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 2016 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/ARP5632AEROSPACERECOMMENDED PRACTICEARP5632Issued 2010-01Reaffirmed 2016-04Rotorcraft: Applic
5、ation of Existing Aircraft Designed Tires, Wheels and BrakesRATIONALEARP5632 has been reaffirmed to comply with the SAE five-year review policy.TABLE OF CONTENTS 1. SCOPE 3 1.1 Purpose . 3 2. APPLICABLE DOCUMENTS 3 2.1 SAE Publications . 3 2.2 U.S. Government Publications 4 2.3 Definitions See defin
6、itions in AIR1489. 4 3. TECHNICAL REQUIREMENTS 5 3.1 Drawings . 5 3.1.1 Design Proposal Drawings 5 3.1.2 Interface Drawing 6 4. DETAIL REQUIREMENTS . 6 4.1 Wheels 6 4.1.1 Radial Static Load (Yield Paragraphs AC 27.731 Wheels, AC27.733 Tires and AC 27.735 Brakes AC 29-2C Certification of Transport Ca
7、tegory Rotorcraft; Paragraphs AC 29.731 Wheels, AC 29.733 Tires and AC 29.735 Brakes Title 14 Part 23 Airworthiness Standards: Normal, Utility, Acrobatic, and Commuter Category Airplanes; Paragraphs 23.731 Wheels, 23.733 Tires and 23.735 Brakes Title 14 Part 25 Airworthiness Standards: Transport Cat
8、egory Airplanes; Paragraphs 25.731 Wheels, 25.733 Tires and 25.735 Brakes TSO-C26 Aircraft Wheels and Brakes TSO-C62 Aircraft Tires 2.2.2 DoD Publications Available from the Document Automation and Production Service (DAPS), Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697
9、-6257, http:/assist.daps.dla.mil/quicksearch/. MIL-PRF-5606 Hydraulic Fluid, Petroleum Base; Aircraft, Missile, And Ordnance MIL-B-8075 Brake Control Systems, Antiskid, Aircraft Wheels, General Specification For MIL-B-8584 Brake Systems, Wheel, Aircraft Design Of MIL-PRF-83282 Hydraulic Fluid, Fire
10、Resistant, Synthetic Hydrocarbon Base MIL-PRF-87257 Hydraulic Fluid, Fire Resistant; Low Temperature, Synthetic Hydrocarbon Base, Aircraft And Missile MIL-PRF-5041 Tires, Ribbed Tread, Pneumatic, Aircraft MIL-W-5013 Wheel and Brake Assemblies Aircraft, General Specification For 2.3 Definitions See d
11、efinitions in AIR1489. SAE INTERNATIONAL ARP5632 4 OF 113. TECHNICAL REQUIREMENTS 3.1 Drawings 3.1.1 Design Proposal Drawings Design proposal drawings prepared by the tire, wheel and/or brake manufacturer(s) for the existing products should include the following: a. Reference the application and the
12、 origin of the proposed existing product. b. All qualification and/or certification data of the proposed existing product. c. Two-view and cross-sectional drawings including definition of the rim, flange, brake and wheel mounting, hydraulic installation data, envelope, interface dimensions and defin
13、itions. d. Material, principal manufacturing process and finish definitions for all major components. e. Wheel static and dynamic loading conditions, brake energy definitions, separate and combined maximum weights for the existing wheel and brake assemblies. f. Brake design parameters including: 1)
14、Heat sink mass and definition of heat sink components. 2) New and worn. 3) Swept area. 4) Mean radius. 5) Piston area. g. Brake performance predictions including: 1) Pressure-volume curve defining the pressure to begin brake piston movement. 2) Dynamic and static torque vs. brake pressure curves. 3)
15、 Pressure to cause disk contact. 4) Brake release pressure. 5) Maximum system pressure at full flow and at no flow. h. Tire performance parameters (1) Load deflection curves. (2) Rated and service pressures. (3) Rated speed. (4) Service loads. i. Other technical information required to communicate t
16、he design. SAE INTERNATIONAL ARP5632 5 OF 113.1.2 Interface Drawing Component and/or assembly interface drawings suitable for alternate source procurement shall be provided by the procuring agency. 4. DETAIL REQUIREMENTS Detail requirements are outlined in the following paragraphs that are unique or
17、 different for rotorcraft applications. These requirements along with additional contractual details are to be defined in detail documentation (contract, procurement specification and interface drawing) by the procuring agency. Detail requirements can be satisfied by additional testing and/or analys
18、is of the existing product that is already qualified or certified for use on an existing fixed winged aircraft. These requirements can be demonstrated by performing additional tests and/or by a report of similarity. Test results and data to support and substantiate the contractual requirements to be
19、 included in the similarity report. Compliance with these minimum performance requirements by manufacturers is recommended as a means of assuring that the equipment will have the capability to satisfactorily perform its intended function(s). NOTE: Aircraft operational characteristics and other exter
20、nal influences may affect performance capabilities. Consequently, anticipated rotorcraft performance should be verified by flight testing. 4.1 Wheels 4.1.1 Radial Static Load (Yield hardware should be compatible with MIL-PRF-5606, MIL-PRF-83282 and MIL-PRF-87257. If the fixed wing aircraft uses a di
21、fferent hydraulic fluid, then a seal change is required to assure fluid - seal compatibility. If the seal glands were manufactured to standard dimensions only a seal material change is required to assure fluid - seal compatibility for rotorcraft application(s). 4.2.2 Design Landing Test Fixed wing a
22、ircraft requirements are - 100 stops at a mean deceleration of not less than 10 ft/sec2. One lining change permitted unless the heat stack is carbon. Rotary wing requirements are - 100 stops at a mean deceleration of not less than 6 ft/sec2(1.83 m/sec2) with no lining change is permitted. (ARP5381).
