AIAA S-114-2005 Moving Mechanical Assemblies for Space and Launch Vehicles《空间和运载火箭动机械组件》.pdf

1、 Standard AIAA S-114-2005 Moving Mechanical Assemblies for Space and Launch Vehicles 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 r

2、ight to download an electronic file of this AIAA standard 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 fil

3、e may not be distributed elsewhere over computer networks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. AIAA S-114-2005 Standard Moving Mechanical Assemblies for Space and Launch Vehicles Sponsored by American Institute

4、of Aeronautics and Astronautics Approved 30 June 2005 Abstract This standard specifies general requirements for the design, manufacture, quality control, testing, and storage of moving mechanical assemblies (MMAs) to be used on space and launch vehicles. This standard is applicable to the mechanical

5、 or electromechanical devices that control the movement of a mechanical part of a space or launch vehicle relative to another part. The requirements apply to the overall MMA as well as to the mechanical components and instrumentation that are an integral part of these mechanical assemblies. AIAA S-1

6、14-2005 ii Library of Congress Cataloging-in-Publication Data Moving mechanical assemblies for space and launch vehicles / sponsored by American Institute of Aeronautics and Astronautics. p. cm. AIAA S-114-2005.“ Includes bibliographical references. ISBN 1-56347-774-2 (hardcopy) - ISBN 1-56347-775-0

7、 (electronic) 1. Space robotics-Standards. 2. Space vehicles-Design and construction-Standards. I. American Institute of Aeronautics and Astronautics. TL1097.M68 2005 629.892-dc22 2005012319 Published by American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Reston, VA 20191 C

8、opyright 2005 American Institute of Aeronautics 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 AIAA S-114-2005 i

9、ii Contents Foreword .vii Introduction.viii 1 Scope 1 2 Tailoring.1 3 Applicable Documents1 4 Vocabulary 2 5 General Design Requirements.5 5.1 Performance Requirements .5 5.1.1 General Performance Requirements .5 5.1.2 Force/Torque Margins 6 5.1.3 Error Budget for Precision Control Assemblies.9 5.1.

10、4 Dynamic Performance 9 5.1.5 Off-nominal Operation 9 5.2 Environmental Design Requirements 10 5.2.1 Launch Environment.10 5.2.2 On-orbit Environment .10 5.2.3 Fabrication, Storage, Transportation, and Handling Environments .10 5.3 Physical Requirements.11 5.3.1 Identification and Marking 11 5.3.2 I

11、nterface Requirements 11 5.3.3 Operability .12 5.3.4 Interchangeability12 5.4 Electrical and Electronic Requirements.12 5.4.1 Cables and Wiring 12 5.4.2 Connectors12 5.4.3 Cable Supports and Strain Relief.13 5.4.4 Cable Loops13 5.4.5 Current Draw.13 5.4.6 Grounding13 5.4.7 Electromagnetic Interferen

12、ce/Electromagnetic Compatibility (EMI/EMC) .13 5.4.8 Electrostatic Discharge.13 5.4.9 Flight Instrumentation .13 5.5 Structural Requirements.13 5.6 Reliability .14 5.6.1 Single-point Failures .14 AIAA S-114-2005 iv 5.6.2 Failure Modes and Effects14 5.6.3 Service Life15 5.6.4 Maintainability .15 6 Co

13、mponent Design Requirements.15 6.1 Fasteners 15 6.1.1 Locking Devices16 6.1.2 Snap Rings16 6.2 Retention and Release Devices.16 6.2.1 Pyrotechnic Actuation Devices.17 6.2.2 Non-explosive Actuation Devices 17 6.2.3 Pin Pullers .17 6.2.4 Separation Nuts 17 6.2.5 Clamp Bands and Retention Cables17 6.3

14、Pivots and Hinges.18 6.4 Cable Systems18 6.5 Springs 18 6.6 Dampers19 6.6.1 Deformable Material Dampers .19 6.6.2 Viscous Dampers19 6.6.3 Eddy Current Dampers.19 6.7 Stops19 6.8 End-of-Travel Latches 20 6.9 Bearings 20 6.9.1 Bearing Materials20 6.9.2 Design and Selection20 6.9.3 Bearing Alignment 21

15、 6.9.4 Ball Bearings.22 6.10 Electric Motors 22 6.10.1 Stepper Motors .22 6.10.2 Torque Motors.22 6.10.3 Direct Current Brush Motors 23 6.11 Power and Signal Transfer Components 23 6.11.1 Slip-ring Assemblies .23 6.11.2 Cable Management Systems.24 6.12 Switches 24 6.13 Gears.24 AIAA S-114-2005 v 6.1

