1、StandardANSI/AIAA S-120A-2015 Mass Properties Control forSpace Systems AIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 12700 Sunrise Valley Drive, Reston, VA 20191-5807 USA. All rights reserved. AIAA grants you a license as follows: The right to downl
2、oad an electronic file of this AIAA standard for 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 distribute
3、d elsewhere over computer networks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. SponsoreAmericanand InternApprovedAmericanApprovedAbstract Mass propSociety ofSpace Ssystematidocumentincluding space vehballistic vedevelo
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8、nd Astronautics 12700 Sunrise Valley Dr, Reston, VA 20191 Copyright 2015 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
9、. Printed in the United States of America ISBN 978-1-62410-385-8 ANSI/AIAA S-120A-2015 iii Contents Foreword v 1 Scope 1 2 Tailoring. 1 3 Applicable Documents . 1 4 Vocabulary 2 4.1 Acronyms and Abbreviated Terms 2 4.2 Terms and Definitions . 3 5 Requirements 10 5.1 Mass Properties Control 10 5.2 An
10、alysis . 19 5.3 Verification 20 5.4 Mass Properties Data Management 23 5.5 Documentation 24 6 Bibliography 25 Annex A Supplemental Information for Terms and Definitions (Informative) 26 A.1 Space System Specific Mass Definitions 27 A.2 Hardware Categories 33 Annex B Functional Breakdown of Mass (Inf
11、ormative) . 34 Annex C Guidance for Compliance with Contractual Requirements (Informative) 37 Figures Figure 1 General Mass Definitions 10 Figure 2 Example of Mass Properties Control Process . 13 Figure 3 Example Plot of Mass versus Time 18 Figure A.1 Space Vehicle Mass Definitions . 29 Figure A.2 L
12、aunch Vehicle Mass Definitions . 32 Tables Table 1 Mass Growth Allowance by Design Maturity 15 Table 2 Mass Risk Assessment Example . 17 Table A.1 Hardware Category Descriptions . 33 Table B.1 Example Functional Breakdown (Satellite) . 34 Table B.2 Example Functional Breakdown (Liquid Propulsion Sta
13、ge) 35 Table B.3 Example Functional Breakdown (Launch/Ballistic Vehicles) 36 Table B.4 Example Functional Breakdown (Manned Reentry Vehicles) . 36 ANSI/AIAA S-120A-2015 iv Table C.1 Numbered Requirements 37 ANSI/AIAA S-120A-2015 v Foreword This revision of the Mass Properties Control for Space Syste
14、ms Standard was developed in response to contractors who noted that there were implicit requirements called out in AIAA S-120-2006 (denoted by the use of the word “shall”) that were not true requirements, thus adding unnecessary costs to contracts. In response, a Mass Properties Engineering (MPE) Co
15、mmittee on Standards (CoS) was formed and voted unanimously to revise the existing standard. The International Society of Allied Weight Engineers, Inc. (SAWE), a major source of MPE Subject Matter Experts, signed a Memorandum of Understanding to jointly develop both a revised standard and a revised
16、recommended practice with the American Institute of Aeronautics and Astronautics (AIAA) CoS. The new revisions, designated as AIAA S-120A-2015 and SAWE RP A-3, are intended to fully replace AIAA S-120-2006 and SAWE RP-11C. When a requirement is identified in a subsection of section 5 of this standar
17、d, the corresponding recommended practice is described in the same numbered subsection of RP A-3. This standard is intended to convey the minimally acceptable mass properties requirements for space systems, while the associated SAWE RP A-3, Mass Properties Control for Space Systems, provides guidanc
18、e for implementation of a program-specific mass properties control plan. Together, the two documents may also be used to establish requirements during preparation of acquisition contracts and program-specific documents. This standard contains proven methods and lessons learned for effective mass pro
19、perties control, combines tools necessary for timely evaluation of program mass properties, and enables early decision making regarding possible design changes. The primary objective of this standard is to provide an effective means for meeting program requirements for space system mass properties c
20、ontrol, analysis, verification, data management, and documentation. It is intended to be comprehensive and practical and will be periodically updated to incorporate advances and innovations. At the time of approval, the members of the AIAA Mass Properties Engineering Committee on Standards were: Geo
