CAJ | 학술논문

为了提高高马赫飞行下光学窗口的光学性能，对比分析了基于气动光学效应三种飞行器模型不同攻角的马赫数场、密度场、温度场和压力场的流场结构及对光学性能的影响。首先,根据飞行器与来流的迎风面，建立了三种飞行器典型模型；继而,给出了0o、5o和10o攻角飞行工况；然后,建立了基于Navier-Stokes方程和湍流模型的三种攻角流场分布；最后,对比分析了宽平头体飞行器中三种攻角温度场作用下的光学系统传递函数。结果表明，马赫数场与密度场、温度场与压力场分别具有相似分布形式；相同飞行速度和攻角下，大迎风面的飞行器光学窗口周围温度与压力较小迎风面大；相同飞行器，较大攻角对应较大流场强度，攻角为0o、5o和10o时传递函数分别为0.188，0.097和0.028。此分析结果可为高马赫飞行下光学窗口优化提供一定的理论依据。
위료제고고마혁비행하광학창구적광학성능，대비분석료기우기동광학효응삼충비행기모형불동공각적마혁수장、밀도장、온도장화압력장적류장결구급대광학성능적영향。수선,근거비행기여래류적영풍면，건립료삼충비행기전형모형；계이,급출료0o、5o화10o공각비행공황；연후,건립료기우Navier-Stokes방정화단류모형적삼충공각류장분포；최후,대비분석료관평두체비행기중삼충공각온도장작용하적광학계통전체함수。결과표명，마혁수장여밀도장、온도장여압력장분별구유상사분포형식；상동비행속도화공각하，대영풍면적비행기광학창구주위온도여압력교소영풍면대；상동비행기，교대공각대응교대류장강도，공각위0o、5o화10o시전체함수분별위0.188，0.097화0.028。차분석결과가위고마혁비행하광학창구우화제공일정적이론의거。
To improve the optical performance of optical window on the condition of high Mach flying, the structures of flight number field, density field, temperature field and pressure field corresponding to three kinds of aircraft on the angle of attack conditions on 0o, 5o and 10o were provided and compared in this paper, as well as the influence to the optical properties of optical system. Firstly, three typical kinds of aircraft models were established based on the windward area of the aircraft head; secondly, the flight conditions on the angle of attack of 0o, 5o and 10o as well as the flight initial environment were provided; then, according to the Navier -Stokes equation and the turbulent model, the flow field distributions corresponding to the three kinds of aircraft model on the conditions of 0o, 5o and 10o were obtained and analyzed; finally, taking the optical system on the operating condition of the flat-head aircraft as an example, the Modulation Transfer Function(MTF) on the operating conditions of the three kinds of attack angle were compared and analyzed. By the analyzed results, the Mach field and the destiny field, the temperature field and press field have the same distribution respectively;in the same flight velocity and angle of attack, the optical window of the aircraft owning large windward side has larger temperature and press than the optical window of small windward side aircraft;being the same aircraft, the operating condition of larger angle of attack corresponds to large flow field around the optical window. When the angles of attack are 0o, 5oand 10o, the values of MTF are 0.188, 0.097 and 0.028, respectively. The work of this study may provide a theoretical basis for the optimization of optical window on the operating condition of high Mach.