›› 2014, Vol. 34 ›› Issue (3): 23-31.doi: 10.3780/j.issn.1000-758X.2014.03.004
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YUGuangxue1,LIZhaoying1,LINPing1,2
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Abstract: Areusablelaunchvehicle(RLV)reentryconceptualdesignandcontrolmodelingresearchwerepresentedforschemeanalysisinthepreliminarydesignstage.TheRLVaerodynamicconfigurationwasawingbodycombinationwithtwoelevonsatthewingtrailingedge,arudderontheverticaltailandaflapattheendofthebody.TheRCS/Aerosurfacescompoundcontrolmathematicalmodelwasdevelopedforattitudecontrol.Inordertorapidlyaccomplishthepreliminaryaerodynamicdatabases,theengineeringpredictionmethodwasappliedtocalculatetheaerodynamicforcesandmoments.Theaerodynamicregionsimplementedwasrarefiedflow,transitionalflow,andhypersoniccontinuumflow.Thecontrolanalysissupportedtheevolutionofthedesigntoprovideanoptimaldesign.AsixdegreesoffreedomreentrysimulationshowsthattheRLVaerodynamicandcontrolmodelhasthesameflightperformancesasthespaceshuttleorbiter.
Key words: Reusablelaunchvehicle, Reentry, Attitudecontrol, Modeling, Reactioncontrolsystem
Yu Guang-Xue, LI Zhao-Ying, LIN Ping. RLVReentryMathematicalModeling[J]. , 2014, 34(3): 23-31.
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