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时间:2019-11-26
《再入飞行器鼻锥逆向喷流对流场及气动热的影响》由会员上传分享,免费在线阅读,更多相关内容在学术论文-天天文库。
1、第3l卷2010矩第8期8月航空学报ACTAAERONAUTICAETASTRONAUTICAS1NICAV01.31NO.8Aug.2010文章编号:1000—6893(2010)08—1552—06再入飞行器鼻锥逆向喷流对流场及气动热的影响戎宜生,刘伟强(国防科学技术大学航天与材料工程学院,湖南长沙410073)InfluenceofOpposingJetonFlowFieldandAerodynamicHeatingatNoseofaReentryVehicleRongYisheng,LiuWeiqiang(CollegeofAerospaceand
2、MaterialsEngineering,NationalUniversityofDefenseTechnology,Changsha410073,China)摘要:使用计算流体力学(CFD)方法研究逆向喷流热防护系统对降低再入飞行器鼻锥物面热流的效果,获得了流场参数,回流再附点位置,物面压力分布以及热流分布。分析了逆向喷流对降低物面热流的物理机理,喷流通过与来流相互作用形成马赫盘,将来流导流到四周,不与物面直接作用形成气动加热,同时喷流回流形成低温区,降低物面与接触气体的温差,进而降低了物面热流。随着总压比率增大,这种效果越明显,气动加热越轻。为更合理分
3、析喷流强度对流场及传热量的影响,将总压比率和流量相结合,提出了新的参数R队。分析该参数的应用效果,结果发现不同的流量与总压比率组合成相同的参数R,。,可以实现相同的激波位置、再附点位置、表面热流峰值位置和总传热量。这说明该参数可用于表征喷流强度,用以分析喷流对流场及传热量的影响。关键词:逆向喷流;气动加热;总压比率;流量;热防护系统中图分类号:V211.3文献标识码:AAbstract:ACFDstudyonthereductionofaerodynamicheatingonthenoseofareentryvehiclebyanopposingjetth
4、ermalprotectionsystemisconducted,bymeansofwhichtheflowfieldparameters,reattachmentpointposition,surfacepressuredistributionandheatfluxdistributionareobtained.Thephysicalmechanismofthereductionofheatfluxisanalyzed.TheopposingjetinteractswiththefreestreamtOformaMathdiskwhichenablest
5、hefreestreamtOflowtOtheedgesratherthaninteractwiththesurfacetOproduceaerodynamicheat-ing.Inaddition,thejetflowsbacktOformacoolrecirculationregion,whichreducesthedifferenceintemper—aturebetweenthesurfaceandthenearbygas,andthusreducestheheatflux.Thelargerthetotalpressurera—tio,thelo
6、weristheaerodynamicheating.Tostudytheeffectoftheintensityoftheopposingjetmoreappro—priately,anewparameterRPAisdefinedbycombiningthefluxandthetotalpressureratio.Thestudyshowsthatthesameshockwaveposition,reattachmentpointposition,peakheatfluxpositionandtotalheatloadcanbeobtainedwith
7、thesameRPAwithdifferentfluxesandtotalpressureratios,whichmeansthenewratioparam-etermayaccountfortheintensityoftheopposingjetandbeusedtOanalyzeitsinfluenceontheflowfieldandtotalheatloadatthenoseofareentryvehicle.Keywords:opposingjet;aerodynamicheating;totalpressureratio;flux;therma
8、lprotectionsystem再入飞行器的发展中,一个亟需解决
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