光学成像制导技术是精确制导武器研究的重要课题，气动光学效应的存在对制导精度产生严重的影响，使飞行器偏离目标位置，甚至脱靶。飞行器和来流之间的相互作用导致其周围流场结构非常复杂，激波、膨胀波以及湍流边界层的存在，使得流场的折射率在空间上分布不均匀，在时间上存在高频脉动。其中，边界层转捩过程引起的气动光学畸变是亟待解决的最大难题。边界层转捩过程是边界层由层流向湍流发展的过程，是一个多因素耦合影响的强非线性、复杂的流动现象，并且一直是湍流研究领域的热点问题。超声速边界层的转捩区具有非常强的非定常性、随机性，且脉动频率高，因此折射率分布极为复杂，光线透过后不仅会发生偏折，还会导致成像模糊和能量分散，严重影响成像制导的精度，通过光学校正的方法很难降低这种影响。本文试图通过延迟边界层转捩，来降低甚至消除超声速边界层转捩对光学传输性能的影响。以超声速旋成体飞行器光学窗口周围的边界层流场为研究对象，本文采用添加扰动片的流动控制方法对边界层气动光学效应变化规律进行了数值模拟研究。研究结果表明：随着攻角的增大，光程差分布由沿着对称面对称分布逐渐过渡为沿流向的变化，且逐渐平缓；施加了扰动片控制后，原本处于光学窗口上方的边界层转捩位置后移，窗口上方流场由转捩区逐渐变为层流区，抑制气动光学效应的效果显著。

Optical imaging detection technology is an important subject in the study of precision guided weapons. The aero-optical effects has a big influence on the guidance precision, and it can make the vehicle off the target position, or even off the target. The interaction between the aircraft and the incoming flow leads to a very complex flow field structure around it. The existence of shock waves, expansion waves and turbulent boundary layer makes the refractive index of the flow field unevenly distributed in space and high frequency jitter in time. Among them, the aero-optical distortion caused by the boundary layer rotation process is the biggest problem to be solved urgently. Boundary layer transition, as a process of boundary layer flow from laminar to turbulent state, is a strong nonlinear complex flow physical phenomenon influenced by multi-factor coupling, and has been a hot topic in turbulence research field.The transition region of the supersonic boundary layer is very unsteady and random, and the pulsation frequency is high, so the refractive index distribution is extremely complex. The light passing through this layer will be deflected, and there will be imaging blur and energy dispersion which seriously affect the accuracy of imaging guidance. It is difficult to reduce this effect by optical correction. This paper attempted to reduce or even eliminate the effect of supersonic boundary layer transition on optical transmission performance by delaying boundary layer transition. Taking the boundary layer flow field around the optical window of the supersonic rotary vehicle as the research object, the study carried out numerical simulation on the variation law of the aero-optical effect of the boundary layer by using the flow control method of adding perturbation plates. The results show that with the increase of the angle of attack, the distribution of optical path difference gradually changes from the symmetrical distribution along the symmetry plane to the change along the flow direction, and gradually flattens. After the turbulence control is applied, the transition position of the boundary layer above the optical window moves backward, and the flow field above the window gradually changes from the transition area to the laminar flow area, which has a significant effect on suppressing the aero-optical effect.