GPU Accelerated Real-time Infrared Characteristic Simulation Of High-speed Flying Object

Infrared simulation are widely used in military, industrial and agricultural production, resource exploration and other fields. Traditional infrared simulation needs a large amount of computation and is required to solve the temperature field data at different moment in advance, the image of infrared simulation can not be generated until temperature field of all moment has been solved. This simulation method for solving temperature field and outputing the results of infrared simulation is not real-time. It does not apply to the high-speed flying target problem which operating conditions change frequently and the results of infrared simulation need to be output synchronously. Since GPU with excellent floating point arithmetic capability, can effectively improve the real-time of infrared simulation, it has great significance for researching on GPU-based real-time infrared simulation. In the paper real-time infrared simulation of a typical high-speed flying target is studied, an unsteady three-dimention temperature field code is programming which is based on finite volume method to simulate the flying target. Then partial solving numerical calculation of temperature field is ported to GPU to improve the speed of temperature field solver and achieve real-time simulation.The paper presents the finite volume method of solving the unsteady three-dimensional temperature field, and uses additional heat source method to derive different types of boundary conditions, finally gets a unified treatment of the boundary conditions. By comparing the caculating results of the unsteady three-dimensional temperature field solver code with the results of FLUENT in different types of boundary conditions, the correctness of the code is verified.Adiabatic wall temperature and constant wall temprature heatflux under different flight altitudes and different flight speeds were calculated by FLUENT, these data were interpolated by inverse distance interpolation method to the target skin mesh. Aerodynamic heating flux database is established and added to unsteady temperature field solver program as additional heatflux source and then the unsteady temperature field of the target along the designated flight track is solved. Different wave band radiometric force distribution were caculated according to the known temperature field.Unsteady three-dimensional temperature field solver based on GPU parallelly computing CUDA implement method is proposed, and the speedup ratio of the method achieved is analysed. When the number of cells is few, this method based on GPU parallel algorithm can not achieve accelerating effect. With increase of the number of cells, speedup ratio is increasing. It indicated that a large number of grid model adopting the GPU parallel computing acceleration method better. Finally, the graphic of the target’s skin temperature field is real-time displayed by Open GL.