16、3.1 Design and Selection25 6.13.2 Harmonic Drives .25 6.13.3 Precision Gears 25 6.14 Pressurized Components.25 7 Parts, Materials, and Processes Requirements25 7.1 General Parts, Materials, and Processes25 7.2 Materials26 7.3 Lubricants26 7.3.1 Rolling Element Bearing Lubricants.27 7.3.2 Solid (Dry)

17、 Film Lubrication 28 7.4 Hard Coatings .28 7.5 Contamination.28 7.5.1 Fabrication and Handling .28 7.5.2 Device Cleanliness .28 7.5.3 Outgassing 29 8 Testing and Inspection Requirements .29 8.1 Parts, Materials, and Process Controls .29 8.1.1 Inspection of Parts 29 8.1.2 Inspection of Assemblies29 8

18、.1.3 Lubricant Processing Procedures30 8.2 Test Fixtures .30 8.3 Test Instrumentation.30 8.4 Test Plans and Procedures31 8.5 Development Tests.32 8.6 Qualification and Proto-qualification Tests 32 8.6.1 Functional and Environmental (Proto-)Qualification .33 8.6.2 Design Life Verification Tests.33 8.

19、7 Component and Subsystem Level Acceptance Tests 34 8.7.1 Run-in Test35 8.7.2 Functional and Environmental Acceptance.35 8.8 Vehicle Level Acceptance Tests36 8.9 Pre-launch Validation Testing and Inspection.36 8.9.1 Interface Tests 36 8.9.2 Inspection36 8.9.3 Pre-launch Validation Exercises 36 8.10

20、Modifications, Rework, and Retesting .36 AIAA S-114-2005 vi 9 Bibliography 38 Annex A Static Torque or Force Margins at Different Coordinate Points (Informative) .39 Tables Table 1 Minimum Recommended Static Torque or Force Margin for New Designs.7 Table 2 Allowable Contact Stress for Bearing Materi

21、als Under Yield Loads.21 AIAA S-114-2005 vii Foreword This standard is based on Military Specification MIL-A-83577B, Moving Mechanical Assemblies (MMA) for Space and Launch Vehicles, which was cancelled by the Department of Defense in the mid 1990s. It is most recently based on a Technical Operating

22、 Report prepared by Brian W. Gore of The Aerospace Corporation with support from the Air Force Space and Missile Systems Center (SMC) and the National Reconnaissance Office (NRO). This standard is the result of contributions received from many individuals, most notably those on the AIAA MMA Committe

23、e on Standards (CoS). At the time of approval, the members of the AIAA MMA CoS were: Stephen Brock, Liaison AIAA Leonard Demchek Lockheed Martin Corporation Ken Emerick, Co-Chair Space Systems/Loral Brian Gore, Co-Chair The Aerospace Corporation Michael Pollard, Co-Chair Lockheed Martin Corporation

24、Dave Putnam Lockheed Martin Corporation Dave Richman The Boeing Company Paul Reynolds Northrop Grumman Corporation Bert Timmerman Hi-Shear Technology Corporation The above consensus body approved this document in June 2005. The AIAA Standards Executive Council (Mr. Amr ElSawy, Chairman) accepted the

25、 document for publication in June 2005. 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 between industry or trade, in general or spec

26、ific, and AIAA to adhere to any AIAA standards publication and no commitment to conform to or be guided by standards reports. However, should a procuring authority choose to use this standard and contractually impose it upon a contractor and/or subcontractor, the use of this standard will be as defi

27、ned by that particular contract. 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 themselves against liability for infringem

28、ent of patents or copyright or both. AIAA S-114-2005 viii Introduction This standard is intended to incorporate those requirements that are common to most Moving Mechanical Assemblies (MMAs) for space and launch vehicles. The requirements stated are a composite of those that have been found to be co

29、st-effective for high reliability space and launch vehicle applications. Not all requirements stated herein are of equal importance or weight. They have been divided into three categories of importance, ranging from requirements that are imposed on all applications to examples of acceptable designs,

30、 items, and practices. The relative weighting of requirements is an important consideration when tailoring this standard to specific applications and in making trade studies of alternatives. The weighting factors that are incorporated in this standard are as follows. “Shall” designates the most impo

31、rtant weighting level, the mandatory requirements. Unless specifically tailored out or modified by the contract, they constitute the firm contractual compliance requirements. Any deviation from the contractually imposed mandatory requirements requires the approval of the procurement authority. “Shal

