BS ISO 14953-2000 Space systems Structural design Determination of loading levels for static qualification testing of launch vehicles《航天系统 结构设计 运载火箭静态限定试验用负载水平的测定》.pdf

1、| | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | BRITISH STANDARD AEROSPACE SERIES BS ISO 1

2、4953:2000 ICS 49.140 NO COPYING WITHOUT BSI PERMISSION EXCEPT AS PERMITTED BY COPYRIGHT LAW Space systems Structural design Determination of loading levels for static qualification testing of launch vehiclesThis British Standard, having been prepared under the direction of the Engineering Sector Com

3、mittee, was published under the authority of the Standards Committee and comes into effect on 15 June 2000 BSI 06-2000 ISBN 0 580 34583 1 BS ISO 14953:2000 Amendments issued since publication Amd. No. Date Comments National foreword This British Standard reproduces verbatim ISO 14953:2000 and implem

4、ents it as the UK national standard. The UK participation in its preparation was entrusted to Technical Committee ACE/68, Space systems and operations, which has the responsibility to: aid enquirers to understand the text; present to the responsible international/European committee any enquiries on

5、the interpretation, or proposals for change, and keep the UK interests informed; monitor related international and European developments and promulgate them in the UK. A list of organizations represented on this committee can be obtained on request to its secretary. Cross-references The British Stan

6、dards which implement international or European publications referred to in this document may be found in the BSI Standards Catalogue under the section entitled “International Standards Correspondence Index”, or by using the “Find” facility of the BSI Standards Electronic Catalogue. A British Standa

7、rd does not purport to include all the necessary provisions of a contract. Users of British Standards are responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, a

8、n inside front cover, the ISO title page, pages ii and iii, a blank page, pages 1 to 4, an inside back cover and a back cover. The BSI copyright notice displayed in this document indicates when the document was last issued.Referencenumber ISO14953:2000(E) INTERNATIONAL STANDARD ISO 14953 Firsteditio

9、n 2000-05-01 SpacesystemsStructuraldesign Determinationofloadinglevelsforstatic qualificationtestingoflaunchvehicles Systmes spatiaux Conception des structures Dtermination des niveaux de chargement pour un essai statique de qualification des vhicules lanceursISO14953:2000(E) ii ISO14953:2000(E)iii

10、Foreword ISO(theInternationalOrganizationforStandardization)isaworldwidefederationofnationalstandardsbodies(ISO memberbodies).TheworkofpreparingInternationalStandardsisnormallycarriedoutthroughISOtechnical committees.Eachmemberbodyinterestedinasubjectforwhichatechnicalcommitteehasbeenestablishedhas

11、therighttoberepresentedonthatcommittee.Internationalorganizations,governmentalandnon-governmental,in liaisonwithISO,alsotakepartinthework.ISOcollaboratescloselywiththeInternationalElectrotechnical Commission(IEC)onallmattersofelectrotechnicalstandardization. InternationalStandardsaredraftedinaccorda

12、ncewiththerulesgivenintheISO/IECDirectives,Part3. DraftInternationalStandardsadoptedbythetechnicalcommitteesarecirculatedtothememberbodiesforvoting. PublicationasanInternationalStandardrequiresapprovalbyatleast75%ofthememberbodiescastingavote. Attentionisdrawntothepossibilitythatsomeoftheelementsoft

13、hisInternationalStandardmaybethesubjectof patentrights.ISOshallnotbeheldresponsibleforidentifyinganyorallsuchpatentrights. InternationalStandardISO14953waspreparedbyTechnicalCommitteeISO/TC20, Aircraft and space vehicles, SubcommitteeSC14, Space systems and operations.INTERNATIONALSTANDARD ISO14953:

14、2000(E)1 SpacesystemsStructuraldesignDeterminationofloading levelsforstaticqualificationoflaunchvehicles 1 Scope ThisInternationalStandardspecifiesaprocedurefordeterminingtheloadinglevelofaqualificationtestofalaunch vehiclestructureandtakesintoaccountalltheminimumallowablestrengthcharacteristicsnece

15、ssaryforthese structures. ThisInternationalStandardestablishestherequiredresistancenecessaryforallmass-produceditemstocomply withproductassurancecriteria. 2 Termsanddefinitions ForthepurposesofthisInternationalStandard,thefollowingtermsanddefinitionsapply. 2.1 externalmechanicalloading systemofforce

16、sandmomentsexternaltoastructureandbroughttobearonthatstructure 2.2 safetyfactor J coefficientbywhichalimitloadismultiplied 2.2.1 yieldstrengthsafetyfactor J E ratiooftheyieldloadofthematerialtothelimitload NOTE Thiscoefficientisapplicableonlytometalstructures. 2.2.2 ultimatesafetyfactor J R ratiooft

17、heallowableultimateloadtothelimitload 2.3 overload excessofinternaldistributedloadusedforcertaincalculationstoaccountfordesign 3 Designofloadinglevels 3.1 General Qualificationtestsshallbeconductedonaflight-typestructure.Becausesuchstructuresareunlikelytoinclude minimumvaluesforallallowablecharacter

18、istics,theloadsusedfordesignshallbecorrectedbeforeuseinISO14953:2000(E) 2 qualificationtests.Allareasofthelaunch-vehicleflightstructureshowntobecriticalinprobablefailuremodesshall beconsideredforthefollowingcorrectionwhichshallbeusedtodeterminequalificationtestloading. 3.2 Calculationofqualification

