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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 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 reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions. Copyright 2007 SAE International All rights reserved. No part of this publication m
3、ay 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: 724-776-4970 (outside USA)
4、 Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org ARP4955 REV. A AEROSPACE RECOMMENDED PRACTICE Issued 1997-12 Reaffirmed 2002-07 Revised 2007-08 Superseding ARP4955 (R) Recommended Practice for Measurement of Static and Dynamic Characteristic Properties of Aircraft
5、 Tires RATIONALE Tire designers and aircraft landing gear analysts must have knowledge of static and dynamic properties of aircraft tires to adequately address technical issues associated with takeoff, landing and taxi operations. For example, tire mechanical properties are fundamental to modeling a
6、ircraft ground handling characteristics such as cross- wind landing performance and aircraft maneuverability on runways or taxiways. Tire properties are key design parameters for nose-gear and main-gear steering systems and for antiskid braking systems. These tire properties are also fundamental to
7、landing gear shimmy analyses. TABLE OF CONTENTS 1. SCOPE.4 2. REFERENCES.4 2.1 Applicable Documents4 2.1.1 SAE Publications4 2.1.2 NASA Publications .4 2.1.3 U.S. Government Publications .5 2.2 Other Applicable References .5 2.3 Symbols5 3. TIRE PREPARATION.7 3.1 Tire Conditioning 7 3.2 Tire Inflati
8、on and Ambient Temperature.7 3.3 Break-in Procedure.7 3.3.1 Break-in Procedure - Static Testing Only.7 3.3.2 Break-In Procedure - Dynamic or Alternate Static Testing 7 4. STATIC PROPERTY TESTS .7 4.1 Loading Apparatus .7 4.1.1 Loading Plate9 4.2 Vertical Load Deflection Curves.9 4.2.1 Vertical Load
9、Deflection Curves.9 4.2.2 Vertical Spring Rate9 4.2.3 Bottoming Point 9 4.3 Non Rolling Lateral Load - Deflection Curves11 4.3.1 Definition of Lateral Deflection .11 4.3.2 Obtaining Lateral Load Deflection Curves .11 4.3.3 Obtaining Lateral Damping.12 4.3.4 Lateral Spring Rate.12 4.3.5 Vertical Sink
10、age13 4.4 Measurement of Shift of the Contact Patch Centroid During Lateral Loading.13 4.5 Non-Rolling Fore and Aft Load Deflection Curves.14 4.5.1 Definition of Fore-Aft Deflection .14 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for R
11、esale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP4955 Revision A - 2 - 4.5.2 Method for Determining Fore-Aft Load Deflection Curves.14 4.5.3 Obtaining Fore and Aft Damping15 4.5.4 Fore-Aft Spring Rate.15 4.5.5 Vertical Sinkage15 4.6 Measurem
12、ent of the Shift of the Contact Patch Centroid During Fore-Aft Loading.15 4.7 Measurement of Brake Torque Radius 16 4.8 Non-Rolling Torsional Load Deflection.16 4.8.1 Equipment Description .17 4.8.2 Applicable Range of Measured Parameters 17 4.8.3 Test Procedure.17 4.8.4 Data Reduction.18 5. ROLLING
13、 TIRE MECHANICAL PROPERTY TESTS19 5.1 Yawed-Rolling Relaxation Length19 5.1.1 Equipment Description .19 5.1.2 Applicable Range of Measured Parameters 20 5.1.3 Test Procedure.20 5.1.4 Data Reduction.20 5.2 Unyawed-Rolling Relaxation Length22 5.2.1 Equipment Description .23 5.2.2 Applicable Range of M
14、easured Parameters 23 5.2.3 Test Procedure.23 5.2.4 Data Reduction.23 5.3 Rolling Cornering Properties24 5.3.1 Equipment Description .25 5.3.2 Applicable Range of Measured Parameters 25 5.3.3 Test Procedures.26 5.3.4 Data Reduction.27 5.4 Rolling Radius 27 5.4.1 Free Rolling Radius28 5.4.2 Yawed or
15、Braked Rolling Radius29 5.5 Rolling Resistance30 5.5.1 Equipment Description .30 5.5.2 Applicable Range of Measured Parameters 30 5.5.3 Test Procedures.31 5.6 Dynamic Tire Shimmy Properties.31 5.6.1 Kinematical Parameters .31 5.6.2 Static Measurements31 5.6.3 Tire Model Parameters.31 5.6.4 Test Proc
16、edure.32 5.6.5 Measurements33 5.6.6 Data Reduction.33 5.6.7 Synthesis of Tire Properties .34 6. NOTES .35 FIGURE 1 LEAST-SQUARES APPROXIMATION OF HYSTERESIS LOOPS DURING CYCLIC LOADING.8 FIGURE 2 LOAD MACHINE CONFIGURATION.8 FIGURE 3 APPROXIMATION OF BOTTOMING POINT.10 FIGURE 4 LOCATION OF METAL STR
