ISO 16454-2007 Space systems - Structural design - Stress analysis requirements《航天系统 结构设计 应力分析要求》.pdf

1、 Reference number ISO 16454:2007(E) ISO 2007INTERNATIONAL STANDARD ISO 16454 First edition 2007-11-01 Space systems Structural design Stress analysis requirements Systmes spatiaux Conception des structures Exigences relatives lanalyse des contraintes ISO 16454:2007(E) PDF disclaimer This PDF file ma

2、y contain embedded typefaces. In accordance with Adobes licensing policy, this file may be printed or viewed but shall not be edited unless the typefaces which are embedded are licensed to and installed on the computer performing the editing. In downloading this file, parties accept therein the resp

3、onsibility of not infringing Adobes licensing policy. The ISO Central Secretariat accepts no liability in this area. Adobe is a trademark of Adobe Systems Incorporated. Details of the software products used to create this PDF file can be found in the General Info relative to the file; the PDF-creati

4、on parameters were optimized for printing. Every care has been taken to ensure that the file is suitable for use by ISO member bodies. In the unlikely event that a problem relating to it is found, please inform the Central Secretariat at the address given below. COPYRIGHT PROTECTED DOCUMENT ISO 2007

5、 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 from either ISO at the address below or ISOs member body in the count

6、ry 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 reservedISO 16454:2007(E) ISO 2007 All rights reserved iii Contents Page Foreword iv Introd

7、uction 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 mathematical model check. 8 4.6 Failure modes 8 4.7 Critical location analysis 9 4.8

8、 Determination margins of safety. 9 4.9 Report 10 Annex A (informative) Structural mathematical model check . 11 ISO 16454:2007(E) iv ISO 2007 All rights reservedForeword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodie

9、s). 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 n

10、on-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, Pa

11、rt 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 castin

12、g 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 16454 was prepared by Technical Committee ISO/TC 20, Aircraft and space vehicles, Subco

13、mmittee SC 14, Space systems and operations. ISO 16454:2007(E) ISO 2007 All rights reserved v Introduction From the beginning of the space age, structural integrity verification has been one of the main fields of mechanical specialists activity. Mission failure and potential danger to human life, ex

14、pensive 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 most important critical conditions for structural integrity analysis. It is usually the main criteria for space struc

15、ture 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 in structural failure, leading to high risk associated with safety of life, and loss of expensive hardware and othe

16、r 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 structures for space application. The analysis and design of space structures has a long history. This International Sta

17、ndard establishes the preferred requirements related to these techniques for static strength critical condition. INTERNATIONAL STANDARD ISO 16454:2007(E) ISO 2007 All rights reserved 1 Space systems Structural design Stress analysis requirements 1 Scope This International Standard is intended to be

18、used for the determination of the stress/strain distribution and margins of safety in launch vehicles and spacecraft primary structure design. Liquid propellant engine structures, solid propellant engine nozzles and the solid propellant itself are not covered, but liquid propellant tanks, pressure v

19、essels and solid propellant cases are within the scope of this International Standard. This International Standard provides requirements for the determination of maximum stress and corresponding margin of safety under loading, and defines criteria for static strength failure modes, such as rupture,

20、collapse and detrimental yielding. Critical conditions associated with fatigue, creep and crack growths are not covered. Notwithstanding these limitations in scope, the results of stress calculations based on the requirements of this International Standard are applicable to other critical condition

21、analyses. In accordance with the requirements of this International Standard, models, methods and procedures for stress determination can also be applied to the displacements and deformation calculations, as well as to the loads definition, applied to substructures and structural members of structur

22、es under consideration. When this International Standard is applied, it is assumed that temperature distribution has been determined and is used as input data. 2 Normative references The following referenced documents are indispensable for the application of this document. For dated references, only

23、 the edition cited applies. For undated references, the latest edition of the referenced document (including any amendments) applies. ISO 14622, Space systems Structural design Loads and induced environment ISO 14623, Space systems Pressure vessels and pressurized structures Design and operation 3 T

24、erms and definitions For the purposes of this document, the following terms and definitions apply. 3.1 A-basis allowable mechanical strength value above 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

25、strain maximum load (stress, strain) that can be accommodated by a material/structure without potential rupture, collapse or detrimental deformation in a given environment NOTE Allowable loads (stresses, strains) commonly correspond to the statistically based minimum ultimate strength, buckling stre

