SAE AIR 744C-2010 Aerospace Auxiliary Power Sources《航空辅助电源》.pdf

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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 theref

2、rom, 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 2015 SAE InternationalAll rights reserved. No part of this publi

3、cation 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: +1 724-776-4970 (out

4、side USA)Fax: 724-776-0790Email: CustomerServicesae.orgSAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedbackon this Technical Report, please visithttp:/www.sae.org/technical/standards/AIR744CAEROSPACEINFORMATION REPORTAIR744REV. CIssued 1964-04Revised 2010-06Reaffirmed 2015-10

5、Superseding AIR744BAerospace Auxiliary Power SourcesRATIONALEAIR744C has been reaffirmed to comply with the SAE five-year review policy.TABLE OF CONTENTS 1.SCOPE 42.REFERENCES 42.1SAE Publications . 42.2U.S. Government Publications 42.3ASTM Publications 42.4DOT Publications 52.5RTCA Publications 52.

6、6Acronyms and Abbreviations 53.TYPES OF POWER SOURCES . 64.REQUIREMENTS FOR POWER SOURCES . 74.1General . 74.2Definition of Requirements 74.3Power Source Selection 85.SOLID PROPELLANTS 95.1Description 95.2Applications . 95.3Components 105.4Advantages . 135.5Disadvantages 135.6Developing Technology 1

7、46.LIQUID PROPELLANTS . 146.1Description 146.2Applications . 146.3Components 157.HIGH PRESSURE STORED GAS SYSTEM 187.1Description 187.2Applications . 187.3Components 187.4Sizing the Container 197.5Advantages . 227.6Disadvantages 228.ENGINE BLEED SYSTEMS . 238.1Description 238.2Applications . 248.3Sy

8、stems and Component Detail and Description (General) . 249.RAM AIR TURBINES 299.1Description 299.2Applications . 299.3Performance Characteristics. 319.4Advantages . 359.5Disadvantages 3610.BATTERIES 3610.1Description 3610.2Primary Batteries . 3610.3Secondary Batteries 3710.4Common Battery Types 3710

9、.5Application Terminology 3710.6Applications . 3810.7Development Batteries 4311.FUEL CELLS . 4411.1Description 4411.2Applications . 4511.3Components 4611.4Advantages . 4611.5Disadvantages 4712.SOLAR CELLS 4712.1Description 4712.2Applications . 4912.3Components 4912.4Performance 4912.5Advantages . 49

10、12.6Disadvantages 4913.NUCLEAR POWER SYSTEMS 5013.1Description 5013.2Applications . 5013.3Components 5013.4Advantages . 5213.5Disadvantages 5214.GAS TURBINE AUXILIARY POWER UNITS (APUS) 5314.1Description 5314.2Applications . 5714.3APU Installations . 5814.4APU Performance . 6514.4.1Uninstalled APU P

11、erformance 6514.4.2Ambient Pressure and Temperature . 6514.4.3Exhaust Gas Back Pressure . 6914.4.4Performance Correction Factors . 6914.4.5APU In-Flight Performance . 6914.5Advantages of an On-Board APU . 6914.6Disadvantages of an On-Board APU 7115.FLYWHEELS 7115.1Description 7115.2Applications . 72

12、15.3Component Detail Design . 7416.NOTES 85SAE INTERNATIONAL AIR744C 2 OF 85FIGURE 1 REPRESENTATIVE TRACES OF STORED GAS TIME VERSUS PRESSUREDURING OPERATION 20FIGURE 2 DENSITY OF NITROGEN VERSUS TEMPERATURE (AT VARIOUS PRESSURES IN PSIA) . 21FIGURE 3 ENGINE/SYSTEMS INTERFACES AND THEIR EFFECTS 24FI

