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1、Standard ANSI/AIAA S-096-2004 AIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 1801 Alexander Bell Drive, Reston, VA 20191-4344 USA. All rights reserved. AIAA grants you a license as follows: The right to download an electronic file of this AIAA standa
2、rd for temporary storage on one computer for purposes of viewing, and/or printing one copy of the AIAA standard for individual use. Neither the electronic file nor the hard copy print may be reproduced in any way. In addition, the electronic file may not be distributed elsewhere over computer networ
3、ks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. Space Systems Flywheel Rotor Assemblies Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111
4、001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IHS -,-,- ANSI/AIAA S-096-2004 American National Standard Space Systems Flywheel Rotor Assemblies Sponsored by American Institute of Aeronautics and Astronautics Approved 30 Nov
5、ember 2004 American National Standards Institute Abstract This standard establishes baseline requirements for the design, fabrication, test, inspection, storage, and transportation of a flywheel rotor assembly used in a spaceflight flywheel system for energy storage and/or attitude control. These re
6、quirements when implemented on a particular system will assure a high level of confidence in achieving safe and reliable operation. Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale
7、, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IHS -,-,- ANSI/AIAA S-096-2004 ii Approval of an American National Standard requires verification by ANSI that the requirements for due process, consensus, and other criteria have been met by the standards develope
8、r. Consensus is established when, in the judgment of the ANSI Board of Standards Review, substantial agreement has been reached by directly and materially affected interests. Substantial agreement means much more than a simple majority, but not necessarily unanimity. Consensus requires that all view
9、s and objections be considered, and that a concerted effort be made toward their resolution. The use of American National Standards is completely voluntary; their existence does not in any respect preclude anyone, whether he has approved the standards or not, from manufacturing, marketing, purchasin
10、g, or using products, processes, or procedures not conforming to the standards. The American National Standards Institute does not develop standards and will in no circumstances give an interpretation of any American National Standard. Moreover, no person shall have the right or authority to issue a
11、n interpretation of an American National Standard in the name of the American National Standards Institute. Requests for interpretations should be addressed to the secretariat or sponsor whose name appears on the title page of this standard. CAUTION NOTICE: This American National Standard may be rev
12、ised or withdrawn at any time. The procedures of the American National Standards Institute require that action be taken to affirm, revise, or withdraw this standard no later than five years from the date of approval. Purchasers of American National Standards may receive current information on all st
13、andards by calling or writing the American National Standards Institute. Library of Congress Cataloging-in-Publication Data American national standard space systems : flywheel rotor assemblies / sponsored by American Institute of Aeronautics and Astronautics. p. cm. ISBN 1-56347-741-6 (hardcopy) - I
14、SBN 1-56347-742-4 (electronic) 1. Space vehicles-Attitude control systems-Equipment and supplies-Standards-United States. 2. Space vehicles-Auxiliary power supply-Equipment and supplies-Standards-United States. 3. Flywheels-Standards- United States. 4. Rotors-Standards-United States. I. American Ins
15、titute of Aeronautics and Astronautics. TL3260.A45 2004 629.474-dc22 2004027019 Published by American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Reston, VA 20191 Copyright 2004 American Institute of Aeronautics and Astronautics All rights reserved No part of this publicatio
16、n may be reproduced in any form, in an electronic retrieval system or otherwise, without prior written permission of the publisher. Printed in the United States of America American National Standard Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA
