SAE-ARP-1598A-1997-R2007.pdf
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1、AEROSPACE RECOMMENDED PRACTICE ARP1598 REV. A Issued1985-08 Revised1997-03 Reaffirmed2007-08 Superseding ARP1598 Landing Gear System Development Plan FOREWORD Changes in the revision are format/editorial only. INTRODUCTION The development of a landing gear system for a modern high performance air ve
2、hicle is an engineering and development process which covers many months in calendar time and also crosses over many disciplines and abilities. The process is subordinate to and dependent upon the plan for development of the vehicle itself. Good engineering design, analysis, and documentation will g
3、enerally identify most of the necessary parts of the development process and allow the design team to more effectively perform the task. The total plan is one which might be prepared by a contractor to describe a development program for a specific aircraft, and be submitted for approval before initi
4、ation of the actual work. The plan should be revised and updated at intervals during the development program as influencing factors dictate. A milestone chart should be a part of the plan and should show the interrelationship between phases of the development work to be performed. Design reviews sho
5、uld be identified and scheduled. The progressive design verification process to demonstrate compliance with requirements must be clearly delineated. The overall plan may cover as little time as several months but more probably as much as several years depending upon the complexity of the development
6、 and, of course, must fall within the constraints of the prime vehicle development plan. The development has been divided into six functional/chronological phases although each phase overlaps and affects the others. These general divisions are: Preliminary Design Design Integration Component Develop
7、ment Subsystem Developmen t“On Air Vehicle” Development Landing Gear System - In Service Reliability and Maintainability Discussion of these six major development phases is given in the following pages. SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the
8、 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 therefrom, is the sole responsibility of the user.” SAE reviews each technical report at least every fiv
9、e 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 may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electro
10、nic, 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) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org RATIONALE This
11、document has been reaffirmed to comply with the SAE 5-Year Review policy. Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:27:00 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP1598
12、 Revision A - 2 - 1.SCOPE: This Aerospace Recommended Practice (ARP) is therefore intended to document the process of landing gear system development. Some of the steps covered are mandatory and others are elective, or dependent upon customer requirements or desires. Economics is a very significant
13、factor and for each analysis or test performed, more confidence and assurance of success is gained, but at a price. Some of the steps are performed as a matter of “good engineering practice” and without special recognition. Others are unique to the particular landing gear system and all together com
14、prise a complete development. 2.REFERENCES: 2.1Applicable 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 shall be the issue in effect on the date of the pu
15、rchase 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 has been obtained. 2.1.1U.S. Government Publicat
16、ions: Available from DODSSP, Subscription Services Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094. MIL-L-87139 3.PRELIMINARY DESIGN: The preliminary design stage of an aircraft (and all of the systems which comprise the vehicle) is a process in which the designer strives for the
17、optimum overall arrangement to best meet the designated requirements. Adequate attention must be given the landing gear system at this time to prevent compromises which may eventually result in increased maintenance and reliability requirements, and excess weight. At the conclusion of the Preliminar
18、y Design phase the Preliminary Design Review (PDR) should be scheduled. 3.1Design (Preliminary): 3.1.1Documentation: In all stages of design, it is of paramount importance to establish the design requirement for the system and to document these requirements. This may be done in the form of a “System
19、 Definition Manual,” “Basic Data Manual,” or any similar form. This documentation, established at this point should be updated as the system design progresses. Initially, requirements only will be shown. Prior to completion of the PDR, the means by which each requirement will be verified, should be
20、identified. Copyright SAE International Provided by IHS under license with SAELicensee=Defense Supply Ctr/5913977001 Not for Resale, 12/04/2007 19:27:00 MSTNo reproduction or networking permitted without license from IHS -,-,- SAE ARP1598 Revision A - 3 - 3.1.2Geometric Arrangement: The geometric ar
21、rangement of the landing gear legs, structures, wheel arrangements, and other features which affect the vehicle/ground relationship including shock strut/tire/axle strokes should be established and shown on a layout type drawing. Careful consideration should be given to tip-back angle, turnover angl
22、e, center of gravity limits, ground clearance to deflected surfaces, landing attitude limits, and takeoff rotation limits. 3.1.3Tire/Wheel/Brake Sizing: Selection of tire and wheel size should be made in accordance with best weight and load information available, and revised as required during the P
23、/D phase until concept freeze. This must be done in conjunction with sizing the brake to fit the wheel cavity and meet design deceleration and kinetic energy and durability requirements. In sizing tires, particular attention must be given to ground flotation requirements, peak dynamic taxi and landi
24、ng loads, and takeoff load-speed-time curves. 3.1.4(N) (Additional Requirements for Carrier Based Aircraft): The tire/wheel must be selected to be compatible with deck strength, cable crossing, and catapulting. 3.1.5Ground Flotation: Tire/wheel sizing and arrangement must be selected in a manner com
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