SAE AS 4073A-2013 Air Cycle Air Conditioning Systems for Military Air Vehicles《军用空中飞行器的空气循环空调系统》.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 2013 SAE International All rights reserved. No part of this pub

3、lication 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

4、(outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/AS4073AAEROSPACESTANDARDAS4073 REV. A Issued 1993-08 Reaffirmed 2000-03 Revised 2013

5、-08 Superseding AS4073 Air Cycle Air Conditioning Systems for Military Air Vehicles RATIONALEMost of the references have been superseded by other documents. They needed to be updated. TABLE OF CONTENTS 1. SCOPE 4 2. APPLICABLE DOCUMENTS 4 2.1 SAE Publications . 4 2.2 U.S. Department of Defense Publi

6、cations 4 2.3 AWS Publications . 5 2.4 NAS Publications 6 3. RECOMMENDED REQUIREMENTS . 6 3.1 System Definition 6 3.2 Characteristics 6 3.2.1 Performance 6 3.2.2 Physical Characteristics 7 3.2.3 Reliability . 9 3.2.4 Maintainability . 9 3.2.5 Environmental Conditions . 9 3.2.6 Transportability 10 3.

7、3 Design and Construction . 10 3.3.1 Materials, Parts, and Processes . 10 3.3.2 Electromagnetic Interference 13 3.3.3 Nameplates and Product Marking 14 3.3.4 Workmanship 14 3.3.5 Interchangeability and Replaceability . 14 3.3.6 Safety 14 3.3.7 Human Performance . 15 3.4 Documentation 15 3.5 Logistic

8、s 15 3.5.1 Maintenance 15 3.6 Precedence . 15 3.7 Major Component Characteristics 15 3.7.1 Air Cycle Machine . 15 3.7.2 Heat Exchangers. 17 3.7.3 Airflow Control System 18 3.7.4 Moisture Control Provisions 19 3.7.5 Ram Air Mover 20 3.7.6 Valves . 20 SAE AS4073A Page 2 of 45 3.7.7 Temperature Control

9、s . 21 3.7.8 System Controller 21 3.7.9 Fans 21 3.7.10 Pneumatically Actuated Components . 22 3.7.11 Ducting, Couplings, and Insulation . 22 3.8 Mockup 22 4. QUALITY ASSURANCE PROVISIONS 22 4.1 Responsibility for Tests. 22 4.2 Classification of Tests . 22 4.3 Test Conditions . 22 4.3.1 Tolerances 23

10、 4.3.2 Cleanliness 23 4.4 Mockup 23 4.5 Preproduction Testing . 23 4.5.1 Test Plan . 23 4.5.2 Test Specimens 23 4.5.3 System Tests 23 4.5.4 Component Tests 24 4.5.5 Ground and Flight Tests . 26 4.5.6 Reliability . 26 4.5.7 Maintainability . 26 4.5.8 Test Report . 26 4.6 Quality Conformance Tests 27

11、4.7 Test Methods 27 4.7.1 Examination of Product . 27 4.7.2 Proof Pressure and Leakage 27 4.7.3 Performance 27 4.7.4 Environmental Tests . 28 4.7.5 Attitude 29 4.7.6 Air Contamination 29 4.7.7 Noise Level . 29 4.7.8 Electromagnetic Interference 29 4.7.9 Flow Resonance . 29 4.7.10 Endurance . 30 4.7.

12、11 Disassembly and Inspection . 30 4.7.12 Burst Pressure 30 4.7.13 Air Cycle Machine Tests . 30 4.7.14 Heat Exchanger Tests 31 4.7.15 Airflow Control System Tests 33 4.7.16 Moisture Control Tests 34 4.7.17 Valve Tests . 34 4.7.18 Switch Tests 34 4.7.19 Sensor Tests . 35 4.7.20 Temperature Control an

13、d System Controller Performance 35 4.7.21 Fan Tests 35 4.7.22 Pneumatically Actuated Component Tests . 35 4.7.23 Minimum Functional 36 4.7.24 Rotational Overspeed . 36 5. DEFINITIONS . 37 5.1 Air Cycle Machine . 37 5.2 Air Vehicle . 37 5.3 Coalescer 37 5.4 Contractor . 37 5.5 Critical Material . 37

14、5.6 Detail Specification 37 5.7 Entrained Moisture 37 5.8 Heat Exchangers. 37 SAE AS4073A Page 3 of 45 5.9 Logistics Critical Component 37 5.10 Manufacturer . 37 5.11 Maximum Normal Operating Speed . 37 5.12 Nonoperating Components . 38 5.13 Operating Components . 38 5.14 Procuring Activity 38 6. NO