17、IPS11 FIGURE 5 TYPICAL LATERAL AND FORE-AFT HYSTERESIS LOOP.12 FIGURE 6 FORCES AND MOMENTS IN VERTICAL PLANE PERPENDICULAR TO WHEEL PLANE14 FIGURE 7 FORCES AND MOMENTS IN VERTICAL PLANE PARALLEL TO WHEEL PLANE16 FIGURE 8 TORSIONAL STIFFNESS CHARACTERISTICS.18 FIGURE 9 TORSIONAL HYSTERESIS LOOP19 FIG
18、URE 10 TYPICAL TEST DATA21 FIGURE 11 UNYAWED ROLLING RELAXATION 22 FIGURE 12 FORCES AND MOMENT IN THE TIRE AT AXLE.24 Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitte
19、d without license from IHS -,-,- SAE ARP4955 Revision A - 3 - FIGURE 13 SCHEMATIC OF INSTRUMENTED DYNAMOMETER USED TO MEASURE TIRE CORNERING CHARACTERISTICS.26 FIGURE 14 VARIATION OF SIDE-FORCE FRICTION COEFFICIENT OF THE SPACE SHUTTLE ORBITER NOSE GEAR TIRE WITH VERTICAL LOAD AND YAW ANGLE.27 Copyr
20、ight SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP4955 Revision A - 4 - 1. SCOPE The purpose of this SAE Aerospace Recommended Practi
21、ce (ARP) is to establish guidelines for the measurement of static and dynamic characteristic properties of aircraft tires. It is intended as a general guide toward standard practice, but may be subject to frequent changes to keep pace with experience and technical advances. This revision (Revision A
22、) is also intended to provide suggested guidelines for synthesizing tire dynamic data necessary for landing gear shimmy analyses. 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
23、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 document takes precedence. Nothing in this document, however, supersedes applicab
24、le laws and regulations unless a specific exemption has 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. 2.1.1.1 SAE J670e Vehicle Dynamics
25、Terminology, 1976 2.1.1.2 SAE 1999-01-5527 An Investigation of Landing Gear Shimmy: Tire Models, Tire Test Methodologies, Analysis and Parameter Studies, John Medzorian, 1991 2.1.1.3 SAE 961300 Relaxation Behavior of Aircraft Tires, C. B. Alsobrook and M. G. Vogel, 1996 2.1.1.4 SAE 2005-01-3438 Mech
26、anical Properties of Radial-Ply Aircraft Tires, John Tanner, Robert Daugherty, Henry Smith, 2005 2.1.2 NASA Publications Available from NASA, Documentation, Marshall Space Flight Center, AL 35812, www.nas.nasa.gov. 2.1.2.1 NASA TR R-64 Mechanical Properties of Pneumatic Tires with Special Reference
27、to Modern Aircraft Tiress, Robert Smiley, Walter Horne, 1960 2.1.2.2 NASA TP 1863 Static and Yawed Rolling Mechanical Properties of Two Type VII Aircraft Tires, John Tanner, Sandy Stubbs, John McCarty, 1981 2.1.2.3 NASA TP 1917 Cornering of the Nose-Gear Tire of the Space Shuttle Orbiter, William Vo
28、gler, John Tanner, 1981 2.1.2.4 NASA TM 1999-209141 Quasi-Static Viscoelastic Finite Element Model of an Aircraft Tire, Arthur Johnson, John Tanner, Angela Mason, 1999 2.1.2.5 NASA TM 2003-212415 A Study of the Mechanical Properties of Modern Radial Aircraft Tires, Robert Daugherty, 2003 Copyright S
29、AE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP4955 Revision A - 5 - 2.1.3 U.S. Government Publications Available from the Document Auto
30、mation and Production Service (DAPS), Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697-6257, http:/assist.daps.dla.mil/quicksearch/. 2.1.3.1 MIL-PRF-5041 Military Specification for Tires, Pneumatic, Aircraft 2.1.3.2 DOT HS 905 952 Mechanics of Pneumatic Tires, Samuel Clark
31、, 1981 2.2 Other Applicable References 2.2.1 J. of Aircraft, Vol.8, No. 9 Synthesis of Tire Equations for Use in Shimmy and Other Dynamic Studies; L. C. Rogers, H. K. Brewer, 1971 2.2.2 J. of Aircraft, Vol. 6, No. 3 Tire Parameters for Landing-Gear Shimmy, R. L. Collins, R. J. Black, 1969 2.3 Symbol
32、s A1 constant depending on initial tire distortion A2 constant depending on the initial lateral force Afy side force amplitude ratio Amz aligning moment amplitude ratio C cornering stiffness C1 zero offset C2 initial tire lateral force Dfy -tan( fy ) 0 Dmz -tan( mz ) 0 F0 steady state force Fd drag
33、force (parallel to the wheel plane) Fs side force (perpendicular to the wheel plane) Fx fore and aft force Fy lateral force Fz vertical load H tire footprint half length h loaded radius, axle height Kl lateral stiffness Kt torsional stiffness Copyright SAE International Provided by IHS under license
