基于GPU并行加速的高速飛行目標(biāo)實時紅外仿真技術(shù)研究
發(fā)布時間：2019-02-12 18:15
【摘要】：紅外仿真在軍事、工農(nóng)業(yè)生產(chǎn)、資源勘探等領(lǐng)域都有廣泛應(yīng)用,傳統(tǒng)的紅外仿真的計算量很大,需要預(yù)先求解不同時刻的溫度場數(shù)據(jù),在所有時刻的溫度場求解完成后才可生成紅外仿真結(jié)果。這種仿真方法中溫度場的求解和紅外仿真結(jié)果輸出不具有實時性,不適用于運行工況需要經(jīng)常變化且需要同步輸出紅外仿真結(jié)果的高速飛行目標(biāo)問題。由于GPU具有出色的浮點運算能力,可以有效提高紅外仿真的實時性,因此對基于GPU并行加速的實時紅外仿真的研究具有重要的意義。本文針對典型高速飛行目標(biāo)的實時紅外仿真進行了研究,編寫了三維非穩(wěn)態(tài)溫度場求解程序,對目標(biāo)非穩(wěn)態(tài)溫度場進行模擬。然后將溫度場求解的部分?jǐn)?shù)值運算移植到GPU中,提高溫度場求解的速度,達到實時仿真的目的。本文首先介紹了三維非穩(wěn)態(tài)溫度場求解的有限體積法,采用附加熱源法對不同類型的邊界條件進行推導(dǎo),最終得到一個統(tǒng)一的邊界條件處理方式。通過對比不同類型的邊界條件下FLUENT計算結(jié)果和程序計算結(jié)果,驗證了三維非穩(wěn)態(tài)溫度場求解程序的正確性。使用FLUENT計算出不同飛行高度和飛行速度下的絕熱壁溫和定壁溫?zé)崃?將這些數(shù)據(jù)通過距離反比插值方法插值到目標(biāo)蒙皮網(wǎng)格上,建立目標(biāo)氣動加熱熱流數(shù)據(jù)庫,以此為基礎(chǔ)建立目標(biāo)氣動加熱參數(shù)化模型,以附加熱流的形式加入非穩(wěn)態(tài)溫度場求解程序中,對目標(biāo)沿指定軌跡飛行過程的非穩(wěn)態(tài)溫度場進行求解分析,并由已知的溫度場求解出目標(biāo)不同波長范圍的輻射力分布。提出了一種基于GPU并行計算的三維非穩(wěn)態(tài)溫度場求解的CUDA實現(xiàn)方法,對該方法能實現(xiàn)的加速比進行分析,發(fā)現(xiàn)在網(wǎng)格數(shù)目較少的情況下,采用這種GPU并行算法不能起到加速效果,當(dāng)網(wǎng)格數(shù)目增大時,加速比隨網(wǎng)數(shù)目的增加而增加,說明對大網(wǎng)格數(shù)目的模型采用GPU并行運算加速效果較好。最后利用Open GL實時顯示該典型高速飛行目標(biāo)的蒙皮溫度場圖像。
[Abstract]:Infrared simulation is widely used in military, industrial and agricultural production, resource exploration and so on. The traditional infrared simulation has a large amount of calculation, so it is necessary to solve the temperature field data at different times in advance. The infrared simulation results can only be generated after the solution of the temperature field is completed at all times. In this method, the solution of temperature field and the output of infrared simulation results are not real-time, so they are not suitable for the high-speed flight target which needs to change frequently and needs to output the infrared simulation results synchronously. Because GPU has excellent floating-point computing ability and can effectively improve the real-time performance of infrared simulation, it is of great significance to study real-time infrared simulation based on parallel acceleration of GPU. In this paper, the real-time infrared simulation of a typical high-speed flying target is studied, and a three-dimensional unsteady temperature field solution program is developed to simulate the unsteady temperature field of the target. Then the partial numerical operation of temperature field solution is transplanted into GPU to improve the speed of temperature field solution and achieve the purpose of real-time simulation. In this paper, the finite volume method for solving the three-dimensional unsteady temperature field is introduced, and the additional heat source method is used to deduce the boundary conditions of different types. Finally, a unified boundary condition treatment method is obtained. The correctness of the three-dimensional unsteady temperature field solution program is verified by comparing the results of FLUENT calculation and program calculation under different boundary conditions. Using FLUENT to calculate the adiabatic wall and constant wall heat flow at different flight altitudes and velocities, the data are interpolated to the target skin mesh by the inverse distance interpolation method, and the target aerodynamic heating heat flow database is established. Based on this, a parameterized model of target aerodynamic heating is established. The unsteady temperature field of the target flying along the specified trajectory is solved and analyzed by adding the unsteady temperature field in the form of additional heat flux. The radiation force distribution in different wavelength range of the target is obtained from the known temperature field. In this paper, a CUDA implementation method for solving 3D unsteady temperature field based on GPU parallel computing is proposed. The speedup ratio of this method is analyzed, and it is found that the number of meshes is small. Using this GPU parallel algorithm can not accelerate the result. When the number of mesh increases, the speedup ratio increases with the increase of the number of grids, which shows that the acceleration effect of GPU parallel operation is better for the model with large mesh number. Finally, Open GL is used to display the skin temperature field image of the typical high speed flying target in real time.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TN219
本文編號：2420663
[Abstract]:Infrared simulation is widely used in military, industrial and agricultural production, resource exploration and so on. The traditional infrared simulation has a large amount of calculation, so it is necessary to solve the temperature field data at different times in advance. The infrared simulation results can only be generated after the solution of the temperature field is completed at all times. In this method, the solution of temperature field and the output of infrared simulation results are not real-time, so they are not suitable for the high-speed flight target which needs to change frequently and needs to output the infrared simulation results synchronously. Because GPU has excellent floating-point computing ability and can effectively improve the real-time performance of infrared simulation, it is of great significance to study real-time infrared simulation based on parallel acceleration of GPU. In this paper, the real-time infrared simulation of a typical high-speed flying target is studied, and a three-dimensional unsteady temperature field solution program is developed to simulate the unsteady temperature field of the target. Then the partial numerical operation of temperature field solution is transplanted into GPU to improve the speed of temperature field solution and achieve the purpose of real-time simulation. In this paper, the finite volume method for solving the three-dimensional unsteady temperature field is introduced, and the additional heat source method is used to deduce the boundary conditions of different types. Finally, a unified boundary condition treatment method is obtained. The correctness of the three-dimensional unsteady temperature field solution program is verified by comparing the results of FLUENT calculation and program calculation under different boundary conditions. Using FLUENT to calculate the adiabatic wall and constant wall heat flow at different flight altitudes and velocities, the data are interpolated to the target skin mesh by the inverse distance interpolation method, and the target aerodynamic heating heat flow database is established. Based on this, a parameterized model of target aerodynamic heating is established. The unsteady temperature field of the target flying along the specified trajectory is solved and analyzed by adding the unsteady temperature field in the form of additional heat flux. The radiation force distribution in different wavelength range of the target is obtained from the known temperature field. In this paper, a CUDA implementation method for solving 3D unsteady temperature field based on GPU parallel computing is proposed. The speedup ratio of this method is analyzed, and it is found that the number of meshes is small. Using this GPU parallel algorithm can not accelerate the result. When the number of mesh increases, the speedup ratio increases with the increase of the number of grids, which shows that the acceleration effect of GPU parallel operation is better for the model with large mesh number. Finally, Open GL is used to display the skin temperature field image of the typical high speed flying target in real time.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TN219
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相關(guān)期刊論文 前3條
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，本文編號：2420663
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