Aerodynamic Heat And The Thermal Response Of Reentry Missile

Aerodynamic heat is unavoidable when missile head reentry the atmosphere, so it is crucial task to do such research, to provide ample theory and data for military purpose. In this paper, some methods are developed to solve the relative problems on aerodynamic heat and its response. Focused on the aerodynamic heat, the heat flux calculation is stressed, then the temperature, by way of parenthesis, the thermal stress is calculated suitably. First, This dissertation briefly introduces hypersonic flow around the missile head. It explains the deduction of the heat density and discusses the close relationship of many aerodynamics parameters in this immense calculation. Taken a certain missile head as an example, it calculates the laminar and turbulent convective heat flux over the blunt nose at zero angle of attack. Not considering the rejection, the ablation and some other factors, it gets the satisfactory results . Also it discusses the heat flux on the transition. In general, it has described an economic program to calculate, the solution and data obtained are comparable to the test results referenced. Second, it investigate the temperature field results in aerodynamic heat under hypersonic flow. Because of the axial symmetry, the question is simplified into two- dimensional calculation. Highly it values the Physical Unit and pay attention to the energy conservation. By applying finite element method, it yields solutions conveniently. Third, on the basis of known temperature field, this paper goes on to do the calculation of heat stress. This time also use the finite elements method .The temperature is taken as 憈hermal load?forced on the missile head, then such thermal stress is settled as general elasticity mechanics question, surly an effective way to do so. Such approach provides accurate results and can be realized in other analogous questions. In conclusion, this paper presents quite an integrated discourse from aerodynamic heat to its aftereffects梩emperature change and heat stress. Such schematism makes it useful to aerodynamic heat research. Based on the sound theory, it develops a credible and steady way to calculate. Taken into many realistic circumstances, it has certain value of engineering application. All the method is fast to execute, easy to program, and meet the precision requirement well.