21、ffrey Beech, Chair National Aeronautics and Space Administration (NASA) Marshall Space Flight Center Mark Andraschko NASA Langley Research Center (LaRC) Jeffrey Bautista Northrop Grumman Jeffrey Cerro NASA LaRC William Griffiths The Aerospace Corporation Jennifer Herron Action Engineering Roland Hol
22、zmann The Boeing Company Robert Hundl Fluor Bell Lee Raytheon Daniel Kwon Orbital ATK Roland Martinez NASA Johnson Space Center (JSC) John Nakai The Aerospace Corporation ANSI/AIAA S-120A-2015 vi Clinton Plaisted A.I. Solutions Glen Richbourg Lockheed Martin Space Systems Company Ricardo Roy United
23、Launch Alliance Robert Shishko Jet Propulsion Laboratory Paul Weitekamp SpaceX David Wolfe Blue Origin Robert Zimmerman Retired The above consensus body approved this document in June 2015. The current members of the AIAA CoS wish to thank the following for their contributions to the initial release
24、 of this document: Tom Ajluni, Kevin Bee, Geoffrey Beech, Roger Belt, Gerard Drewek, David Finkleman, Michael Froehlich, William Griffiths, Mahantesh Hiremath, Gary Holloway, Roland Holzmann, Quang Lam, Bell Lee, Dean Liensdorf, Ian MacNeil, Thomas McGovern, John Nakai, Geoffrey Reber, Glen Richbour
25、g, Ricardo Roy, Ronald Solomon, Richard Sugiyama, Joseph Vecera, Ernest Wade, Louis Yang, and Robert Zimmerman. The AIAA Standards Executive Council (Mr. Allen Arrington, Chairman) accepted the document for publication in October 2015. The AIAA Standards Procedures dictate that all approved Standard
26、s, 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 approving
27、 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. Annexes A, B, and C in this documen
28、t are informative. ANSI/AIAA S-120A-2015 1 1 Scope This standard defines terminology and establishes uniform processes, procedures, and methods for the management, control, monitoring, determination, verification, and documentation of mass properties during the design and development phases of space
29、 systems, including modifications to operational systems. This standard applies to space vehicles (SVs) or spacecraft (SC), upper stage vehicles, injection stages, satellite payloads, reentry vehicles, launch vehicles (LVs), and ballistic vehicles. This standard defines a minimum set of mass propert
30、ies requirements and is intended for use in developing a program-specific, contractually required mass properties control plan (MPCP). When used in conjunction with the International Society of Allied Weight Engineers, Inc. (SAWE) Recommended Practice RP A-3, the two documents serve as a comprehensi
31、ve reference for requirements and best practices in the field of space systems mass properties. 2 Tailoring When viewed from the perspective of a specific program or project context, the requirements defined in this standard may be tailored in a program-specific MPCP. The requirements of this standa
32、rd are presented as a minimum set, and any changes or removal should be undertaken in consultation with the procuring authority and subject matter experts where applicable. For the purpose of this document, the customer is the organization that sets the allowable mass, and the contractor is the orga
33、nization responsible for developing the system or sub-system within the allowable mass. For the purposes of this document the term program is used to refer to either a project or program. NOTE Tailoring is a process by which individual requirements or specifications, standards, and related documents
34、 are evaluated and made applicable to a specific program or project by selection and, in some exceptional cases, modification and addition of requirements in the standards. 3 Applicable Documents The following documents contain provisions which, through reference in this text, constitute provisions
35、of this standard. For dated references, subsequent amendments to, or revisions of, any of these 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 documents indicated below. For un
36、dated references, the latest edition of the document referred to applies. SAWE RP A-3 Mass Properties Control for Space Systems SAWE RP 6 Standard Coordinate Systems for Reporting the Mass Properties of Flight Vehicles SAWE RP 16 Measurement of Missile and Spacecraft Mass Properties ANSI/AIAA S-120A
