ANSI AIAA R-020A-1999 Recommended Practice for Mass Properties Control for Satellites Missiles and Launch Vehicles《航天系统用估计和预算重量和动力费用导则》.pdf

1、ANS I/AIAA R-020A-1999 Recommended Practice for Mass Properties Control for Satellites, Missiles, 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 grant

2、s you a license as follows: The right 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

3、. In addition, the electronic file 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. COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information

4、 Handling ServicesAl WAN S I R-020A-1999 Recommended Practice for Mass Properties Control for Satellites, Missiles, and Launch Vehicles COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling ServicesANWAIAA R-020A-1999 American National Standard Recommended Prac

5、tice for Mass Properties Control for Satellites, Missiles and Launch Vehicles Sponsored by American Institute of Aeronautics and Astronautics In cooperation with Society of Allied Weight Engineers Approved August 23,2000 American National Standards Institute Abstract This Recommended Practice provid

6、es a methodology for the management of the growth of mass properties during the development of aerospace flight vehicles. It is particularly applicable to missiles, satellites, and launch vehicles. The standardized methodology is consistent with former Mil-Std 181 1 and is based on planning, control

7、ling, and reporting at each stage of product or system development. COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling ServicesANSIIAIAA R-020A-1999 i Approval of an American National Standard requires verification by ANSI that the requirements for due proce

8、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. National Standard Substantial agreement means much m

9、ore than a simple 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 any

10、one, whether he has 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 A

11、merican National Standard. 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

12、the title page of 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 ap

13、proval. Purchasers of American National Standards may receive current information on all standards by calling or writing the American National Standards Institute. Recommended practice: mass properties for satellites, missiles, and launch vehicles/generated by AIAA Design Engineering Committee on St

14、andards in cooperation with the Society of Allied Weight Engineers, Government/lndustry Missiles and Space Systems Committee. p. cm. “ANSVAIAA R-020A-1999“ Includes bi bliog rap h ical references. ISBN 1-56347-387-9 (softcover), 1-56347-454-9 (electronic) 1. Space vehicles-Design and construction-St

15、andards. 2. Space Vehicles-Weight-Standards 3. Space vehicles-Propulsion systems-Standards. I. Society of Allied Weight Engineers. Government Industry Missiles and Space Systems Committee. II. AIAA Design Engineering Committee on Standards. TS875.R43 2000 629.4602 1 873-dc2 1 99-089674 Published by

16、American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Suite 500, Reston, VA 20191-4344 Copyright O 2000 American Institute of Aeronautics and Astronautics, Inc. All rights reserved. No part of this publication may be reproduced in any form, in an electronic retrieval system o

17、r otherwise, without prior written permission of the publisher. Printed in the United States of America II COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling ServicesANSIIAIAA R-020A-1999 Contents Foreword v 1 2 3 3.1 3.2 3.2.1 3.2.2 3.2.3 3.3 3.3.1 3.3.2 3.

18、3.3 3.3.4 3.3.5 3.3.6 4 4.1 4.2 4.3 4.4 4.5 4.6 5 5.1 5.2 5.2.1 5.2.2 5.2.3 5.2.4 5.2.5 5.3 5.3.1 5.3.2 5.3.3 Scope . 1 Refe re n ces 1 Definitions 1 Mass Properties . 1 Mass Properties Categories . 1 Estimated Properties 1 Calculated Properties . 1 Measured Properties 1 Mass Control Parameters 2 Ma

19、ss Growth Allowance 2 Predicted Mass 2 Contractor Limit 2 Contractor Margin 2 Customer Reserve 3 Mission Limit 3 Design and Development Process . 3 Bid 3 CoDR 3 PDR . 4 CDR . 4 PRR . 4 FRR 5 Mass Properties Control Process . 5 Overview of Control Process 5 Documentation . 5 Control Plan 6 . Verifica