13、GURE 4 BLEED STUDY OF THE JT9D-3A ENGINE, STANDARD DAY CONDITIONS 27FIGURE 5 BLEED AIR CHARACTERISTICS OF THE JTD9D-3A ENGINE . 28FIGURE 6 SENSITIVITY CURVES FOR THE A1SA BPR-280024 ENGINE 30FIGURE 7 GENERALIZED TURBINE POWER COEFFICIENT CHARACTERISTICS VERSUSN/VO FOR A FREESTREAM TURBINE 33FIGURE 8

14、 GENERALIZED TORQUE CHARACTERISTICS FOR HIGH- AND LOW-SOLIDITY TURBINESHAVING THE SAME BLADE SWEPT AREA AND SAME OPERATING AIRSPEED 35FIGURE 9 ALKALILNE FUEL CELL CONCEPT 46FIGURE 10 TYPICAL AIRCRAFT PNEUMATIC SYSTEM 53FIGURE 11 CROSS-SECTION OF AN INTEGRAL BLEED AIR APU 54FIGURE 12 CROSS-SECTIOIN O

15、F A TWO-SPOOL APU 55FIGURE 13 CROSS-SECTION OF A LOAD COMPRESSOR APU 55FIGURE 14 CROSS-SECTION OF A SINGLE-SPOOL, SHAFT- ONLY- LOAD, APU . 56FIGURE 15 SECONDARY POWER SYSTEM FOR U.S. AIR FORCE B-1B 58FIGURE 16 TYPICAL APU TAILCONE INSTALLATIONS 60FIGURE 17 EXAMPLES OF MOUNTING ARRANGEMENTS 61FIGURE

16、18 TYPICAL APU FUEL SUPPLY SYSTEM . 62FIGURE 19 TYPICAL APU CONTROL PANELS (DC-10) . 64FIGURE 20 APU SIMPLIFIED CONTROL PANEL (B-767) . 64FIGURE 21 TYPICAL SINGLE-SHAFT INTEGRAL-BLEED APU PERFORMANCE (MAXIMUM EGT CONDITION) . 66FIGURE 22 TYPICAL TWO-SPOOL APU PERFORMANCE 67FIGURE 23 TYPICAL PERFORMA

17、NCE FOR LOAD COMPRESSOR APU . 68FIGURE 24 TYPICAL CORRECTION FACTOR CURVES 70FIGURE 25 TYPICAL STARTING AND OPERATING ENVELOPE WITH 100% RAM RECOVERY . 71FIGURE 26 COMPARATIVE PRACTICAL ENERGY STORAGE CAPABILITIES 73FIGURE 27 COMPARATIVE POWER EXTRACTION CHARACTERISTICS AND EFFICIENCY 73FIGURE 28 FL

18、YWHEEL SHAPE FACTORS FOR VARIOUS GEOMETRIES 76FIGURE 29 FLYWHEEL SPEED REDUCTION CHARACTERISTICS 78FIGURE 30 SOLID UNIFORM STRESS DISK FLYWHEEL GEOMETRY OPTIMIZATION CHART 81TABLE 1 TYPICAL SOLID PROPELLANTS FOR GAS GENERATORS 11TABLE 2 MONOPROPELLANT CHARACTERISTICS 16TABLE 3 TYPICAL BIPROPELLANT C

19、HARACTERISTICS 17TABLE 4 ADVANTAGES AND DISADVANTAGES OF BLEED AIR APPLICATION 23TABLE 5 COMPUTATION OF POWER AVAILABILITY 25TABLE 6 TYPICAL DATA FOR AIRCRAFT ENGINE JT3D-3B. 26TABLE 7 TURBINE POWER COEFFICIENTS 32TABLE 8 COMMON BATTERY TYPES . 37TABLE 9 COMPARISON OF PRIMARY BATTERIES . 39TABLE 10

20、COMPARISON OF SECONDARY BATTERIES 42TABLE 11 SUMMARY TABLE . 44TABLE 12 TYPES OF FUEL CELLS 45TABLE 13 APU/AIRCRAFT INTERFACE CONSIDERATIONS . 59TABLE 14 FLYWHEEL MATERIAL PROPERTIES . 74TABLE 15 FLYWHEEL GEOMETRY FOR AN OPTIMIZED DISK 79SAE INTERNATIONAL AIR744C 3 OF 851. SCOPE This SAE Aerospace I