15、TES 38 TABLE 1 ENDURANCE LIFE . 7 TABLE 2 VERIFICATION CROSS REFERENCE INDEX (VCRI) . 39 TABLE 3 SYSTEM TESTS . 45 SAE AS4073A Page 4 of 45 1. SCOPE This SAE Aerospace Standard (AS) defines the requirements for air cycle air conditioning systems used on military air vehicles for cooling, heating, ve

16、ntilation, and moisture and contamination control. General recommendations for an air conditioning system, which may include an air cycle system as a cooling source, are included in MIL-E-18927E (AS) and JSSG-2009.Air cycle air conditioning systems include those components which condition high tempe

17、rature and high pressure air for delivery to occupied and equipment compartments and to electrical and electronic equipment. This document is applicable to open and closed loop air cycle systems. Definitions are contained in Section 5 of this document. 2. APPLICABLE DOCUMENTS The following publicati

18、ons form a part of this document 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 cite

19、d herein, the text of this document 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: 877-606-73

20、23 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org.AIR1826 Acoustical Considerations for Aircraft Environmental Control System Design AMS-H-6875 Heat Treatment of Steel Raw Materials AMS-STD-2175 Castings, Classing and Inspection of ARP780 Environmental Systems Schematic Symbols A

21、S4395 Fitting End-Flared, Tube Connection, Design Standard AS4396 Fitting End, Bulkhead, Flared Tube Connection, Design Standard AS5202 Port or Fitting End, Internal Straight, Thread, Design Standard AS8879 Screw Threads - Unj Profile, Inch Controlled Radius Root With Increased Minor DiameterAS71051

22、 Pipe Threads, Taper, Aeronautical National Form, Symbol ANPT - Design and Inspection Standard 2.2 U.S. Department of Defense Publications Available from DLA Document Services, Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697-6396, http:/quicksearch.dla.mil/.JSSG-2009 Air

23、Vehicle Subsystems MIL-DTL-5541 Chemical Conversion Coatings on Aluminum Alloys MIL-S-7742 Screw Threads, Standard, Optimum Selected Series, General Specification for SAE AS4073A Page 5 of 45 MIL-B-7883 Brazing of Steels, Copper, Copper Alloys, Nickel Alloys, Aluminum and Aluminum Alloys MIL-I-8500

24、Interchangeability and Replaceability of Component Parts for Aircraft and Missiles MIL-A-8625 Anodic Coatings, For Aluminum and Aluminum Alloys MIL-E-18927 Environmental Control Systems, Aircraft, General Requirements for MIL-STD-130 Identification Marking of U.S. Military Property MIL-STD-461 Elect

25、romagnetic Emission and Susceptibility Requirements for the Control of Electromagnetic InterferenceMIL-STD-704 Aircraft Electric Power Characteristics MIL-STD-810 Environmental Test Methods and Engineering Guidelines MIL-STD-882 System Safety Program Requirements MIL-STD-889 Dissimilar Metals MIL-ST

26、D-1472 Human Engineering Design Criteria for Military Systems, Equipment and Facilities MIL-STD-1474 Noise Limits MIL-STD-7179 Finishes, Coatings, and Sealants for the Protection of Aerospace Weapon System MIL-STD-31000 Technical Data Packages (TDP) MIL-HDBK-310 Global Climatic Data for Developing M

27、ilitary Products MIL-HDBK-831 Military Handbook: Preparation of Test Reports MIL-HDBK-1568 Materials and Processes for Corrosion Prevention and Control in Aerospace Weapon Systems MIL-HDBK-1587 Materials and Processes Requirements for Air Force Weapon Systems 2.3 AWS Publications Available from Amer

28、ican Welding Society, 8669 NW 36 Street, #130, Doral, FL 33166, Tel: 800-443-9353 or 305-443-9353, www.aws.org.AWS C3.4 Specification for Torch Brazing AWS C3:5 Specifications for Induction Brazing AWS C3.6 Specification for Furnace Brazing AWS C3.7 Specification for Aluminum Brazing AWS D17.1 Speci

29、fication for Fusion Welding for Aerospace Applications SAE AS4073A Page 6 of 45 2.4 NAS Publications Available from Aerospace Industries Association, 1000 Wilson Boulevard, Suite 1700, Arlington, VA 22209-3928, Tel: 1-703-358-1000, www.aia-aerospace.org.NASM33540 Safety Wiring and Cotter Pinning, Ge

30、neral Practice for 3. RECOMMENDED REQUIREMENTS This section contains recommended requirements for inclusion in Section 3 Requirements of a detail specification prepared for procurement of air cycle air conditioning systems for use on new or retrofit on existing military aircraft.3.1 System Definitio

