SAE ARP 1493C-2013 Wheel and Hydraulically Actuated Brake Design and Test Requirements for Military Aircraft《军事航空器用轮子和液压制动器的设计和试验要求》.pdf

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 2013 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.orgSAE values your input. To provide feedback on this Technical Report, please visit http:/www.sae.org/technical/standards/ARP1493CAEROSPACERECOMMENDED PRACTICEARP1493 REV. CIssued 1979-07 Reaffirmed 2007-

5、07 Revised 2008-06 Stabilized 2013-11 Superseding ARP1493B Wheel and Hydraulically Actuated Brake Design and Test Requirements for Military Aircraft RATIONALE Due to current U.S. government rules effecting sharing of information regarding military technology and services (i.e. ITAR, EAR, etc.) furth

6、er updates to this document will no longer be possible. STABILIZED NOTICE This document has been declared “Stabilized“ by the SAE A-5A Wheels, Brakes and Skid Controls Committee and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and conti

7、nued suitability of technical requirements. Newer technology may exist. Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-TABLE OF CONTENTS 1. SCOPE 3 1.1 Purpose. 3 2. REFERENCES 3 2.1 Applicable Docu

8、ments 3 2.1.1 SAE Publications. 3 2.1.2 ASTM Publications 4 2.1.3 U.S. Government Publications 4 2.2 Definitions . 4 2.2.1 Design Drawings. 4 2.2.2 Normal Operating Pressure 4 2.2.3 Normal Parking Pressure 4 2.2.4 Maximum Operating Pressure 5 2.2.5 Weights and Speeds. 5 2.2.6 Loads 5 3. REQUIREMENTS

9、 . 6 3.1 Drawings . 6 3.1.1 Design Proposal Drawings 6 3.1.2 Interface Drawings 6 3.2 Materials 7 3.3 Protective Treatment. 7 3.4 Detail Design Requirements . 7 3.4.1 Wheel Design Requirements 7 3.4.2 Brake Design Requirements. 9 3.4.3 Detail Design Requirements - General. 10 3.4.4 Interface Definit

10、ion for Wheel and Brake Detail Design . 11 3.5 Capability Requirements. 14 3.5.1 Performance 14 3.5.2 Reliability. 14 3.5.3 Maintainability . 14 3.5.4 Braking Capacity. 15 3.5.5 Wheel Capacity. 19 3.5.6 Compatibility Requirements 19 3.5.7 Environment 19 _ SAE INTERNATIONAL ARP1493C Page 1 of 31Copyr

11、ight SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4. QUALITY ASSURANCE PROVISIONS 20 4.1 Product Verification. 20 4.1.1 Stress Analysis 20 4.2 Test Methods 20 4.2.1 Radial Load Test. 20 4.2.2 Design Landing

12、 Radial Load Test. 21 4.2.3 Combined Load Test. 21 4.2.4 Burst Test 22 4.2.5 Roll Test 22 4.2.6 Tubeless Wheel Pressure Test. 23 4.2.7 Dynamic Torque Test 23 4.2.8 Lining Fusion Test. 26 4.2.9 Turnaround Dynamic Torque Test 26 4.2.10 Compatibility Tests 26 4.2.11 Structural Torque Test 26 4.2.12 Ove

13、rpressure Test 26 4.2.13 Endurance Test. 27 4.2.14 Extreme Temperature Test. 27 4.2.15 Extreme Temperature Test. 27 4.2.16 Service Test 28 4.2.17 Safety of Flight Tests 28 4.3 Quality Conformance Tests 28 4.3.1 Tests of Materials and Parts . 28 4.3.2 Tests of Wheel Assemblies. 28 4.3.3 Tests of Brak

14、e Assemblies . 29 4.3.4 Replacement Wheel and Brake Assemblies. 30 4.3.5 Replacement Wheel and Brake Assembly Parts 30 5. NOTES 30 5.1 Data Submittal. 30 5.2 Conformance to Test Samples . 31 5.3 Reprocurement Specification 31 5.4 Interface Document. 31 _ SAE INTERNATIONAL ARP1493C Page 2 of 31Copyri

15、ght SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-1. SCOPE This document covers military aircraft wheel and hydraulically actuated brake equipment. 1.1 Purpose This document provides recommended practices fo