21、nformation Report (AIR) is a review of the general characteristics of power sources that may be used to provide secondary, auxiliary, or emergency power for use in aircraft, space vehicles, missiles, remotely piloted vehicles, air cushion vehicles, surface effect ships, or other vehicles in which ae

22、rospace technology is used. The information contained herein is intended for use in the selection of the power source most appropriate to the needs of a particular vehicle or system. The information may also be used in the preparation of a power source specification. Considerations for use in making

23、 a trade study and an evaluation of the several power sources are included. More detailed information relating to specific power sources is available in other SAE Aerospace Information Reports or in Aerospace Recommended Practices. 2. REFERENCES The following publications form a part of this documen

24、t to the extent specified herein. The latest issue of SAE publications shall apply. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this docu

25、ment takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 2.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 7

26、24-776-4970 (outside USA), www.sae.org. ARP699 High Temperature Pneumatic Duct Systems for Aircraft AIR1168/1 Thermodynamics of Incompressible and Compressible Fluid Flow AIR1343 Liquid Propellant Gas Generation Systems J1775 Bleed-Air Pneumatic Systems for Gas Turbine Equipped Marine and Amphibious

27、 Craft 2.2 U.S. Government Publications Available from the Document Automation and Production Service (DAPS), Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697-6257, http:/assist.daps.dla.mil/quicksearch/.MIL-STD-810 Environmental Engineering Considerations and Laboratory T

28、ests MIL-DTL-5624 Turbine Fuels, Aviation Grades, JP4-JP5 MIL-PRF-7808 Lubricating Oil, Aircraft Turbine Engine, Synthetic Base MIL-PRF-23699 Lubricating Oil, Aircraft Turbine Engine, Synthetic Base, NATO Code Number 0-156 Reviewer: 68 AR AV GS SH 2.3 ASTM Publications Available from ASTM Internatio

29、nal, 100 Barr Harbor Drive, P.O. Box C700, West Conshohocken, PA 19428-2959, Tel: 610-832-9585, www.astm.org. ASTM D1655 Standard Specification for Aviation Turbine Fuels ASTM D910 Standard Specification for Aviation Gasolines SAE INTERNATIONAL AIR744C 4 OF 852.4 DOT Publications Available from DOT,

30、 400 7th Street SW, Washington, DC 20024. DOT 3HT DOT Code of Federal Regulations (Title 49) Transportation 49 Parts 400 to 99, Revised as of October 1, 1992 2.5 RTCA Publications Available from RTCA, Incorporated, 1828 L Street, NW, Suite 805, Washington D.C. 20036, Tel: 202-833-9339, Fax: 202-833-

31、9434, www.rtca.org.RTCA DO-311 Minimum Operational Performance Standards for Rechargeable Lithium Battery SystemsRTCA DO-254 Design Assurance Guidance for Airborne Electronic Hardware RTCA DO-178B Software Considerations in Airborne Systems and Equipment Certification 2.6 Acronyms and Abbreviations

32、AC Alternating CurrentADG Accessory Drive Gearbox AIR Aerospace Information Report ALSEP Apollo Lunar Surface Experiment Package AM Air Mass APU Auxiliary Power Unit ARP Aerospace Recommended Practice ATS Air Turbine Starter ATSCV Air Turbine Starter Control Valve AU Astronomical UnitCRT Cathode Ray

33、 Tube DC Direct CurrentDOT Department of Transportation EBW Exploding Bridgewire ECA Electronic Control Assembly ECU Electronic Control Unit EGT Exhaust Gas Temperature FAA Federal Aviation Administration HP Hydraulic PumpSAE INTERNATIONAL AIR744C 5 OF 85HS Hydraulic StarterIDG Integrated Drive Gene