17、Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IHS -,-,- ANSI/AIAA S-096-2004 iii Contents Foreword v 1 Scope 1 2 Applicable Documents1 3 Vocabulary 1 3.1 Abbreviations and Acronyms .1 3.2 Terms
18、 and Definitions.2 4 General Requirements .5 4.1 Design Requirements.5 4.1.1 System Analysis5 4.1.2 Loads, Speeds and Environments.6 4.1.3 Strength.6 4.1.4 Static Stiffness 6 4.1.5 Rotor Dynamics 6 4.1.6 Thermal .7 4.1.7 Static Strength Margin of Safety 7 4.1.8 Fracture Control*.7 4.1.9 Fatigue Life
19、8 4.1.10 Time Dependent Behavior8 4.1.11 Stress-Rupture Life.8 4.1.12 Corrosion and Stress Corrosion Control and Prevention .8 4.1.13 Outgassing8 4.2 Materials Requirements9 4.2.1 Metallic Materials9 4.2.2 Composite Materials.9 4.2.3 Ceramic Materials.10 4.2.4 Polymeric Materials 11 4.3 Fabrication
20、and Process Control11 4.4 Quality Assurance.12 4.4.1 Inspection Plan .12 4.4.2 Inspection Techniques12 4.4.3 Inspection Data.12 4.4.4 Traceability* 12 4.5 Repair and Refurbishment .13 4.6 Storage Requirements13 4.7 Transportation Requirements.13 Copyright American Institute of Aeronautics and Astron
21、autics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IHS -,-,- ANSI/AIAA S-096-2004 iv 5 Verification Requirements 13 5.1 Design Requirements Verificatio
22、n13 5.1.1 System Analysis Verification13 5.1.2 Loads, Speeds and Environments Verification .14 5.1.3 Strength Verification .14 5.1.4 Static Stiffness Verification.14 5.1.5 Rotor Dynamics Verification.14 5.1.6 Thermal Verification15 5.1.7 Static Strength MoS Verification 15 5.1.8 Fracture Control Ver
23、ification*.16 5.1.9 Fatigue Life Verification17 5.1.10 Time Dependent Behavior Verification17 5.1.11 Stress-Rupture Life Verification .17 5.1.12 Corrosion and Stress Corrosion Control and Prevention Verification17 5.1.13 Outgassing Verification.17 5.2 Acceptance Tests.17 5.2.1 Inspection18 5.2.2 Pro
24、of Spin Test .18 5.2.3 Modal Test.18 5.3 Qualification Tests 18 5.3.1 Inspection19 5.3.2 Proof Spin Test .19 5.3.3 Thermal Vacuum Tests 19 5.3.4 Vibration and Shock Tests .19 5.3.5 Damage Tolerance (Safe-Life) Test*.19 5.3.6 Modal Test.19 5.3.7 Ultimate Load Test19 Tables Table 1 Design Requirements
25、 Verification Matrix.15 Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IHS -,-,- ANSI/AIAA S-
26、096-2004 v Foreword This Standard establishes baseline requirements for the design, fabrication, test, inspection, storage, and transportation of a flywheel rotor assembly used in a spaceflight flywheel system for energy storage and/or attitude control. These requirements when implemented on a parti
27、cular system will assure a high level of confidence in achieving safe and reliable operation. The development effort of this Standard was one of the major activities of the Flywheel Rotor Safety and Longevity (FRSL) Working Group which was formed in June 2000 with the emphasis on inclusion of aerosp
28、ace prime companies, flywheel rotor suppliers, university researchers and all interested government agencies. James Chang is the Chairman of this Working Group. Jennifer Ratner is the Secretary and David Christopher is the Technical Advisor. Kerry McLallin and Jerry Fausz are the government sponsors
29、. At the time of document preparation, the members of the AIAA Flywheel Rotor Safe-Life Standards Working Group were: James B. Chang, Chair The Aerospace Corporation Charles Bakis Penn State Univ Norman Brackett Beacon Power Corporation John Coyner AFS Trinity Power Corp Dean Flanagan Flywheel Energ
30、y Systems, Inc. Yasser Gowayed Auburn University Joseph Klupar Honeywell Kevin Konno NASA Glenn Research Center Kerry McLallin NASA Glenn Research Center Jennifer Ratner The Aerospace Corporation James Schindler Boeing Phantomworks Carlos Stevens Honeywell Satellite Systems Richard Thompson Universi
31、ty of Texas - Center for Electromechanics Jerome Tzeng U.S. Army Research Lab Jeff Welsh AFRL, Space Vehicles Directorate David Zimcik National Research Council Canada The above consensus body approved this document in June 2004. The AIAA Standards Executive Council (Mr. Phil Cheney, chairman) accep
32、ted the document for publication in October 2004. The AIAA Standards Procedures dictates that all approved Standards, Recommended Practices, and Guides are advisory only. Their use by anyone engaged in industry or trade is entirely voluntary. There is no agreement to adhere to any AIAA standards pub