26、ngth and yield strength, respectively. ISO 16454:2007(E) 2 ISO 2007 All rights reserved3.3 basic data input data required to perform stress 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

27、 fall, with a confidence level of 95 % 3.5 collapse failure mode induced by quasi-static compression, shear or combined stress, accompanied 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

28、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. 3.7 creep process of a permanent material deformation resulting from long duration under constant or slowly altered load NOTE The u

29、ltimate creep deformation, corresponding to the loss of material integrity is often much larger than ultimate deformation in the case 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, sy

30、stem, subsystem or component during service life 3.9 critical location structural point at which rupture, local buckling or detrimental 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

31、variations of loads and structure resistance, and inaccuracies in the knowledge of their statistical distributions 3.11 destabilizing load load that produces compressive stress at critical location 3.12 detrimental yielding metallic structures permanent deformation specified at the system level to b

32、e detrimental 3.13 development test test to provide design information that can be used to check the validity of analytic technique and assumed design parameters, to uncover unexpected system response characteristics, to evaluate design changes, to determine interface compatibility, to prove qualifi

33、cation and acceptance procedures and techniques, to check manufacturing technology, or to establish accept/reject criteria ISO 16454:2007(E) ISO 2007 All rights reserved 3 3.14 flight-type hardware test test of a flight structure article, a protoflight model, a representative special model or a stru

34、ctural element fabricated with the same or close to flight hardware technology 3.15 gauges thickness and other structure 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 desig

35、n safety factor, which is used to determine analytically in a simple way actual or allowable loads or stresses, and which 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 maxi

36、mum that can be expected during service life and in the presence of the environment NOTE For stabilizing loads, the limit 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 environme

37、nt and adjacent parts of vehicle, and accelerations NOTE This includes pressures, external loads and enforced displacements acted at considered structural element, pretension, inertial loads caused by accelerations and thermal gradients. 3.19 loading case particular condition described in terms of l

38、oads/pressures/temperatures combinations, which can occur for some parts of structure at the same time during its service 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

39、 of that member if it occurs under loading 3.21 margin of safety M Sexpression of the margin of the limit load multiplied by design safety factor against the allowed load Another representation of the concept: AL S DS LL 1 F M fF = (1) where AL F is the allowable load under specified functional cond

40、itions (e.g. yield, rupture, collapse, local buckling); LL F is the limit load; DS f is the design safety factor. NOTE Load can imply corresponding stress or strain. ISO 16454:2007(E) 4 ISO 2007 All rights reserved3.22 minimum allowable minimum material mechanical properties warranted by the supplie

41、r 3.23 pressure external load caused by fluid action on a structural surface NOTE The terms “pressure” and “load” 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 fre

42、quencies 3.25 rupture loss of integrity by structure material differed from fatigue and ultimate creep deformation 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,

43、plates, profiles, strips, etc. 3.27 stabilizing load load which decreases compressive stresses if applied in conjunction with destabilizing loads 3.28 static strength property of a structure, characterized by its capability to withstand loads and temperature combinations without rupture, collapse, d

44、etrimental local buckling and detrimental deformation 3.29 strength failure mode condition of a structure or a structural member considered as a critical condition in accordance with stress analysis results 3.30 stress analysis analytical procedure to determine structure stress/strain distribution,

45、deformations and margins of safety 3.31 structure primary structure, unit attachments, pressure/loads carrying elements 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

46、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 ISO 16454:2007

47、E) ISO 2007 All rights reserved 5 4 Requirements 4.1 General For structures used in space systems, such as launch and space vehicles, the stress analysis and corresponding determination of margin of safety for various static strength failure modes shall meet the requirements specified in this Inter

48、national Standard. Basic data, structural models, methods for stress analysis and strength criteria are considered critical for the successful completion of these procedures. Unless otherwise noted below, there are no limitations set out in this International Standard that restrict the use of result

49、s from stress calculations for other applications. 4.2 Basic data 4.2.1 General Basic data used for space structure stress analyses shall meet the requirements included in 4.2 Basic data shall include all the following information: structural configuration, geometry and gauges, structural materials and their properties, and loading case list, load and temperature combinations, and corresponding design safety factors for every loading case. 4.2.2 Structural configuration, geometry and gauges 4.2.2.1 Struc