Thermal Analysis Of Hypersonic Vehicle's Components With Aerodynamic Heating Influence

The development of hypersonic vehicle is a main direction in aeronautics and astronautics in 21 century. It provides impetus to the development of international strategic structure, military force contrast, science and technology, economy and society. One of the important issues in the design of hypersonic vehicle is the thermal protection.In this thesis, the design and analysis of thermal protection system (TPS) of a typical hypersonic vehicle is performed. Firstly, the aerodynamic heating methods of hypersonic vehicles are presented. In the different time, the results of aerodynamic heating are computed. The nose tip, lateral plate of inlet, lip of inlet and leading edge of tail are heated very severity. Secondly, the conceptual design of this vehicle's TPS is carried out in typical hot area. The aerodynamic heating results are used as initial boundary condition, and the thermal simulation of structure is carried out by finite element method (FEM) software. The influence of temperature to the thermal load is considered, and the heat flow rate per unit area is iteratively modified with heating time. So three dimensional transient temperature distributing is obtained with different material and different design. Thirdly, based on the temperature field, the thermal distortion and thermal stress is numerically calculated with the help of FEM. Finally, numerical solution is adopted to study thermal contact resistance (TCR) within the bolts of aircraft. The relation between TCR and roughness is researched by finite element program.The whole research of this thesis has several useful assist to thermal structure design and analysis about hypersonic vehicle, which also has certain value of engineering application.