16、r designing and testing wheels and hydraulically actuated brakes for use on new designs of military aircraft. Intended users are airframe and military personnel who prepare detail design and performance specifications. It is not intended to be a procurement document. This document provides updated i

17、nformation to MIL-W-5013 which has been classified inactive for new design. 2. REFERENCES 2.1 Applicable Documents The following publications 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 shal

18、l 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 document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption ha

19、s been obtained. 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org. ARP597 Wheels and Brakes, Supplementary Criteria for Design Endurance Civil Transport Air

20、craft AS707 Thermal Sensitive Inflation Pressure Release Devices for Tubeless Aircraft Wheels ARP813 Maintainability Recommendations for Aircraft Wheels and Brake Design ARP1619 Replacement and Modified Brakes and Wheels ARP5146 Assessment of Aircraft Wheel Sealing Systems AS5202 Port or Fitting End

21、, Internal, Straight Thread, Design Standard AS5440 Hydraulic Systems, Aircraft, Design and Installation Requirements for AIR5451 A Guide to Landing Gear System Integration ARP5481 Recommended Wheel Tie Bolt Preload Procedure ARP5600 Disposition of Damaged Wheels Involved in Accidents/Incidents AS88

22、60 Landing Gear Structural Requirements as Listed in the MIL-886X Series of Specifications AS25427 Coupling Assembly, Hydraulic, Self-Sealing, Quick Disconnect AS28775 Packing, Preformed, Hydraulic, +275F (O-Ring) AMS2175 Castings, Classification and Inspection of _ SAE INTERNATIONAL ARP1493C Page 3

23、 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.1.2 ASTM Publications Available from ASTM International, 100 Barr Harbor Drive, P.O. Box C700, West Conshohocken, PA 19428-2959, Tel: 610-832-9

24、585, www.astm.org. ASTM E 1417 Standard Practice for Liquid Penetrant Testing ASTM E 1444 Standard Practice for Magnetic Particle Testing 2.1.3 U.S. Government Publications Available from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, http:/assist.d

25、aps.dla.mil/quicksearch/. JSSG-226 Aircraft Structures, General Specification MIL-A-8625 Anodic Coatings for Aluminum and Aluminum Alloys MIL-HDBK-275 Lubricants Fluids and Compounds for use in Flight Vehicles and Components, Selection Guide MIL-HDBK-838 Lubrication of Military Equipment MIL-P-83461

26、 Packing, Preformed, Petroleum Hydraulic Fluid Resistant Improved Performance at 275F (135 C) for use in Boss Fittings, Sizes and Tolerances MIL-PRF-23377 Primer Coatings; Epoxy, High-Solids MIL-PRF-85285 Coating, Polyurethane, Aircraft and Support Equipment MIL-W-5013 Wheel and Brake Assemblies, Ai

27、rcraft, General Specification (for Reference Only - Inactive for New Design) MS27436 Cable Configuration, Grounding Aircraft MS27611 Valve, Hydraulic Bleeder, Aircraft Wheel Brake 2.2 Definitions 2.2.1 Design Drawings The terms “specification control drawing” or “applicable design drawing” used in t

28、his document mean the design drawing prepared by and available from the procuring activity. 2.2.2 Normal Operating Pressure The term “normal operating pressure” means the brake hydraulic pressure required to produce an aircraft deceleration in accordance with the procurement document, as determined

29、by the average of the distance averaged pressure measurements in landplane landing design gross weight tests specified in 4.2.7. 2.2.3 Normal Parking Pressure The term “normal parking pressure” means the brake hydraulic pressure required to lock the wheel at the rated static load specified for the w

30、heel. _ SAE INTERNATIONAL ARP1493C Page 4 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-2.2.4 Maximum Operating Pressure The term “maximum operating pressure(s)” means the maximum brake hydrau

31、lic pressure(s) supplied at the brake under design conditions. 2.2.5 Weights and Speeds The weight conditions specified in Table 3 and related speeds should be used to establish design values. When the procurement document specifies more severe conditions these should be used instead. For speeds the