37、-2015 2 4 Vocabulary 4.1 Acronyms and Abbreviated Terms 3D Three dimensional ACS Attitude Control System AIAA American Institute of Aeronautics and Astronautics ANSI American National Standards Institute ATP Authorization to ProceedCAD Computer-Aided Design CCB Change Control BoardCDR Critical Desig
38、n Review CDRL Contract Data Requirements List CFE Customer-Furnished Equipment CM Center of Mass CoS Committee on Standards ECLSS Environmental Control and Life Support System EIDP End Item Data Package FBS Functional Breakdown Structure GSE Ground Support Equipment H High (probability of occurrence
39、) ID Identify IPT Integrated Product Team ISO International Organization for Standardization JSC Johnson Space Center kg Kilogram L Low (probability of occurrence) LaRC Langley Research Center LV Launch Vehicle M Medium (probability of occurrence) MGA Mass Growth Allowance MIL-HDBK Military Handbook
40、 MOI Moment(s) of Inertia MP Mass Properties ANSI/AIAA S-120A-2015 3 MPCB Mass Properties Control Board MPCP Mass Properties Control Plan MPE Mass Properties Engineer, Mass Properties Engineering NASA National Aeronautics and Space Administration NTE Not to Exceed PDR Preliminary Design Review POI P
41、roduct(s) of Inertia PSRR Pre-shipment Readiness Review RP Recommended Practice SAWE International Society of Allied Weight Engineers, Inc. SC Spacecraft SV Space Vehicle SWI Standard Work Instruction TP Test Procedure TPM Technical Performance Measurement VDL Variance Discrepancy Log WBS Work Break
42、down Structure 4.2 Terms and Definitions For the purposes of this document, the following terms and definitions apply. Annex A provides vehicle-specific graphical summaries of the relationships between key definitions. Actual Mass Properties mass properties determined by measurement or by comparison
43、 of nearly identical components, for which measured mass properties are available (assessed as maturity category A5 or A6 in Table 1) Allowable Mass the limit against which mass margins are calculated NOTE 1 The allowable mass is a derived requirement set early in the program and is intended to rema
44、in constant until there is a change in requirements. NOTE 2 Examples of an allowable mass include a contractor not-to-exceed (NTE) mass limit or an informal mass allocation to a design organization. Balance Mass mass added to a system or component to achieve static or dynamic balance Ballast mass th
45、at may be added, removed, or relocated to meet mass properties, stability, or orbital injection requirements ANSI/AIAA S-120A-2015 4 Baseline the current state of requirements, design definition, and other formally controlled Program documentation Basic Mass the current mass of dry hardware based on
46、 an assessment of the most recent baseline design NOTE 1 The design assessment includes the estimated, calculated, or measured (or actual) mass and includes an estimate for undefined design details like cables, multi-layer insulation, and adhesives. NOTE 2 The mass growth allowances (MGA) and uncert
47、ainties are not included in the basic mass. NOTE 3 Basic mass is sometimes referred to as Current Best Estimate. Bulk Item a constituent of an assembly or part that is not readily identified by an exact quantity or graphical representation and where its shape, volume, and mass may be determined upon
48、 installation or by a note only. These items generally have a quantity of “as required” in the parts list, e.g., paints, structural adhesives, fluids, tapes. Bus the portion of an SV that supports payloads and performs functions related to the SVs basic operation and maintenance, such as flight cont
49、rol, power, and propulsion Calculated Mass Properties mass properties determined from preliminary or released drawings or controlled computer models (assessed as maturity category C3 or C4 in Table 1) Center of Mass (CM) the point at which the distributed mass of a simple or composite body can be acted upon by a linear force without inducing any rotation of the body Critical Mass Properties those mass properties that have limits that would jeopardize mission performance or safety if exceeded Dry Mass the mass of a space system without propellants or i