34、rator MCT Maximum Continuous Rating MTBF Mean Time Between Failures NRC Nuclear Regulatory Commission O/F Oxidizer to Fuel Ratio PMG Permanent Magnet Generator SNAP Space Nuclear Auxiliary Power SPS Secondary Power System TBI Thru-Bulkhead InitiatorTC Torque ConverterTSFC Thrust Specific Fuel Consum

35、ption 3. TYPES OF POWER SOURCES The more prominent types of auxiliary power sources are described. These power sources provide energy in the form of gas or airflow at various pressures and temperatures or as mechanical or electrical energy. Energy conversion equipment may be required to convert the

36、energy to the form desired, i.e., to shaft, electric, hydraulic, or pneumatic power. These power sources are: a. Solid propellant gas generators that produce hot gas b. Liquid propellant gas generators that produce hot gas c. Noncirculating or blowdown systems that provide gas from a stored high-pre

37、ssure fluid d. Engine bleed systems that provide high-pressure air e. Ram air turbines that generate mechanical power to drive generators or pumps f. Primary and secondary batteries g. Fuel cells that produce electrical power h. Solar cells that convert incident sunlight into electrical power i. Nuc

38、lear (usually radioisotope fueled) thermoelectric power sources j. Auxiliary gas turbine engines for bleed air and/or mechanical power k. Stored mechanical energy (flywheel) SAE INTERNATIONAL AIR744C 6 OF 854. REQUIREMENTS FOR POWER SOURCES 4.1 General An auxiliary power source may be required to: a

39、. Provide continuous power to a system, auxiliary system, or subsystem b. Provide power in response to system needs c. Provide power in the event of malfunction or failure of a primary power source An auxiliary power source may not be required to meet, in full, the specification requirements for the

40、 primary power source, i.e., limited duty. A malfunction of an auxiliary power source when used in a manned vehicle, other than when used in place of a failed primary source, shall not cause a catastrophic failure of the parent vehicle. 4.2 Definition of Requirements At a minimum, a clear definition

41、 of the following requirements should be made: a. Functional Requirements: A description of primary and secondary (if any) functional requirements should be made. b. Type: Type, energy-level duration, and quality of power required; such as hydraulic, pneumatic, electrical, mechanical, actuation, or

42、force (thrust) should be described. c. Duty Cycle: Operational requirements should be described, including those for ground checkout prior to and following the mission as well as those for the complete mission. Also to be included are: overload requirements and quality of power; operational requirem

43、ents for a single mission or for successive missions extending over a period of time; system prefunction testing requirements, i.e., solid propellant gas generator lot sample destruct tests; and unattended standby time.d. Response Time: Power source response time should be described with respect to

44、actuation, activation signal or command, or changing loads. e. Environment: Operational and nonoperational power source requirements should be described during and/or after exposure to the following environmental conditions: 1. Pressure 2. Acceleration 3. Temperature 4. Contaminants 5. Ambient gases

45、 6. Foreign objects 7. Ambient liquids 8. Corrosion/erosion 9. Vibration 10. Radiation 11. Shock SAE INTERNATIONAL AIR744C 7 OF 85The effect of an extended time period in the environment on standby status should be considered. The requirements of MIL-STD-810 should apply. 4.3 Power Source Selection

46、In making a tradeoff study of candidate power sources, the systems approach is suggested. Considerations to be made regarding use of candidate power sources may include those listed below: a. Cost: Cost considerations may include: 1. Unit cost 2. System cost 3. Nonrecurring cost 4. Development cost

47、5. Cost per unit of output or performance 6. Life cycle cost b. Weight: Weight considerations may include: 1. Weight per unit of output 2. System weight c. Installation: Packaging of shaping of system to fit available envelope should be considered, as should any requirements for protective zones, sh

48、ielding, servicing, and mounting provisions. d. Availability: Availability considerations may include: 1. Off-the-shelf 2. Development time 3. Lead time 4. Single or multiple sources e. Complexity: Complexity considerations may include any special equipment requirements. f. Reliability and Safety: Reliability