23、 Recommend rotorcraft performance in accordance with ARP5381. 4.2.3 Rejected Takeoff Energy Evaluate and analyze fixed wing brakes for rotorcraft using maximum gross STOL (Short Take Off or Landing) or VTOL (Vertical Take Off or Landing) weight, whichever is greater at aborted take-off velocity. 4.2
24、.4 Turn-Around Takeoff Time Evaluate and analyze fixed wing brakes for rotorcraft use, turn around take-off time to be less than 15 minutes. 4.2.5 Static Torque Performance (Hot/Cold/Wet) Evaluate and analyze fixed wing brakes for rotorcraft use, retain static torque performance of aircraft from whi
25、ch the components were adopted. 4.2.6 Dynamic Braking Performance (Wet/Dry, Deceleration) Evaluate and analyze fixed wing brakes for rotorcraft use, retain dynamic braking performance of aircraft from which the components were adopted. 4.2.7 Endurance Performance (Wet/Dry, Deceleration) Fixed wing a
26、ircraft requirements are 100 000 cycles at rated design landing pressure. Adjust at every 25 000 cycles for wear at 25%, 50%, and 75% and at 100% wear limit. Also, 5000 cycles at rated maximum pressure. Rotary wing requirements are 50 000 cycles at rated design landing pressure. Adjust at every 12 5
27、00 cycles for wear at 25%, 50% and 75% and at 100% wear limit. Also, 2500 cycles at rated maximum pressure. (ARP5381) Recommend rotorcraft performance in accordance with ARP5381. 4.2.8 Spectrum Dynamic Torque Test A dynamic torque test should be conducted in order to duplicate service type energy in
28、put as specified by the procuring activity. The entire test should be conducted with the same inertia equivalent as used for landing design gross weight. The test sequence, the number of stops and the data requirements are to be determined by the procuring activity. 4.2.9 Parking Hold Recommend roto
29、rcraft performance in accordance with ARP5381. 20 degree slope overpressure (TSO-C26 and ARP5381) or 10 degree slope (AC29.735, FAR PART 27.735 and AC No: 27.735). 4.2.10 Structural Torque Requirements Evaluate and analyze fixed wing brakes for rotorcraft use, wheel rated radial load for at least 3
30、seconds. (ARP5381) SAE INTERNATIONAL ARP5632 8 OF 114.2.11 Overpressure Tests Evaluate and analyze fixed wing brakes for rotorcraft use, recommend rotorcraft performance in accordance with ARP5381. Fixed wing - 2.0 times the brake rated maximum pressure. Rotorcraft - 2.0 times the brake rated minimu
31、m slope pressure or 2.0 times the brake rated maximum pressure whichever is greater. (ARP5381) 4.2.12 Overall Size Envelope High flotation tire deflection envelope should be maintained to avoid wheel and or brake to tire contact. Maintain clearance envelope throughout wheel/axle stroke. Allow suffic
32、ient component clearance due to deflection(s) at high loads. 4.2.13 Corrosion Resistance Requirements Consider trapped cavities for moisture, salt and debris as this may severely impact utilization of fixed wing components for rotorcraft applications. Brakes will frequently be submerged in mud, sand
33、, snow and water. Rotor downwash has a tendency to sand/grit blast and generally deposit corrosive substances in every hidden area. Assure compatibility with fuel, hydraulic fluids, decontamination and de-icing fluids. 4.2.14 Fluid Displacement/Running Clearance Requirements Retain displacement/runn
34、ing clearance of aircraft from which the components were adopted from, avoid brake heat stack drag. 4.2.15 Brake Pressure vs. Torque Requirements Evaluate and analyze fixed wing brakes for rotorcraft use, retain brake pressure vs. torque requirements of aircraft from which the components were adopte
35、d. 4.2.16 Temperature Extremes Evaluate and analyze fixed wing brakes for rotorcraft use, performance to be consistent with ambient temperature extreme range of -65 F (-54.9 C) to +180 F (82.2 C). 4.2.17 Anti-Skid Requirements Anti-skid is not required for rotorcraft, however the following guideline
36、s should be used if anti-skid is desired. The wheel and brake assembly should be designed to operate satisfactorily with an anti-skid control system provided in accordance with MIL-B-8075. Dynamometer testing should be conducted to determine the compatibility of the anti-skid system when installed a
