1、raising standards worldwideNO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAWBSI Standards PublicationBS ISO 10786:2011Space systems Structuralcomponents and assembliesBS ISO 10786:2011 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of ISO 10786:2
2、011.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68/-/1, Space systems and operations - Design,Engineering and Production.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include a
3、ll the necessaryprovisions of a contract. Users are responsible for its correctapplication. BSI 2011ISBN 978 0 580 66621 6ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strat
4、egy Committee on 31 July 2011.Amendments issued since publicationDate Text affectedBS ISO 10786:2011Reference numberISO 10786:2011(E)ISO 2011INTERNATIONAL STANDARD ISO10786First edition2011-07-15Space systems Structural components and assemblies Systmes spatiaux Composants et assemblages de structur
5、e BS ISO 10786:2011ISO 10786:2011(E) COPYRIGHT PROTECTED DOCUMENT ISO 2011 All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized in any form or by any means, electronic or mechanical, including photocopying and microfilm, without permission in wri
6、ting from either ISO at the address below or ISOs member body in the country of the requester. ISO copyright office Case postale 56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.org Web www.iso.org Published in Switzerland ii ISO 2011 All rights reservedBS ISO 10
7、786:2011ISO 10786:2011(E) ISO 2011 All rights reserved iiiContents Page Foreword iv Introduction.v 1 Scope1 2 Normative references1 3 Terms and definitions .2 4 Symbols and abbreviated terms 11 5 Tailoring13 6 Requirements.13 6.1 General .13 6.2 Design requirements.13 6.3 Material requirements .18 6
8、.4 Manufacturing and interfaces requirements 21 6.5 Quality assurance23 6.6 Traceability.25 6.7 Deliverables .25 6.8 In-service requirements26 6.9 Maintenance requirements.26 6.10 Repair and refurbishment.28 7 Verification of general requirements.28 7.1 General .28 7.2 Verification of design require
9、ments 29 7.3 Acceptance tests .39 7.4 Qualification progamme (qualification tests) .40 8 Special structural items42 8.1 General .42 8.2 Special structural items with published standards .42 8.3 Special structural items without published standards42 9 Documentation requirements.43 9.1 Interface contr
10、ol documents 43 9.2 Applicable (contractual) documents .44 9.3 Analysis reports 44 10 Data exchange .46 10.1 Data set requirements.46 10.2 System configuration data .46 10.3 Data exchange between design and structural analysis.46 10.4 Data exchange between structural design and manufacturing46 10.5
11、Data exchange with other subsystems.47 10.6 Tests and structural analysis.47 10.7 Structural mathematical models47 Annex A (informative) Recommended best practices for structural design 48 Annex B (informative) Design requirements verification methods58 Annex C (informative) Design requirements veri
12、fication methods61 Annex D (informative) Margin of safety for combined loads64 Bibliography65 BS ISO 10786:2011ISO 10786:2011(E) iv ISO 2011 All rights reservedForeword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies)
13、. The work of preparing International Standards is normally carried out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non
14、-governmental, in liaison with ISO, also take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part
15、 2. The main task of technical committees is to prepare International Standards. Draft International Standards adopted by the technical committees are circulated to the member bodies for voting. Publication as an International Standard requires approval by at least 75 % of the member bodies casting
16、a vote. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. ISO 10786 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcomm
17、ittee SC 14, Space systems and operations. BS ISO 10786:2011ISO 10786:2011(E) ISO 2011 All rights reserved vIntroduction Structures are the backbones of all spaceflight systems. A structural failure could cause the loss of human lives for manned space systems or could jeopardize the intended mission
18、 for unmanned space systems. Currently, there is no International Standard that covers all the aspects that can be used for spaceflight structural items such as spacecraft platforms, interstage adaptors, launch vehicle buses and rocket motor cases. The purpose of this International Standard is to es
19、tablish general requirements for structures. It provides the uniform requirements necessary to minimize the duplication of effort and the differences between approaches taken by the participating nations and their commercial space communities in developing structures. In addition, the use of agreed-
20、upon standards will facilitate cooperation and communication among space progammes. BS ISO 10786:2011BS ISO 10786:2011INTERNATIONAL STANDARD ISO 10786:2011(E) ISO 2011 All rights reserved 1Space systems Structural components and assemblies 1 Scope This International Standard establishes requirements
21、 for the design; material selection and characterization; fabrication; testing and inspection of all structural items in space systems, including expendable and reusable launch vehicles, satellites and their payloads. This International Standard, when implemented for a particular space system, will
22、assure high confidence in achieving safe and reliable operation in all phases of its planned mission. This International Standard applies specifically to all structural items, including fracture-critical hardware used in space systems during all phases of the mission, with the following exceptions:
23、adaptive structures, engines and thermal protection systems. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only the edition cited applies. For undated references, the latest edition of the referenced document (
24、including any amendments) applies. ISO 14622:2000, Space systems Structural design Loads and induced environment ISO 14623:2003, Space systems Pressure vessels and pressurized structures Design and operation ISO 14953:2000, Space systems Structural design Determination of loading levels for static q
25、ualification testing of launch vehicles ISO 14954:2005, Space systems Dynamic and static analysis Exchange of mathematical models ISO 15864:2004, Space systems General test methods for space craft, subsystems and units ISO 16454:2007, Space systems Structural design Stress analysis requirements ISO
26、21347:2005, Space systems Fracture and damage control ISO 21648:2008, Space systems Flywheel module design and testing ISO 22010:2007, Space systems Mass properties control ISO 24638:2008, Space systems Pressure components and pressure system integration ISO 24917:2010, Space systems General test re
27、quirements for launch vehicles MIL-STD-1540, Revision D Test Requirements for Space Vehicles BS ISO 10786:2011ISO 10786:2011(E) 2 ISO 2011 All rights reserved3 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1 A-basis allowable A-basis design all