32、l, where practical,” designates the second weighting level. Alternative designs, items, or practices may be used for specific applications when the use of the alternative is substantiated by documented technical trade studies and/or test. These trade studies shall be made available for review when r

33、equested or provided to the customer in accordance with the contract provisions. Unless required by other contract provisions, deviations from the “shall, where practical” requirements do not require approval of the procurement authority. “Preferred,” “should,” or “may” designates the lowest weighti

34、ng level. Unless required by other contract provisions, deviations from these preferred requirements do not require approval of the procurement authority and do not require documented technical substantiation. AIAA S-114-2005 1 1 Scope This standard specifies general requirements for the design, man

35、ufacture, quality control, testing, and storage of moving mechanical assemblies (MMAs) to be used on space and launch vehicles. This standard is applicable to the mechanical or electromechanical devices that control the movement of a mechanical part of a space or launch vehicle relative to another p

36、art. The requirements apply to the overall MMA as well as to the mechanical components and instrumentation that are an integral part of these mechanical assemblies. When this standard is used to specify general requirements for MMAs to be used on launch vehicles, injection stages, reentry vehicles,

37、or other vehicles, the term “space vehicle” is to be interpreted as the applicable vehicle. 2 Tailoring Where possible, the requirements in the standard are stated in terms that are self-tailoring to each application. However, additional tailoring of the requirements should be considered throughout

38、the acquisition process within the constraints of the major program elements. These elements typically include performance, testing, reliability, schedules, production costs, operating costs, maintenance costs, and other high-cost drivers in the projected life cycle. Contractors are encouraged to id

39、entify to the procurement authority, for program office review and reconsideration, any requirements imposed by this standard that are believed excessive. However, contractors are reminded that deviations from contractually imposed requirements can be granted only by the procurement authority. The u

40、se of the weighting factors (see Introduction) in the standard is intended to assist in the tailoring of requirements to specific applications and to assist contractors in the design process. Because the implications of the weighting factors vary with the type of contract and with other contract pro

41、visions, it is important to provide clear contractual language, particularly regarding design reviews and the resolution of any subsequent actions. NOTE Tailoring is a process by which individual requirements or specifications, standards, and related documents are evaluated and made applicable to a

42、specific program or project by selection, and in some exceptional cases, modification and addition of requirements in the standards. 3 Applicable Documents The following applicable documents contain provisions that, through reference in this text, constitute provisions of this standard. For dated re

43、ferences, subsequent amendments to, or revisions of, any of these publications do not apply. However, parties to agreements made on the basis of this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated re

44、ferences, the latest edition of the normative document referred to applies. In the event of a conflict between the text of this standard and the references cited herein and the vendors ISO 9001 or AS 9001 quality systems, the text of this standard shall take precedence. Nothing in this standard, how

45、ever, shall supersede applicable laws and regulations unless a specific exemption has been obtained. AFBMA Standards AFBMA Standards for Ball and Roller Bearings and Balls AGMA Handbook American Gear Manufacturers Association Handbook AIAA-S-110-2005 Space Systems Structures, Structural Components,

46、and Structural Assemblies AIAA-S-113-2005 Criteria for Explosive Systems and Devices Used on Launch and Space Vehicles AIAA S-114-2005 2 ASTM F 2094 Standard Specification for Silicon Nitride Bearing Balls MIL-STD-1686 Electrostatic Discharge Control Program For Protection Of Electrical And Electron

47、ic Parts, Assemblies And Equipment (Excluding Electrically Initiated Explosive Devices) MIL-HDBK-83575 Wiring Harness, Space Vehicle, Design and Testing, General Specification for MIL-PRF-46010 Lubricant, Solid Film, Heat Cured, Corrosion Inhibiting MIL-STD-1522 Standard General Requirements for Saf

48、e Design and Operation of Pressurized Missile and Space Systems SAE-AMS-QQ-S-763 Steel, Corrosion Resistant, Bars, Wire, Shapes, and Forgings Aerospace Corp. TR-2004(8583)-1 Test Requirements for Launch, Upper-Stage, and Space Vehicles (to be superseded by MIL-STD-1540E and subsequent versions) 4 Vo

49、cabulary For the purposes of this document, the following terms and definitions apply. Addendum the radial height of an involute gear tooth above the pitch line NOTE A long addendum modification is often specified on a pinion gear to balance the tooth bending stress between the pinion teeth and gear teeth. Approach Action in gearing, the involute action before the point of contact between the meshing gears has reached the pitch point NOTE In spur gearing, pinions with a long addendum modification working with a gear with no addendum modification will have less approach ac