37、nd the brake designed to this specification. As a minimum, dynamometer stops should be run simulating wet and dry brake stack condition, wet and dry runway condition at both landing speed and one-half landing speed. Simulate aircraft hydraulic system. The tests should demonstrate full brake torque c
38、ontrol for maximum runway friction under all conditions. A test plan should be coordinated with and be approved by the procuring activity before start of testing. (MIL-W-5013) 4.2.18 Reliability Requirements The reliability requirements imposed by the rotorcraft platform procurement agency on which
39、the brakes are intended to be used should be retained and analyzed for verification. 4.2.19 Leakage Requirements Evaluate and analyze fixed wing brakes for rotorcraft use, during endurance tests, if performed or by similarity leakage at static seals shall not exceed a trace. Leakage at moving seals
40、shall not exceed one drop per inch of peripheral length at each condition of wear limit or 0.3 in3(5 cc) total. During leakage tests the brake shall be subjected to an operating pressure equal to 1.5 times brake rated maximum pressure (BRPMAX ) for 5 minutes. The brake pressure shall then be adjuste
41、d to an operating pressure of 5 psig (35 kPa) for 5 minutes. There shall be less than one drop leakage per seal and no permanent set of the structural components during this test. (ARP5381) SAE INTERNATIONAL ARP5632 9 OF 114.2.20 Capacity/Performance Growth Considerations Unless otherwise specified
42、by the procuring activity, capacity/performance growth considerations should not be taken into account in the selection process of a suitable brake assembly. However, given the provisions of this ARP, a level of inherent capacity/performance above the minimum requirement could result and thereby pro
43、vide a growth potential on the rotorcraft for which the brake is intended. The supplier therefore should disclose the capacity/performance growth of the procured hardware. This will allow the procuring agency to utilize existing equipment with a known history and braking capacity. 4.2.21 Handed Part
44、s are to be non-handed, such that an assembly may be readily interchanged on axles independent of part orientation, subject to exception from the design authority. 4.3 Tires 4.3.1 Static Load Rating Static loading may be increased up to 1.50 times the published maximum aircraft tire load rating for
45、the selected tire as long as a corresponding increase is made in the recommended inflation pressure. For the selected, existing tire applied to a rotorcraft, define the maximum static load. 4.3.2 Cable Bruise Test (Carrier-Based Rotorcraft Only) At carrier inflation pressures, the tire manufacturer
46、shall provide (1) a vertical load-deflection curve and table; 2) when loading against a 1.625 inch (41.3 mm) diameter plain round steel stock or carrier cable, a vertical load-deflection curve and table. Repeat 180 degrees away from initial load point. (MIL-PRF-5041) 4.3.3 Inflation Tire inflation p
47、ressures should be increased by the same ratio above the published rated inflation pressure as the load is increased above the published load rating as stated in paragraph 4.3.1. Over Pressurization: For the selected, existing tire, report the minimum burst pressure level. To achieve a minimum safet
48、y level, this value should be at least 3 times the maximum permissible inflation pressure. The maximum permissible inflation pressure for tires used on rotorcraft is 1.8 times the normal aircraft rated inflation pressure. 4.3.4 Dimensions For the selected tire, report the maximum new tire dimensions
49、 outside diameter, section width, and shoulder point - at the maximum permissible inflation pressure, after a standard growth period. Maximum dimensions of aircraft tires used on rotorcraft are permitted to grow 4% greater than the aircraft standard tire dimensions due to the higher inflation pressures permitted when used on rotorcraft. 4.3.5 Overall Size Envelope, Tire Size The tire deflection and clearance envelope sha
