【摘要】：飛行器在高速飛行過(guò)程中,由于飛行速度達(dá)到5馬赫,周?chē)諝鈺?huì)與光學(xué)頭罩發(fā)生嚴(yán)重摩擦,引起光學(xué)窗口外表面溫度升高,產(chǎn)生激波層和邊界層等,在目標(biāo)與光學(xué)成像設(shè)備之間產(chǎn)生不規(guī)則的梯度折射率場(chǎng),即產(chǎn)生了氣動(dòng)光學(xué)效應(yīng)。氣動(dòng)光學(xué)效應(yīng)會(huì)導(dǎo)致系統(tǒng)成像存在光程差,進(jìn)而造成波像差,產(chǎn)生偏移、抖動(dòng)、模糊,導(dǎo)引頭內(nèi)的光學(xué)成像系統(tǒng)將接收到受影響的目標(biāo)圖像,降低對(duì)目標(biāo)識(shí)別、追蹤能力。因此對(duì)超高音速飛行器氣動(dòng)光學(xué)效應(yīng)的研究在制導(dǎo)方面具有重大意義。本文首先分析了大氣氣動(dòng)光學(xué)效應(yīng)的研究歷史,尤其是對(duì)近些年來(lái)氣動(dòng)光學(xué)效應(yīng)研究取得的成就和發(fā)展趨勢(shì)進(jìn)行了詳盡分析。闡述了本文研究主要內(nèi)容為對(duì)飛行速度為5馬赫的超高音速飛行器在不同飛行條件平穩(wěn)飛行時(shí),周?chē)黧w分布情況及對(duì)成像影響。其次,通過(guò)對(duì)流體力學(xué)進(jìn)行研究,利用網(wǎng)格建模軟件建立了飛行器二維網(wǎng)格模型,本文采用了一種非均勻分布的模型網(wǎng)格對(duì)飛行器周?chē)木W(wǎng)格流場(chǎng)進(jìn)行采樣劃分。利用動(dòng)態(tài)流體力學(xué)有限元分析軟件,設(shè)定飛行器飛行參數(shù),如飛行攻角和不同環(huán)境參數(shù)變量,確定邊界條件,求解器,求解方法和求解方程,研究了邊界層和激波的氣動(dòng)光學(xué)效應(yīng);調(diào)整飛行器飛行攻角與飛行環(huán)境參數(shù)變量,對(duì)結(jié)果進(jìn)行比較分析得出不同參數(shù)對(duì)飛行器周?chē)鲌?chǎng)的影響。再次,本文對(duì)光線(xiàn)在流場(chǎng)中傳播方式進(jìn)行了研究分析,結(jié)合光線(xiàn)追跡法和物理光學(xué)法,通過(guò)研究傳統(tǒng)的光線(xiàn)追跡法使用了一種固定步長(zhǎng)光線(xiàn)追跡法,能夠在不影響計(jì)算精確度的情況下簡(jiǎn)化建模難度。最后,本文對(duì)所得數(shù)據(jù)進(jìn)行了分析得出結(jié)果,將仿真結(jié)果與理論進(jìn)行比較,并對(duì)結(jié)果進(jìn)行了理論上的解釋。綜上,本文所研究的主要內(nèi)容為通過(guò)Fluent生成光學(xué)窗口周?chē)鷧^(qū)域的空氣密度離散分布,使用MATLAB讀取得到的數(shù)據(jù)建立折射率的離散分布,并模擬無(wú)限遠(yuǎn)處點(diǎn)源的入射光線(xiàn),通過(guò)固定步長(zhǎng)的光線(xiàn)追跡法得到在光學(xué)窗口面上波像差分布,并做傅立葉變換得到相面的復(fù)振幅分布,進(jìn)而分析像質(zhì)評(píng)價(jià)函數(shù)并獲得結(jié)論。
[Abstract]:During the high speed flight, due to the flight speed of Mach 5, the surrounding air will have serious friction with the optical hood, which will cause the temperature of the outer surface of the optical window to rise, resulting in shock layer and boundary layer, etc. There is an irregular gradient refractive index field between the target and the optical imaging equipment, that is, the aero-optical effect is produced. The effect of aero-optics will lead to the optical path difference in the imaging of the system, which will lead to wave aberration, offset, jitter, blur, and the optical imaging system in the seeker will receive the affected target image and reduce the ability of target recognition and tracking. Therefore, the study of aerodynamic optical effect of hypersonic vehicle is of great significance in guidance. In this paper, the research history of atmospheric aero-optical effects is first analyzed, especially the achievements and development trends of aero-optical effects in recent years are analyzed in detail. The main content of this paper is the fluid distribution and its influence on the imaging of supersonic aircraft with a speed of 5 Mach when it flies smoothly under different flight conditions. Secondly, through the research of fluid mechanics, the two-dimensional mesh model of aircraft is established by using the grid modeling software. A non-uniform distributed model grid is used to sample and partition the grid flow field around the aircraft. Using the finite element analysis software of dynamic fluid dynamics, the flight parameters, such as flight angle of attack and variables of different environmental parameters, are set, boundary conditions, solver, solving methods and solving equations are determined. The aero-optical effects of the boundary layer and shock wave are studied, and the influence of different parameters on the flow field around the aircraft is obtained by adjusting the flight angle of attack and the flight environment parameter variables. Thirdly, this paper studies and analyzes the propagation mode of light in the flow field. Combining the ray tracing method and physical optics method, a fixed step ray tracing method is used by studying the traditional ray tracing method. It can simplify the modeling difficulty without affecting the calculation accuracy. Finally, the results are analyzed, and the simulation results are compared with the theory, and the results are explained theoretically. In summary, the main content of this paper is to generate the discrete distribution of air density in the area around the optical window by Fluent. The discrete distribution of refractive index is established by using the data read from MATLAB, and the incident light of point source in infinite distance is simulated. The wavefront aberration distribution on the optical window surface is obtained by the ray tracing method with fixed step size, and the complex amplitude distribution of the phase surface is obtained by Fourier transform, and the image quality evaluation function is analyzed and the conclusion is obtained.
【學(xué)位授予單位】：北京理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類(lèi)號(hào)】：V211

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