34、 with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP4955 Revision A - 6 - Kx fore and aft stiffness L relaxation length Lf unyawed rolling relaxation length Ly yawed-rolling relaxation le
35、ngth Mfy Afy 0 Mmz -Amz 0 Mx overturning moment My brake torque r tire undeflected radius RBT brake torque radius re effective rolling radius reb effective braked rolling radius rey effective yawed rolling radius t time V horizontal velocity of wheel x distance rolled xc fore-aft shift of the center
36、 of pressure yc lateral shift of the center of pressure wheel slip angle = angle between SAE X axis and velocity of wheel plane on ground vector (rad) a maximum amplitude of twist during oscillation m mean tire twist lateral displacement of footprint tire deflection mz aligning moment phase angle fy
37、 side force phase angle phase angle t torsional damping coefficient x fore and aft damping coefficient Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitted without licen
38、se from IHS -,-,- SAE ARP4955 Revision A - 7 - wavelength = yaw oscillation frequency / longitudinal velocity a wheel yaw amplitude yaw angle t tire twist angle angular velocity of wheel yaw rate 3. TIRE PREPARATION 3.1 Tire Conditioning Before break-in, the tire shall be conditioned by mounting on
39、its design rim and inflating it to the rated inflation pressure. The tire shall be allowed to remain in this condition for 24 h at an ambient temperature ranging from 60 to 100 F (15.6 to 37.8 C). 3.2 Tire Inflation and Ambient Temperature After the tire has been conditioned for 24 h on the design r
40、im as indicated in 4.1, the tire pressure shall be readjusted to the rated inflation pressure with a gauge which has been calibrated to within 1%. All tests shall be carried out at temperatures range of 60 F (15.6 C) to 100 F (37.8 C). 3.3 Break-in Procedure 3.3.1 Break-in Procedure - Static Testing
41、 Only This method of tire break-in prepares the test tire by inflating it to rated inflation pressure and loading the tire under direct vertical load against a hard, flat, unyielding surface to the point that the tire deflection measures 50% of the section height. The load is then removed. This load
42、-deflection procedure is carried out five times each at two locations equally spaced around the tire, with the centerline of the contact patch being located at 180 degree intervals around the circumference of the tire. When the tire has been unloaded for 1 h or more, the break-in procedure should be
43、 repeated before resuming static loading testing. Figure 1 illustrates the effect of this break-in procedure on the hysteresis characteristics of the tire vertical load-deflection curve. 3.3.2 Break-In Procedure - Dynamic or Alternate Static Testing This method of tire break-in prepares the test tir
44、e by inflating it to rated inflation pressure, corrected for flywheel curvature, then performing five rated load take-off cycles of a load-speed-time curve representative of the applicable aircraft. 4. STATIC PROPERTY TESTS 4.1 Loading Apparatus The tire is to be mounted on either a suitable yoke or
45、 a mandrel and loaded vertically against a hard, flat, unyielding surface under a camber angle of 0 1/4, and under a caster angle of 0 1/4 (see Figure 2). The load measuring system shall be accurate within 1% of the load applied to the tire. If a mandrel type axle is used in the testing equipment, c
46、ompensation should be made for the resulting axle deflection created during the loading of the tires. Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:56:48 MSTNo reproduction or networking permitted without licens
47、e from IHS -,-,- SAE ARP4955 Revision A - 8 - FIGURE 1 - LEAST-SQUARES APPROXIMATION OF HYSTERESIS LOOPS DURING CYCLIC LOADING FIGURE 2 - LOAD MACHINE CONFIGURATION Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:
48、56:48 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP4955 Revision A - 9 - 4.1.1 Loading Plate The surface of the plate in contact with the tire shall be a smooth metal plate. Other surfaces may be used in lieu of this surface but must be noted with the reporting of the data. Any contamination of th