20、tion Plan . 6 Status Reports . 7 Detail Reports 7 Trend Analysis Report 7 Analysis . 8 Flight Analysis 8 Ground Support Equipment . 9 Configuration Definitions and Limitations 9 COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling ServicesANSIIAIAA R-020A-1999

21、 . 5.4 Verification . 9 5.4.1 5.4.2 5.4.3 Determination of Mass Properties Verification Requirements 9 . Determination of Mass Properties Limits . 1 O Mass Properties Verification Process 1 O iv COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling ServicesANSV

22、AIAA R-020A-1999 Foreword This Recommended Practice for Mass Properties Control of Satellites, Missiles and Launch Vehicles is sponsored by the American Institute of Aeronautics and Astronautics (AIAA) as part of its Standards Program. This recommended practice is produced by the AIAA Design Enginee

23、ring Committee on Standards in concert with the Society of Allied Weights Engineers, Inc (SAWE). The purpose is to provide a comprehensive methodology for mass properties control through the multiple phases of hardware development. It serves to link existing mass properties documentation between the

24、 AIAA, SAWE and United States Government, and to amplify those areas of mass properties control which may need clarification for good engineering practice. This document supersedes the former AIAA document, “Estimating and Budgeting Weight and Power Contingencies for Spacecraft Systems” (ANSVAIAA G-

25、020- 1 992). The AIAA Standards Procedures provide 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 standard publication and no commitment to conform or

26、 be guided by any standards report. 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 infrin

27、gement or copyrights or bot h. At the time of publication, the members of the AIAA Design Engineering Committee on Standards were: Roger L. Belt Boeing (Co-Chairman) Alvin W. Sheffler Motorola (Co-Chairman) Angelo Colao William F.Eckles William T. Griffiths Robin Gubby Glen S. Mathews Daniel C. Maus

28、ser Bob McFarland Glen T. Richbourg Christine Rusch Phillip Schipani John Shea Lincoln Laboratory, MIT Spectrum Astro, Inc. Hughes Space and Communications Telesat Canada Lockheed Martin Missiles and Space The Aerospace Corporation Space Systems Lora1 Lockheed Martin Missiles and Space Raytheon Orbi

29、tal Sciences Corporation Boeing The following are members of The Society of Allied Weight Engineers: GovernmentAndustry Missiles and Space Systems Committee: William T. Griffiths, Glen S. Mathews, Daniel C. Mausser, Glen T. Richbourg, Christine Rusch, and Roger L. Belt. The following are part of the

30、 editorial committee: Glen S. Mathews, Roger L. Belt, and Alvin W. Sheffler. Certain Recommended Practices published by the Society of Allied Weight Engineers are referenced in this standard. The SAWE documents may be obtained from the Society. The postal address is: Society of Allied Weight Enginee

31、rs, Inc. P. O. Box 60024, Terminal Annex Los Angles, CA 90060 The Web site address is: http:/www.sawe.org The AIAA Standards Executive Council accepted the document for publication in August 2000. V COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling Services

32、COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by Information Handling ServicesANSIIAIAA R-020A-1999 1 Scope The management and control of mass properties is of fundamental importance in the design and manufacturing process of aerospace hardware. Mass properties are to be manag

33、ed and controlled as any other system performance parameter. They need to be allocated, analyzed, controlled and verified. The full set of mass properties, including mass, center of gravity, moments of inertia and products of inertia need to be tracked throughout the program to assure compliance wit

34、h the program requirements. 2 Re fe re n ces The following documentation is referenced in this Recommended Practice. If a conflict exists between this Recommended Practice and these referenced documents, the user may contact AIAA for aid in resolving the conflict. Mil-Hdbk-1811, “Mass Properties Con

35、trol for Space Vehicles”, August 1998 SAWE Recommended Practice #9, “Weight and Balance Control System for Guided Missiles and Space Launch Vehicles” SAWE Recommended Practice #IO, “Weight and Balance Data Reporting Forms for Guided Missiles and Space Launch Vehicles” SAWE Recommended Practice #I 1,

