The Rapid Engineering Aero-heating Calculation And Thermal Respond For Complex Shaped Hypersonic Vehicles

Aerodynamic-heating is one of the inevitable key techniques during theinvestigation and design of hypersonic vehicle. It also can directly affect the vehicle’sperformance and safety. Focusing on aerodynamic-heating on the surface ofhypersonic vehicle, a engineering method, which is applicable for complex shapedvehicles, to calculate the heat flux distribution is established in this thesis.Based on penal method, the aerodynamic-pressure distribution on hypersonicvehicle surface is calculated by using modified Newtonian theory. First, the vehiclesurface is meshed with non-structural mesh, then by using modified Newtoniantheory, the aerodynamic-pressure in every triangle penal is calculated according toNewton’s second law. Last, the aerodynamic-pressure distribution on the wholesurface is gotten by adding that in every penal up. The streamline trajectory on thevehicle surface is calculated based on Newtonian steepest method, then by utilizingthe pressure distribution, reference enthalpy method, and fitted function of hightemperature gas parameters, the gas parameters on the streamline are given, which areused to get the Reynolds number and the heat flux on the target point.To validate the aerodynamic-heating calculation method given in this thesis, afew models are tested. First, the heat flux on stagnation point of blunt-nosed body aregiven. Then heat flux distribution on the surface of lifting body, wave rider body andblunt-nosed body in the situation with different attack angle are calculated.Finally, the heat flux calculated before is loaded to the finite element model andthe penal’s thermal response on lifting body is gotton. The thickness of TPS isoptimized. And the nose cap’s thermal response during flight is investigated.The result indicates that the method for calculating aerodynamic-heating offeredin this thesis can obviously simplify the solution procedure by using reasonableengineering approximation, be fit for aerodynamic-heating calculation on complexconfiguration body both in efficiency and precision, and meet the need of engineeringestimation. In a word, it can provide certain reference in practical application.