31、n This paragraph should contain a comprehensive definition of the system to be developed. A functional schematic drawing and identification of major components shall be included. Use ARP780 as a guide in the preparation of the schematic drawing.3.2 Characteristics 3.2.1 Performance The system shall

32、provide air at the flow rates, temperatures, pressures, and moisture and contaminant levels necessary to meet the environmental control and environmental protection performance requirements specified in the detail specification. The detail specification shall define the following operational conditi

33、ons, where applicable, throughout the ground and flight operating envelope of the air vehicle: a. Temperature, pressure, humidity, and level of contaminants of bleed air, ram air, or compressed ram air at the inlet to the system b. Temperature and pressure of the compartment where the system is inst

34、alled c. Occupied and equipment compartment pressure schedules d. Heat sink inlet temperature, pressure, flow rate, and maximum allowable heat input e. Minimum air flows required for all operating conditions f. Supply air distribution ducting and heat sink system pressure drop and flow rate g. Allow

35、able quantity of occupied and equipment compartment air to be recirculated h. Maximum allowable engine horsepower and bleed air extraction i. Maximum allowable electrical power 3.2.1.1 Useful Life The nonoperating components of the system shall be designed to have a life equal to or greater than tha

36、t of the air vehicle on which the system is to be installed. The useful life of the operating components of the system shall be as specified in the detail specification. Throughout the useful life, component overhaul is permissible provided the component can be overhauled economically. SAE AS4073A P

37、age 7 of 45 3.2.1.2 Endurance Life Components which cannot be overhauled economically shall have an endurance life equal to the useful life. Recommended minimum endurance life for system components which can be overhauled is shown in Table 1: TABLE 1 - ENDURANCE LIFE In addition, endurance tests as

38、specified in Section 4 shall be conducted to show that the system components comply with design requirements. The number of endurance test cycles for system components of missile and all other applications shall be reduced as defined in the detail specification. 3.2.1.3 Contamination Air contaminati

39、on levels within occupied compartments as a result of system operation shall not exceed exposure limits established in the detail specification. 3.2.1.4 Noise Level Noise levels within occupied compartments as a result of system operation shall conform to the requirements of the detail specification

40、, which may have varying requirements for different operating modes. Use AIR1826 as a guide for reducing system noise levels. Use MIL-STD-1474 as a guide for establishing allowable noise levels. 3.2.1.5 Leakage Internal and external leakage rates for all system components shall not exceed the values

41、 specified in the detail specification. System performance requirements shall be met at maximum allowable leakage rates. 3.2.1.6 Equipment Warmup Time The system shall be capable of operating at full capacity within 60 seconds of initial operation after soaking in the ambient temperature extremes ou

42、tlined in 3.2.5. 3.2.2 Physical Characteristics 3.2.2.1 Weight The weight of the system shall not exceed the maximum allowable weight specified in the detail specification. 3.2.2.2 Size and Configuration The size and configuration of the system and its components and assemblies shall be in accordanc

43、e with the detail specification. Where desirable, the complete system or a major portion thereof shall be preassembled into a compact package; however, system configuration shall be compatible with service and repair requirements while installed in the air vehicle.SAE AS4073A Page 8 of 45 3.2.2.3 Ha

44、ndling Provisions Preassembled packages and components whose weight exceeds the lifting capability of one person as defined by MIL-STD-1472 shall have provisions for the use of handling aids to enable lifting the assembly or component into and out of the air vehicle and for placing the assembly or c

45、omponent on the ground. These provisions shall not in any way hinder the use of the normal mounting points. 3.2.2.4 Flange Orientation To facilitate assembly, the system shall be designed to provide for freedom in the relative orientation of inlet and discharge flange planes consistent with the over

46、all design philosophy of the aircraft. Detail requirements will be specified in the detail specification. 3.2.2.5 Mounting The system mounting provisions shall be such that structural loads are not reacted at the duct connections and stress is not induced into system components when installed in the

47、 air vehicle. Mounting provisions shall be capable of withstanding the inertia loads as specified in the detail specification. The system shall have provisions for mounting to the air vehicle as required by the detail specification. 3.2.2.6 Structural Integrity 3.2.2.6.1 Proof Pressure Unless otherw

48、ise specified in the detail specification, all system components which are exposed to positive or negative pressure shall withstand, without permanent deformation, a proof pressure equal to the greater of the following: a. 1.5 times the gage pressure with the component at the associated temperature

49、for the most adverse pressure and temperature condition that occurs during normal operation. b. 1.1 times the gage pressure with the component at the associated temperature for the most adverse pressure and temperature condition that occurs in the event of failure of a pressure or temperature control device. 3.2.2.6.2 Burst Pressure Unless otherwise specified in the detail specification, all system components which are exposed to p