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1、第35卷第4期航天返回与遥感2014年8月SPACECRAFTRECOVERY&REMOTESENSING17充气式返回舱气动热特性研究1,22高艺航贺卫亮(1北京宇航系统工程研究所,北京100076)(2北京航空航天大学宇航学院,北京100191)摘要文章针对航天器返回实时性和经济性的需求,以充气式返回舱为研究对象,研究该飞行器从空间站返回过程中的气动特性,重点分析气动热特性。文章通过引入分子运动论、Kemp-Riddell方法、Linear桥函数等计算方法,建立起该飞行器在自由分子流区、过渡流区和连续流区高超声速情况下的表面热平衡方程,得出了该飞
2、行器返回过程中的驻点热流密度和驻点壁面温度。计算分析了该飞行器最大直径D1和半锥角α等几何尺寸对其气动热特性的影响,得到在一定范围内增大D1和α可以有效减小驻点热流密度和驻点壁面温度,并研究在峰值加热高度附近70km、80km处不同马赫数下的气动热特性。在此基础上,依据热防护系统材料和布局,将气动加热计算的表面热流分布作为外壁边界条件,分析了结构材料层的温度变化特性。关键词充气展开再入减速气动热特性航天返回中图分类号:V475.9文献标志码:A文章编号:1009-8518(2014)04-0017-09DOI:10.3969/j.issn.1009-
3、8518.2014.04.003ResearchonAerodynamicHeatingCharacteristicsofInflatableReentryDecelerator1,22GAOYihangHEWeiliang(1BeijingInstituteofAstronauticalSystemsEngineering,Beijing100076,China)(2SchoolofAstronautics,BeihangUniversity,Beijing100191,China)AbstractAccordingtotherequirement
4、ofreal-timereentryforaspacecraft,thispaperpresentsadetailedanalysisofaerodynamicsforInflatableReentryDecelerator’sreentryfromtheInternationalSpaceStation,duringwhichaerodynamicheatingisespeciallyconsidered.Basedontheheattransfercalculationmethods,theoryofmolecularmotion,Kemp-Ri
5、ddellandLinearbridgefunctions,theheattransfersimulationmodelsareestablishedinfree-streamregime,transitionalflowregime,andcontinuumregimeofhypersoniccondition,andtheheatfluxofstagnationcanbecalculated,aswellasstagnationtemperature.Theeffectsofthestructuralpa-rameterssuchasmaximu
6、mdiameterofD1andhalfconeangleαonthecharacteristicsofaerodynamicheatingareanalyzedanditisdemonstratedthatstagnationheatfluxandtemperaturecanbereducedapparentlyasD1andαincreasetosomeextent.Fortheareanearthepeakstagnationheating,theheights70kmand80kmarechosentobespeciallystudiedon
7、theircharacteristicsofaerodynamicheatingastheMachnumberincreases.Thethermalprotectionsystem(TPS)materialsarechosenandarranged.Accordingtothelayout,temperaturesatvariouslayersarecalculatedwiththesurfaceheatfluxdistributionasouterboundarycondition.Keywordsinflatable;reentry;decel
8、eration;aerodynamicheatingcharacters;spacecraftrecover