1、BS ISO16454:2007ICS 49.140NO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAWBRITISH STANDARDSpace systems Structural design Stress analysisrequirementsThis British Standardwas published under theauthority of the StandardsPolicy and StrategyCommittee on 28 February2009 BSI 2009ISB
2、N 978 0 580 54019 6Amendments/corrigenda issued since publicationDate CommentsBS ISO 16454:2007National forewordThis British Standard is the UK implementation of ISO 16454:2007.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68/-/1, Space systems and operations - Engi
3、neeringDesign production.A list of organizations represented on this committee can be obtained onrequest to its secretary.This publication does not purport to include all the necessary provisionsof a contract. Users are responsible for its correct application.Compliance with a British Standard canno
4、t confer immunityfrom legal obligations.BS ISO 16454:2007Reference numberISO 16454:2007(E)ISO 2007INTERNATIONAL STANDARD ISO16454First edition2007-11-01Space systems Structural design Stress analysis requirements Systmes spatiaux Conception des structures Exigences relatives lanalyse des contraintes
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8、t at the address given below. COPYRIGHT PROTECTED DOCUMENT ISO 2007 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 writing fr
9、om 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 2007 All rights reservedBS ISO 16454:200
10、7ISO 16454:2007(E) ISO 2007 All rights reserved iiiContents Page Foreword iv Introduction v 1 Scope . 1 2 Normative references . 1 3 Terms and definitions. 1 4 Requirements 5 4.1 General. 5 4.2 Basic data 5 4.3 Analysis methodology and software 7 4.4 Structural mathematical model . 7 4.5 Structure m
11、athematical model check. 8 4.6 Failure modes 8 4.7 Critical location analysis 9 4.8 Determination margins of safety. 9 4.9 Report 10 Annex A (informative) Structural mathematical model check . 11 BS ISO 16454:2007ISO 16454:2007(E) iv ISO 2007 All rights reservedForeword ISO (the International Organi
12、zation for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). 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 establishe
13、d has the right to be represented on that committee. International organizations, governmental and non-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.
14、International Standards are drafted in accordance with the rules given in the ISO/IEC Directives, Part 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. Pub
15、lication as an International Standard requires approval by at least 75 % of the member bodies casting 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
16、 rights. ISO 16454 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations. BS ISO 16454:2007ISO 16454:2007(E) ISO 2007 All rights reserved vIntroduction From the beginning of the space age, structural integrity verification has be
17、en one of the main fields of mechanical specialists activity. Mission failure and potential danger to human life, expensive ground constructions and other public and private property are the most probable consequences in the case of space structural integrity failure. Static strength is one of the m
18、ost important critical conditions for structural integrity analysis. It is usually the main criteria for space structure weight evaluation. If the space structure is too heavy, the mission could be extremely expensive or impossible to achieve. If the space structure is underdesigned, it could result
19、 in structural failure, leading to high risk associated with safety of life, and loss of expensive hardware and other property. It is therefore necessary to specify unique requirements for static strength analysis in order to provide cost effective design and light-weight, reliable and low risk stru
20、ctures for space application. The analysis and design of space structures has a long history. This International Standard establishes the preferred requirements related to these techniques for static strength critical condition. BS ISO 16454:2007BS ISO 16454:2007INTERNATIONAL STANDARD ISO 16454:2007
21、(E) ISO 2007 All rights reserved 1Space systems Structural design Stress analysis requirements 1 Scope This International Standard is intended to be used for the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft primary structure design. Liquid p
22、ropellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure vessels and solid propellant cases are within the scope of this International Standard. This International Standard provides requirements for the determ
23、ination of maximum stress and corresponding margin of safety under loading, and defines criteria for static strength failure modes, such as rupture, collapse and detrimental yielding. Critical conditions associated with fatigue, creep and crack growths are not covered. Notwithstanding these limitati
24、ons in scope, the results of stress calculations based on the requirements of this International Standard are applicable to other critical condition analyses. In accordance with the requirements of this International Standard, models, methods and procedures for stress determination can also be appli
25、ed to the displacements and deformation calculations, as well as to the loads definition, applied to substructures and structural members of structures under consideration. When this International Standard is applied, it is assumed that temperature distribution has been determined and is used as inp
26、ut data. 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 (including any amendments) applies. ISO 14622, Space
27、systems Structural design Loads and induced environment ISO 14623, Space systems Pressure vessels and pressurized structures Design and operation 3 Terms and definitions For the purposes of this document, the following terms and definitions apply. 3.1 A-basis allowable mechanical strength value abov
28、e which at least 99 % of the population of values is expected to fall, with a confidence level of 95 % 3.2 allowable load allowable stress allowable strain maximum load (stress, strain) that can be accommodated by a material/structure without potential rupture, collapse or detrimental deformation in