32、 values in Table 1 should be used: TABLE 1- WEIGHT AND SPEED CONDITIONS Condition Brakes on Speed Aircraft Weight Normal Landing 0.9 VaLPLGW Maximum Landing 0.9 VaMLGW Rejected Takeoff (RTO) 1.0 MWLO MTOGW Worn Brake RTO 1.0 MWLO MTOGW Rapid Turnaround (if required) Landing 0.9 VaLPLGW Taxi-In * LPL

33、GW Taxi-Out * MTOGW RTO 1.0 MWLO MTOGW where: Va - Standard day approach speed for related weight LPLGW = Landplane landing gross weight MLGW = Maximum landing gross weight MWLO = Rational main wheel lift off speed at sea level standard day or a specified by the procuring activity MTOGW - Maximum ta

34、keoff gross weight * = Brake energy is the total amount of braking required to oppose the idle thrust over the taxi distance and the number of anticipated stops during the taxi phase 2.2.6 Loads For the purpose of load testing, the following definitions will apply: a. Limit Load: The maximum load an

35、ticipated during all normal conditions of operation as determined by the procurement activity. It should be not less than the load determined by using AS8860 specification, JSSG-2006, or as defined in the aircraft detail specification. b. Yield Load: 1.15 times the limit load. c. Design Ultimate Loa

36、d: 1.5 times the limit load. d. Design landing loads will be as determined by the procurement activity in accordance with the load conditions of AS8860. _ SAE INTERNATIONAL ARP1493C Page 5 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or network

37、ing permitted without license from IHS-,-,-3. REQUIREMENTS The wheel and brake should fulfill all the regulatory and/or any airframe manufacturers design requirements that are considered applicable to the aircraft being designed. 3.1 Drawings 3.1.1 Design Proposal Drawings Design proposal drawings p

38、repared by the wheel and brake manufacturer should include the following: a. Reference to the applicable specification. b. End-view and cross-sectional drawing including definition of the rim flange, brake and wheel mounting, hydraulic interface data, and envelope definition. c. Material, principal

39、manufacturing process, and finish definition for all major components. d. Wheel static and dynamic loading conditions, brake energy definitions, separate and combined maximum weights for the wheel and brake assemblies. e. Brake design parameters, including: 1. Heat sink mass and definition of heat s

40、ink components, new and fully-worn 2. Swept area 3. Mean radius 4. Piston area f. Brake performance predictions, including: 1. Pressure-volume curve defining the pressure to begin brake piston movement 2. Pressure to cause disk contact 3. Brake release pressure (brake rotors are free to rotate) 4. M

41、aximum system pressure as prescribed by the procuring activity to provide full flow to allow for rudder, spoilers, speed brakes, etc. g. Other technical information required communicating the design 3.1.2 Interface Drawings Interface drawings should be developed and approved by the procuring activit

42、y that define the applicable interfaces with tolerances for the wheels and brakes. This should include but not limited to all interfaces with the axle, landing gear, hydraulic system, hub cap, brake temperature or tire pressure monitoring system as applicable. Component or assembly interface drawing

43、s suitable for alternate source procurement should be the subject of separate contract by specific request. _ SAE INTERNATIONAL ARP1493C Page 6 of 31Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.

44、2 Materials Unless otherwise specified in the procurement specification, the following materials are commonly used for the major components: a. Aluminum components: Forged aluminum alloys of 2040-T6, 7050-T74, 2014-T6 or 2014-T61 are suitable alloys for wheel halves and brake housings 3.3 Protective

45、 Treatment Unless otherwise specified in the procurement specification, aluminum alloy should be anodized in accordance with MIL-A-8625, Type II or III, all over after cold working. In addition, all exterior surfaces should be painted with one coat of MIL-PRF-23377 primer and two coats of MIL-PRF-85

46、285 urethane topcoat. 3.4 Detail Design Requirements 3.4.1 Wheel Design Requirements Wheel design should meet the specified requirements with all tire part numbers specified by the procuring agency. 3.4.1.1 Tie Bolts Wheel tie bolts, where used, should be of the through-type with nuts: no inserts should be permitted. If chamfered washers are used, they should be chamfered on both sides. Appropriate MS head form bolts should be used. Appropriate thread lubricant and tie bolt torque procedure (reference ARP5481) should be specified with appropriate substantia