36、 “Mass Properties Control of Space Vehicles” SAWE Recommended Practice #6, “Standard Coordinate System for Reporting the Mass Properties of Flight Vehicles” 3 Def i n it ions 3.1 Mass Properties The mass properties of a given item include the mass, center of gravity (CG), mass moments of inertia and

37、 the mass products of inertia of that item. Although the term “weight” is commonly used in practice, the proper term is “mass” and that term is used throughout this document. 3.2 Mass Properties Categories Mass properties are typically categorized as “estimated”, “calculated”, or “measured” (or “act

38、ual”) according to the method used to determine their value. The percent of the hardware mass that is based on each of these categories is an indication of the confidence that can be placed in the reported mass properties data. In general, the following definitions apply: 3.2.1 Estimated Properties

39、Mass properties determined from preliminary data, such as sketches or calculations from layout drawings, are typically considered to be in the estimated category. 3.2.2 Calculated Properties Mass properties determined from released drawings or controlled computer models are typically considered to b

40、e in the calculated category. 3.2.3 Measured Properties Mass properties determined by measurement or by comparison of nearly identical components for which measured mass properties are available are in the measured category. 1 COPYRIGHT American Institute of Aeronautics and AstronauticsLicensed by I

41、nformation Handling ServicesANSIIAIAA R-020A-1999 Figure 1 is an illustration of related terms commonly used in reporting mass properties during the development of aerospace hardware. The definitions of these terms are given here in logical sequence rather than alphabetical order. Mission Limit Cust

42、omer Reserve Contractor Limit Pred i ded Actual System Proceed PDR CDR Mass Delivery I I I I I I I I I I Time Figure 1 - Mass Control Parameters (Idealized to illustrate definitions) 3.3 Mass Control Parameters The Basic Mass Properties of an item are the mass properties data based on an assessment

43、of the most recent baseline design. This design assessment includes the estimated, calculated, or measured mass properties, and includes an estimate for undefined design details. The mass growth allowance is not included. 3.3.1 Mass Growth Allowance The Mass Growth Allowance is the predicted change

44、to the Basic Mass Properties of an item based on an assessment of the design and the fabrication status of the item, along with an estimate of the design changes that may occur. The design changes may be implemented in order to satisfy the contracted design requirements during the development proces

45、s. The Mass Growth Allowance associated with these design changes compensates for the lack of design maturity. Configuration changes driven by major contract or requirements changes are not included in the mass growth allowance. 3.3.2 Predicted Mass The Predicted Mass of an item is the Basic Mass pl

46、us the Mass Growth Allowance, and is intended to estimate the final mass at the end of the development cycle. 3.3.3 Contractor Limit The Contractor Limit Mass of an item is established early in the program based on prior experience with similar hardware items. It includes a margin above the Predicte

47、d Mass to allow for uncertainties during the design cycle. The Contractor Limit is intended to remain constant through the course of the program. 3.3.4 Contractor Margin The Contractor Margin is the difference between the Contractor Limit and the Predicted Mass. 2 COPYRIGHT American Institute of Aer

48、onautics and AstronauticsLicensed by Information Handling ServicesANSIIAIAA R-020A-1999 3.3.5 Customer Reserve The Customer Reserve may be defined by the customer acquiring the hardware from the contractor. This value is defined by the customer according to the agreements of the contract. 3.3.6 Miss

49、ion Limit The Mission Limit is the maximum mass that can still satisfy all of the mission performance requirements. 4 Design and Development Process The program phases related to mission or project development generally follow the common set of milestones shown here. Mass Properties Reviews are to be conducted at each milestone and Mass Properties Reports generated: Bid Proposal or Bid Stage CoDR Conceptual Design Review PDR Preliminary Design Review CDR Critical Design Review PRR Pre-shipment Readiness Review FRR Flight Readiness Review The following sections define these stages and