29、 a given environment NOTE Allowable loads (stresses, strains) commonly correspond to the statistically based minimum ultimate strength, buckling strength and yield strength, respectively. BS ISO 16454:2007ISO 16454:2007(E) 2 ISO 2007 All rights reserved3.3 basic data input data required to perform s
30、tress analysis and to determine margins of safety 3.4 B-basis allowable mechanical strength value above which at least 90 % of the population of values is expected to fall, with a confidence level of 95 % 3.5 collapse failure mode induced by quasi-static compression, shear or combined stress, accomp
31、anied by very rapid irreversible loss of load resistance capability 3.6 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 t
32、here is an interface between them. 3.7 creep process of a permanent material deformation resulting from long duration under constant or slowly altered load NOTE The ultimate creep deformation, corresponding to the loss of material integrity is often much larger than ultimate deformation in the case
33、of short time loading. 3.8 critical condition most severe environmental condition in terms of load and temperature, or combination thereof, imposed on a structure, system, subsystem or component during service life 3.9 critical location structural point at which rupture, local buckling or detrimenta
34、l deformation will first lead to structural failure 3.10 design safety factor coefficient by which limit loads are multiplied in order to account for the statistical variations of loads and structure resistance, and inaccuracies in the knowledge of their statistical distributions 3.11 destabilizing
35、load load that produces compressive stress at critical location 3.12 detrimental yielding metallic structures permanent deformation specified at the system level to be detrimental 3.13 development test test to provide design information that can be used to check the validity of analytic technique an
36、d assumed design parameters, to uncover unexpected system response characteristics, to evaluate design changes, to determine interface compatibility, to prove qualification and acceptance procedures and techniques, to check manufacturing technology, or to establish accept/reject criteria BS ISO 1645
37、4:2007ISO 16454:2007(E) ISO 2007 All rights reserved 33.14 flight-type hardware test test of a flight structure article, a protoflight model, a representative special model or a structural element fabricated with the same or close to flight hardware technology 3.15 gauges thickness and other structu
38、re dimensions which relative scattering could result in significant effect on stress levels and/or margin of safety 3.16 knockdown coefficient empirical coefficient, other than design safety factor, which is used to determine analytically in a simple way actual or allowable loads or stresses, and wh
39、ich is defined on the basis of test results of flight-type structures, model structures or structural members as compared with corresponding stress analysis data 3.17 limit load maximum that can be expected during service life and in the presence of the environment NOTE For stabilizing loads, the li
40、mit load is the minimum load. 3.18 loads volume forces and moments, concentrated and/or distributed over the structure surfaces or structure, caused by its interaction with environment and adjacent parts of vehicle, and accelerations NOTE This includes pressures, external loads and enforced displace
41、ments acted at considered structural element, pretension, inertial loads caused by accelerations and thermal gradients. 3.19 loading case particular condition described in terms of loads/pressures/temperatures combinations, which can occur for some parts of structure at the same time during its serv
42、ice life 3.20 local buckling failure mode, which occurs when an alternative equilibrium mode of a structural member exists, and which could lead to detrimental deformation or rupture of that member if it occurs under loading 3.21 margin of safety MSexpression of the margin of the limit load multipli
43、ed by design safety factor against the allowed load Another representation of the concept: ALSDS LL1FMfF=(1) where ALF is the allowable load under specified functional conditions (e.g. yield, rupture, collapse, local buckling); LLF is the limit load; DSf is the design safety factor. NOTE Load can im
44、ply corresponding stress or strain. BS ISO 16454:2007ISO 16454:2007(E) 4 ISO 2007 All rights reserved3.22 minimum allowable minimum material mechanical properties warranted by the supplier 3.23 pressure external load caused by fluid action on a structural surface NOTE The terms “pressure” and “load”
45、 are sometimes referred to simultaneously in this International Standard. 3.24 primary structure part of a vehicle that carries the main loads and/or defines the fundamental resonance frequencies 3.25 rupture loss of integrity by structure material differed from fatigue and ultimate creep deformatio
46、n attainment, which could prevent the structure from withstanding load combinations 3.26 semi-finished item product that is used for structure manufacturing or assembling EXAMPLE Sheets, plates, profiles, strips, etc. 3.27 stabilizing load load which decreases compressive stresses if applied in conj
47、unction with destabilizing loads 3.28 static strength property of a structure, characterized by its capability to withstand loads and temperature combinations without rupture, collapse, detrimental local buckling and detrimental deformation 3.29 strength failure mode condition of a structure or a st
48、ructural member considered as a critical condition in accordance with stress analysis results 3.30 stress analysis analytical procedure to determine structure stress/strain distribution, deformations and margins of safety 3.31 structure primary structure, unit attachments, pressure/loads carrying el
49、ements of pressure vessels, loads carrying elements of appendages 3.32 structural mathematical model analytical or digital presentation of a structure NOTE It is advisable that the model provides adequate description of the structures response under loads/pressures/temperatures. 3.33 ultimate load limit load multiplied by ultimate design safety factor 3.34 unit part of a vehicle which is designed mainly to provide vehicle functioning and which differs from a structure BS ISO 16454:2007ISO 16454:2007(E) ISO 2007