33、lication and no commitment to conform to or be guided by standards reports. In formulating, revising, and approving standards publications, the committees on standards will not consider patents that may apply to the subject matter. Prospective users of the publications are responsible for protecting
34、 themselves against liability for infringement of patents or copyright or both. Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networki
35、ng permitted without license from IHS -,-,- Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IH
36、S -,-,- ANSI/AIAA S-096-2004 1 1 Scope This document establishes a top level certification standard for the design, analysis, material selection and characterization, fabrication, test and inspection of the flywheel rotor assembly (FRA) in a flywheel used for energy storage and/or attitude control i
37、n manned and unmanned space systems. This standard, when implemented on an FRA in a particular flywheel system, can assure a high level of confidence in achieving safe and reliable operation. This document may also be applicable to flywheel systems used in aircraft, mobile, stationary and subterrane
38、an applications if appropriate changes are agreed to between the responsible authority and the flywheel developer. This document applies specifically to FRAs in flywheels used in space flight applications. The standard is applicable to the parts in the FRA, which rotate under normal operating condit
39、ions. Included are rim, hub and/or shaft, and other associated rotating parts such as the rotating bearing components and the motor generator rotor. This document does not include verification requirements applicable to the system level of the flywheel. At the flywheel system level, the qualificatio
40、n and acceptance test requirements specified in MIL-STD- 1540 are applicable. 2 Applicable Documents The following documents contain provisions which, through reference in this text, constitute provisions of this standard. For dated references, subsequent amendments to, or revisions of, any of these
41、 publications do not apply. However, parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references, the latest edition of the normative document referred to applies. M
42、IL-STD-1540 Military Standard, Test Requirements for Launch, Upper-Stage, and Space Vehicle MIL-STD-1629 Failure Modes and Effects Criticality Analysis MIL-HDBK-5 Military Handbook, Metallic Material and Elements for Aerospace Vehicle Structures MIL-HDBK-17 Defense Department Handbook, Polymer Matri
43、x Composites MIL-HDBK-340 Military Handbook, Test Requirements For Launch, Upper Stage or of low released energy; or if the part is failsafe; or if there is only a remote possibility of significant crack growth on the part to begin with. Fracture Mechanics an engineering discipline which describes t
44、he behavior of cracks or crack-like defects in materials under stress Fracture Toughness a generic term for measurements of resistance to extension of a crack Impact Damage damage in a non-metallic part within the FRA that is caused by an object striking on the part or the part striking on an object
45、 Copyright American Institute of Aeronautics and Astronautics Provided by IHS under license with AIAA Licensee=IHS Employees/1111111001, User=Wing, Bernie Not for Resale, 04/18/2007 10:00:18 MDTNo reproduction or networking permitted without license from IHS -,-,- ANSI/AIAA S-096-2004 4 Impact Damag
46、e Tolerance the ability of the fracture critical non-metallic parts in the FRA to resist strength degradation due to the impact damage event Initial Flaw A local discontinuity or a crack-like defect in the parts of a FRA before the application of load and/or deleterious environment. Key Process Para
47、meter (KPP) the critical process parameters that affect key design and product characteristics Life Factor the factor by which the service life is multiplied to obtain total fatigue life or safe-life NOTE Life Factor is often referred to as a scatter factor that is normally used to account for the s
48、catter of materials fatigue or crack growth data. Limit Load the maximum load or combination of loads a rotating part is expected to experience at any time during its intended operation and expected environment Margin of Safety (MoS) MoS= Allowable Load/(Limit Load X Design Safety Factor) 1 NOTE Load may mean stress or strain. Maximum Expected Operating Speed (MEOS) the maximum spinning speed that a part in a FRA is expected to experience during its normal operation NOTE MEOS is synonymous with limit speed. M