随着科技的发展, 高速度飞行器对成像质量的要求越来越高。研究了含共形整流罩系统在超音速飞行时由于摩擦生热对其产生的光机性能影响, 设计了应用长径比为1的共形整流罩的共形光学系统, 系统采用楔形镜进行视场扫描, 瞬时视场2?棕=4°, 扫描视场2?棕=60°, 完成了速度为3Ma、攻角为0°共形整流罩空气动力学仿真实验, 得到了共形整流罩在超音速飞行情况下的表面温度分布值, 通过流固耦合, 计算出整流罩在高速飞行时不同时间段的面型变化量。通过拟合, 将热形变量以Zernike系数的形式施加到共形光学系统中, 观察其对成像质量的影响。结果表明: 共形整流罩在飞行中所引入的动态像差会对光学系统的成像质量产生影响。为保证系统精度, 文中通过采用空间光调制器(Spatial Light Modulator, SLM)对不同时刻的像差进行校正, 校正后系统成像质量接近衍射极限, 实现了对共形光学系统在高速飞行下所产生的动态热像差进行校正, 对高精度飞行器有着重要科学意义。

With the development of science and technology, there are more and more high requirements of imaging quality for high speed aircraft. The effect of friction heating on imaging quality of supersonic speed system with a conformal dome was studied. An conformal optical system with a conformal dome which had a length-to-diameter ratio of 1 was designed. The system had two wedge mirrors for field scanning, which provided a instantaneous FOV of 4° and a scanning FOV of 60°. A conformal fairing aerodynamic simulation experiment with the speed of Mach 3 and attack angle of 0° was finished. The surface temperature distribution of conformal dome in supersonic speed was obtained. Through the fluid-solid interaction, surface variation of different periods was calculated. The thermal surface variation was fitted into Zernike coefficients and applied to conformal optical system. The analysis results showed that the dynamic aberration introduced by high speed flight affected the imaging quality of optical system. In order to guarantee the system precision, a Spatial Light Modulator (SLM) was used to correct the aberration of different periods. After correction, system imaging quality was close to the diffraction limit, which had realized thermal aberration correction of conformal dome in supersonic speed flight. This study has certain significance to the development of high precision aircraft.