5 OF 542.4 Other Publications:NATO

29、 Standardization Agreements (STANAG):STANAG 2895 Extreme Climatic Conditions and Derived Conditions for Use in Defining Design/Test Criteria for NATO Forces MaterialSTANAG 3208 Air Conditioning ConnectionsSTANAG 3315 Air Cabin Pressurizing Test ConnectionsSTANAG 3372 Pneumatic Starting NippleSTANAG

30、3610 Characteristics of Conditioned Breathable Air Supplied to Aircraft on the GroundAir Transport Association of America, Airline Industry Standard: World Airlines Technical Operations Glossary (WATOG) - 8th EditionAir Transport Association of America, Maintenance Steering Group, MSG-3Code of Feder

31、al Regulations, Title 29, Part 1910 Occupational Safety and Health Standards, Section 1910.93 Air ContaminantsRTCA/DO-160 Environmental Conditions and Test Procedures for Airborne EquipmentInternational Organization for Standardization, ISO 2026 Aircraft Connections for Starting by Air3. DESIGN PHIL

32、OSOPHY:Helicopters became much more viable as military and civil aircraft with the proliferation of the turboshaft engine in the 1960s, largely overcoming the drawbacks of their underpowered reciprocating engine predecessors. Unlike most turbojet and turboprop powered fixed-wing aircraft, rotorcraft

33、 had no need to be pressurized because of their low altitude operation. ECS on these fixed-wing aircraft were dominated by air cycle systems, which utilized engine compressor bleed air for pressurization and operation of the system. These systems were integral to the aircraft design from inception,

34、and engines were rated for maximum takeoff power while providing engine bleed air for air conditioning as well as other parasitic engine loads, such as electrical generators or hydraulic pumps. Penalties were measured in terms of fuel burn, with the added advantage of being able to turn off the air

35、conditioning during takeoff to obtain extra engine power in case of an engine failure at this very critical time.SAE INTERNATIONAL ARP292C 6 OF 543. (Continued):Historically, helicopter ECS has been added as an afterthought to an already designed airframe and power plant installation, or as a retrof

36、it to a production aircraft. Because of the extensive aircraft use of air cycle ECS, with its comparative light weight, high reliability and the availability of engine compressor bleed air from a turboshaft engine, air cycle systems have been predominantly used in military helicopter applications. H

37、owever, because helicopter engines are not designed to be bled while producing rated power, a double penalty is paid; one for fuel consumption, and one for loss of rated engine power due to the increase in turbine inlet temperature resulting from the loss of compressor core flow. Optimization of the

38、 ECS for available bleed pressure, even when added as an afterthought, can minimize these penalties, as can proper design of the engine bleed port. However, the best system for a new helicopter must include ECS power requirements in the specifications for main and auxiliary power systems, as is curr

39、ent practice on virtually all fixed wing aircraft.Several recent military and civil applications have incorporated vapor cycle ECS. Comparisons between air cycle and vapor cycle ECS producing the same amount of cooling and heating, when full integration with power sources is possible, should include

40、:a. Additional fuel consumption due to bleed and/or power consumptionb. Installed weight as it relates to higher engine requirements and the subsequent increase in specific fuel consumptionc. Installed power requirements as they relate to higher engine horsepower requirements and the subsequent incr

41、ease in specific fuel consumption.Steps should be taken to ensure that the design philosophy of the helicopter ECS reflects that of the helicopter on which it is installed. The helicopter systems specification will list primary design parameters (such as helicopter use considerations) from which an

42、ECS design philosophy can be formulated. The systems specification should be reviewed in detail prior to ECS preliminary design, and particular attention should be paid to (but not limited to) the following.3.1 Regulations:The ECS must comply with the airworthiness requirements listed in the helicop

43、ter systems specification. Although other portions of the systems specification may conflict with airworthiness requirements, airworthiness requirements should prevail.SAE INTERNATIONAL ARP292C 7 OF 543.1.1 Commercial Regulations: The FAA regulates the design of commercial helicopters for operation

44、in the United States in FAR Part 27 Normal Category Rotorcraft and FAR Part 29 Transport Category Rotorcraft. FAR Part 27 and Part 29 applicable requirements include the following in Table 1:Certification and operation of commercial helicopters in the United States is regulated by the FAA in FAR Par

45、ts 121-139, as applicable.Operating rules based on FAA or other individual country regulations are applied by the particular country of registry. Adequate provisions should be made in systems design to ensure that it is possible to meet other relevant requirements.Departure from convention in design

46、 or in operating environment may result in special airworthiness requirements being imposed. The requirements may be identified as special conditions until such time as they are incorporated into the applicable code of regulations. The existence and interpretation of such special conditions should b

47、e established at the outset.TABLE 1 - Part 27 and Part 29 Applicable RequirementsPart 27 Part 2927.561 27.831 - 27.853 27.859 27.861 27.863 27.116327.130127.130927.132227.146129.561 29.831 29.833 29.853 29.859 29.861 29.863 29.116329.130129.130929.132229.1461GeneralVentilationHeatingCompartment inte

48、riorsHeating systems/combustionFire protection of structure, controls, and other partsFlammable fluid fire protectionPowerplant accessoriesFunction and installationEquipment, systems, and installationsWarning, caution, and advisory lightsEquipment containing high energy rotorsSAE INTERNATIONAL ARP29

49、2C 8 OF 543.1.2 Military Regulations:3.1.2.1 Air Force/Army: ECS requirements are derived for each individual helicopter through tailoring of AFGS 87145 and/or MIL-E-18927.3.1.2.2 Navy: Overall requirements are derived from tailoring of SD-24K, Vol. II. ECS requirements are specified in MIL-E-18927 and bleed air system requirements are specified in MIL-B-81365.3.1.2.3 STANAG: Certain ECS provisions are the subject of NATO Standardization A