AIAA S-096-2004 Space Systems Flywheel Rotor Assemblies《航天系统.飞轮转子组件》.pdf

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 stand

2、ard 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 netwo

3、rks 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 ANSI/AIAA S-096-2004 American National Standard Space Systems Flywheel Rotor Assemblies Sponsored by American Institute of Aeronau

4、tics and Astronautics Approved 30 November 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 stor

5、age and/or attitude control. These requirements when implemented on a particular system will assure a high level of confidence in achieving safe and reliable operation. ANSI/AIAA S-096-2004 ii Approval of an American National Standard requires verification by ANSI that the requirements for due proce

6、ss, consensus, and other criteria have been met by the standards developer. 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

7、majority, but not necessarily unanimity. Consensus requires that all views 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 ha

8、s approved the standards or not, from manufacturing, marketing, purchasing, 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 S

9、tandard. Moreover, no person shall have the right or authority to issue an 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

10、this standard. CAUTION NOTICE: This American National Standard may be revised 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

11、 of American National Standards may receive current information on all standards 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

12、of Aeronautics and Astronautics. p. cm. ISBN 1-56347-741-6 (hardcopy) - ISBN 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-Sta

13、ndards-United States. 4. Rotors-Standards-United States. I. American Institute 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 Aer

14、onautics and Astronautics All rights reserved No part of this publication 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 ANSI/AIAA S-096-2004 iii Cont

15、ents Foreword v 1 Scope 1 2 Applicable Documents1 3 Vocabulary 1 3.1 Abbreviations and Acronyms .1 3.2 Terms 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 Dyna

16、mics 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 Life8 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 Outgassing 8 4.2 Materials Requirements9 4.2.1 Metallic M

17、aterials 9 4.2.2 Composite Materials .9 4.2.3 Ceramic Materials.10 4.2.4 Polymeric Materials 11 4.3 Fabrication 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

18、 Storage Requirements13 4.7 Transportation Requirements.13 ANSI/AIAA S-096-2004 iv 5 Verification Requirements 13 5.1 Design Requirements Verification13 5.1.1 System Analysis Verification 13 5.1.2 Loads, Speeds and Environments Verification .14 5.1.3 Strength Verification .14 5.1.4 Static Stiffness

19、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 Verification* .16 5.1.9 Fatigue Life Verification 17 5.1.10 Time Dependent Behavior Verification 17 5.1.11 Stress-Rupture Life Verification .17 5.1.12 Co

20、rrosion 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 Proof 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 V

21、ibration 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 Verification Matrix .15 ANSI/AIAA S-096-2004 v Foreword This Standard establishes baseline requirements for the design, fabrication, test, inspe

22、ction, 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 particular system will assure a high level of confidence in achieving safe and reliable operation. The developmen

23、t 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 aerospace prime companies, flywheel rotor suppliers, university researchers and all interested government agencies

24、. 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. At the time of document preparation, the members of the AIAA Flywheel Rotor Safe-Life Standards Working Gr

25、oup 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 Energy Systems, Inc. Yasser Gowayed Auburn University Joseph Klupar Honeywell Kevin Konno NASA Glenn Research Cen

26、ter Kerry McLallin NASA Glenn Research Center Jennifer Ratner The Aerospace Corporation James Schindler Boeing Phantomworks Carlos Stevens Honeywell Satellite Systems Richard Thompson University of Texas - Center for Electromechanics Jerome Tzeng U.S. Army Research Lab Jeff Welsh AFRL, Space Vehicle

27、s 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) accepted the document for publication in October 2004. The AIAA Standards Procedures dictates that all approved S

28、tandards, 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 publication and no commitment to conform to or be guided by standards reports. In formulating, revising, and ap

29、proving 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 themselves against liability for infringement of patents or copyright or both. ANSI/AIAA S-096-2004 1 1 Sco

30、pe 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 in manned and unmanned space systems.

31、 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 subterranean applications if appropriate chang

32、es 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 conditions. Included are rim, hub and/or s

33、haft, 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 qualification and acceptance test requirements s

34、pecified 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 publications do not apply. However,

35、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. MIL-STD-1540 Military Standard, Test R

36、equirements 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 Matrix Composites MIL-HDBK-340 Military Ha

37、ndbook, 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 the behavior of cracks or crack-like d

38、efects 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 ANSI/AIAA S-096-2004 4 Impact Damage

39、 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 Param

40、eter (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 sc

41、atter 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

42、 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. Maximum Design Speed (MDS) the highest possible operating speed based on a combination o

43、f credible failures NOTE NASA requires manned systems to accommodate any combination of two credible failures that will affect speed. Non-Destructive Evaluation (NDE) a process or procedure for determining the quality or characteristics of a material, part, or assembly without permanently altering t

44、he subject or its properties NOTE In this document, this term is synonymous with non-destructive inspection (NDI), and non-destructive testing (NDT). Operating Environments all environments experienced during service life of FRA Proof Spin Test a spin test that is run on a flight FRA at a pre-select

45、ed spinning speed that is higher than MEOS Polymeric Materials an organic material composed of molecules characterized by the repetition of one or more types of monomeric units Qualification Tests the required formal tests used to prove that the design, manufacturing, and assembly have resulted in h

46、ardware conforming to specification requirements and is acceptable for the intended usage NOTE Qualification test is synonymous with certification test. ANSI/AIAA S-096-2004 5 Service Life the period of time (or cycles) starting with the manufacturing of a specific part in a FRA and continuing throu

47、gh all acceptance testing, handling, storage, transportation, normal operation, refurbishment, re-testing, and reuse that may be required or specified for that part Stress-Rupture Life the time during which the composite maintains structural integrity considering the combined effects of stress level

48、(s), time at stress level(s), and associated environments Touchdown Bearings bearings required to act as the rotor suspension system in the non-operating mode and/or the backup suspension system in the operating mode during main suspension system failure Touchdown Event an event in which the rotor i

49、s forced onto its touchdown bearings due to malfunction of primary bearings, overload or other anomaly Ultimate Load the product of the limit load and the design ultimate safety factor; the load that the parts in a FRA must withstand without catastrophic failure in the expected environment Ultimate Strength the ultimate load that the parts in a FRA withstand without catastrophic failure in the applicable operating environment Visual Damage Threshold (VDT) an impact energy level shown by test(s) that creates an indication that is detectable by a trained inspector