28、owable A-value mechanical strength value above which at least 99 % of the population of values is expected to fall, with a confidence level of 95 % ISO 16454:2007 3.2 acceptance test required formal test conducted on flight hardware to ascertain that the materials, manufacturing processes, and workm
29、anship meet specifications and that the hardware is acceptable for intended usage ISO 14623:2003 3.3 adaptive structures autonomous structural systems which incorporate sensors, processors, and actuators to enable adaptation to changing environmental conditions, thereby enhancing safety, stability,
30、vibration damping, acoustic noise suppression, aerodynamic performance and optimization, pointing accuracy, load redistribution, damage response, structural integrity, etc. 3.4 allowable load maximum load that can be accommodated by a structure or a component of a structural assembly without potenti
31、al rupture, collapse, or detrimental deformation in a given environment NOTE 1 “Allowable loads” commonly correspond to the statistically based ultimate strength, buckling strength, and yield strength, or maximum strain (for ductile materials). NOTE 2 “Allowable load” is often referred to as just “a
32、llowable”. 3.5 assembly combination of parts, components and units which forms a functional entity 3.6 B-basis allowable B-basis design allowable B-value mechanical strength value above which at least 90 % of the population of values is expected to fall, with a confidence level of 95 % ISO 16454:200
33、7 3.7 buckling failure mode in which an infinitesimal increase in the load could lead to sudden collapse or detrimental deformation of a structure EXAMPLE Snapping of slender beams, columns, struts and thin-wall shells. BS ISO 10786:2011ISO 10786:2011(E) ISO 2011 All rights reserved 33.8 catastrophi
34、c failure failure which results in the loss of human life, mission or a major ground facility, or long-term detrimental environmental effects 3.9 collapse failure mode induced by quasi-static loads (compression, shear or combined stress) accompanied by irreversible loss of load-carrying capability 3
35、.10 composite material combination of materials different in composition or form on a macro scale NOTE 1 The constituents retain their identities in the composite. NOTE 2 The constituents can normally be physically identified, and there is an interface between them. ISO 16454:2007 EXAMPLE Composites
36、 include fibrous (composed of fibres, usually in a matrix), laminar (layers of materials), and hybrid (combination of fibrous and laminar). 3.11 composite overwrapped pressure vessel COPV pressure vessel with a fibre-based composite system fully or partially encapsulating a liner NOTE The liner serv
37、es as a liquid or gas permeation barrier and may or may not carry substantial pressure loads. The composite overwraps generally carry pressure and environmental loads. ISO 14623:2003 3.12 composite structure structural components that are made of composite materials 3.13 damage tolerance ability of
38、a structure or a component of a structural assembly to resist failure due to the presence of flaws, cracks, or other damage for a specified period of unrepaired usage ISO 21347:2005 3.14 design parameter physical feature which influences the design performance of the design of structural items NOTE
39、According to the nature of the design variables, different design problems can be identified such as: structural sizing for the dimensioning of beams, shells, etc.; shape optimization; material selection; structural topology. BS ISO 10786:2011ISO 10786:2011(E) 4 ISO 2011 All rights reserved3.15 desi
40、gn safety factor factor by which limit loads are multiplied in order to account for uncertainties and variations that cannot be analysed or accounted for explicitly in a rational manner NOTE Design safety factor is sometimes referred to as design factor of safety, factor of safety or just safety fac
41、tor. 3.16 detrimental deformation structural deformation, deflection or displacement that prevents any portion of the structure or some other system from performing its intended function or that jeopardizes mission success 3.17 development test test to provide information that can be used to check t
42、he validity of analytic techniques and assumed design parameters, uncover unexpected system response characteristics, evaluate design changes, determine interface compatibility, prove qualification and acceptance procedures and techniques, check manufacturing technology, or establish accept/reject c
43、riteria ISO 16454:2007 3.18 dynamic load time-dependent load with deterministic or stochastic variation 3.19 failure mode rupture, collapse, detrimental deformation, excessive wear or any other phenomenon resulting in an inability to sustain loads, pressures and corresponding environments, or that j
44、eopardizes mission success NOTE This definition applies to structural failure. 3.20 fail-safe structure structural item for which it can be shown by analysis or test that, as a result of structural redundancy, the structure remaining after the failure of any element of the structural item can sustai
45、n the redistributed limit load, with an ultimate safety factor of 1,0 ISO 21347:2005 3.21 fatigue life number of cycles of stress or strain of a specified character that a given structure or component of a structural assembly can sustain (without the presence of flaw) before failure of a specified n
46、ature could occur 3.22 failure mode effects and critically analysis FMECA analysis performed to systematically evaluate the potential effect of each functional or hardware failure on mission success, personnel and system safety, system performance, maintainability and maintenance requirements NOTE I
47、t is also used to rank by the severity of its effect. 3.23 flaw local discontinuity in a structural material EXAMPLES Crack, cut, scratch, void, delamination disbond, impact damage and other kinds of mechanical damage. ISO 21347:2005 BS ISO 10786:2011ISO 10786:2011(E) ISO 2011 All rights reserved 53
48、.24 fracture control application of design philosophy, analysis methods, manufacturing technology, verification methodology, quality assurance, including non-destructive evaluation (NDE) and operating procedures to prevent premature structural failure caused by the presence and/or propagation of fla
49、ws during fabrication, testing, transportation, handling, and service events such as launch, in-orbit operation, and return 3.25 fracture-critical item fracture-critical part structural part whose failure due to the presence of a flaw would result in a catastrophic failure 3.26 full scale article full-size test article which represents the whole flight structure or a part of the flight structure with representative loading and boundary conditions 3.27 hydrogen embrittlement mech