19、testloading Thecorrectedexternalloading,P Q ,(force,moment,pressure)usedforqualificationtestsshallbecalculatedfrom thefollowingequation: PPJ Q lim C where P lim istheexternalloadinglimitcorrespondingtotheofthehigheststresscombinationofexternalloadslikely tooccursimultaneouslywhileinservice(valueused

20、fordesign); J C isthecorrectedsafetyfactor(see3.3). 3.3 Correctedsafetyfactor Thecorrectedfactor,J C ,isgivenbythefollowingequation: J JK K K KK T C adj min where: J isthesafetyfactorusedfordesign(eitherforyieldorforultimateconditions); K min isthecorrectionfactorforthickness(see3.4.1); K adj isthec

21、orrectionfactorforadjacentstructures(see3.4.2); K T isthecorrectionfactorforthermalgradients(see3.4.3); K isthecorrectionfactorfortemperature(see3.4.4); K isthecorrectionfactorforthemoduli(see3.4.5). 3.4 Correctionfactors 3.4.1 Correctionfactorforthickness,K min Thisfactortakesintoaccounttheinfluenc

22、eoftheminimumthicknessonthestructureresistance;itisdefinedas theratioofthethicknessofthetestspecimentotheminimumallowablemanufacturingthickness. Thiscorrectionfactorisapplicableonlytometalstructures.Forotherstructures,useK min =1. 3.4.2 Correctionfactorforadjacentstructures,K adj 3.4.2.1 Generallysp

23、eakingduringstaticqualificationtests,theinfluenceofadjacentstructuresshouldbe simulated.Inthiscase,takeK adj =1. 3.4.2.2 Whentheinfluenceofadjacentstructurescannotbesimulatedcorrectlybythetestfacility,usea correctionfactorK adj .Theauthorityinchargeofthestructureshalldeducethisfactorbycomparingresul

24、tsoftwo calculationsmadefromthetheoreticalmodel.ISO14953:2000(E)3 3.4.2.3 Makethefirstcalculationusingboundaryconditionsofthetestconfigurationandyieldsandforeach area,determinethestress test . 3.4.2.4 Makethesecondcalculationusingboundaryconditionsoftheflightconfigurationandyieldsand determinethestr

25、ess flight . Inbothcalculations,theconfigurationshallincludethelocalstiffnessofinterfaceswithoutoverload. 3.4.2.5 ThefactorK adj isdeterminedby: KK adj flight test overload whereK overload istheoverloadfactorusedfordesignW1. If,asaresultK adj 1,useK adj =1. 3.4.3 Correctionfactorforthermalgradients,

26、K T Thisfactoristheratiooftheincreaseinstressresultingfromtheeffectofthelocalthermalgradienttothestress correspondingtoazerothermalgradient. 3.4.4 Correctionfactorfortemperature,K Thisfactortakesintoaccounttheeffectoftemperatureonthecharacteristicsofthematerial;itisdefinedasthe ratioofthevalueofthec

27、haracteristicconsideredattheoperatingtemperatureoftheflightstructuretoitsvalueat thetesttemperature: K C C , , flight test where C ,flight isacharacteristicattheoperatingtemperature; C ,test isacharacteristicatthetesttemperature. 3.4.5 Correctionfactorforthemoduli,K Thisfactortakesintoaccounttheeffe

28、ctofYoungsmodulus,allowablestresses,andgeometryonthewrinkling strength,compressionstrength,andtensilestrengthofthestructureattheambienttemperature.Fora characteristicC i actinginagivenfailuremode: K fC fC i i () () , , min test where C i,min istheminimumallowablevalueofthecharacteristicC i atambient

29、temperature(20C); C i,test isthevalueofcharacteristicC i forthespecimensubjectedtothetestat20C; f(C i ) isthefunctionwhichtranslatestheeffectofthegivencharacteristicsinthefailuremodeconsidered.ISO14953:2000(E) 4 EXAMPLE:f(C 1 )=C 1 2 ,ifthestructurestrengthisproportionaltothesquareofC 1 inthefailure

30、modeconsidered. IfseveralcharacteristicsC 1 ,C 2 ,.,C n ,actinthefailuremodeconsidered,theywillgivethefollowingequation: K fC fC fC fC fC fC n n () () )() () test test test 1 1 2 2 ,min , ,min , ,min , ( () NOTE Withmetalstructures,theminimumthicknessistheminimumallowablemanufacturingthickness. 3.5

31、Comparisonofresults Iftheresultsofcalculationsofstressmadefortestconditionsaresignificantlydifferentfromthosemadeforflight conditionsorifthecorrectedsafetyfactor,J C ,reachesanon-crediblevalue,otherspecificmodesoftestsand correctionofdesignloads,i.e.otherthanthoseproposedinthisInternationalStandard,

32、maybeusediftheyhave beenalreadyestablished,justifiedandpreviouslyused. 3.6 ImplementationofthisInternationalStandard Thecorrectedexternalloadingshallbedeterminedforalltheareasoftheflight-typestructureconsideredascritical accordingtocalculationsinviewofprobablefailuremodes. ThelowestvalueofP Q shallb

33、eselectedforqualificationtests.BS ISO 14953:2000 BSI 389 Chiswick High Road London W4 4AL | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | | |

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