Design Of Ceramic Thermal Protect System Considering Fairing Of Its Inner Curve

With the rapid development of space technology,reusable launch vehicles(RLV)have become hotspots of major countries and regions because of its powerful features and economic advantages.Different from other spacecraft,RLV encounter severe aerodynamics heating problem which leads to the birth of thermal protection system(TPS).As one of the most important subsystem of RLV,TPS must be considered in the conceptual stage of the design of RLV.Considering the needs of automated design of ceramic TPS in the conceptual stage,this paper introduce the design process of TPS from reading and processing heat flux data of design nodes to calculation of radiation equilibrium temperature,from selecting backup material of protection layer to analyzing 1-D transient heat transfer model and from optimizing thickness of protection layer to outputting the result of design nodes.And achieve the goal of automated design of TPS by using integration platform Isight.Then,in order to eliminate discontinuity of inner curve due to changing of material caused by uneven distributing of heat flux,this paper propose a fairing method basing on least square method and hermit form of cubic spline interpolation and use Matlab complete the programming of fairing method.Finally,using a 2-D airfoil example to demonstrate the integration of automated design process of TPS and fairing method showed in this paper are effective.