The Numerical Method Of Temperature Field And Infrared Radiation Signature Of Air-breathing Hypersonic Vehicle

In recenter years,hypersonic technology is the direction of weapon developing that many military great powers pay attention to.The study on the temperature field of hypersonic vehicle can guide designers to select the materials.The research on the infrared radiation can provide reference data for the infrared detection system against the hypersonic vehicle.In this thesis,the numerical method of the temperature field and infrared radiation signature of air-breathing hypersonic vehicle was studied.In the simulation of the temperature field of air-breathing hypersonic vehicle,the computational domain was divided into a domain which does not contain the combustor and another domain containing combustor.The Reynolds averaged NS equation was used to simulate the flow field in the computational domain which does not contain the combustor.The effect of the turbulence model and variable specific heat capacity on aerodynamic heat of hypersonic flow was discussed.In the combustor domain,a quasi one dimensional calculation method for the temperature field of the regenerative combustor was developed,which can be used to quickly evaluate the combustor's cooling structure.In this thesis,the discrete transfer method was used as the numerical method of the infrared radiation of hypersonic vehicle.A vector method used on GPU was proposed to calculate the view factor,which can significantly reduce the computation time.The temperature field and infrared radiation signature of Air-breathing hypersonic vehicle at different mach number,was calculated.The infrared of the aircraft and hypersonic vehicle was compared.