飞行器在大气层中超音速飞行时，被气动加热的光学整流罩产生强的红外辐射，降低了红外目标的跟踪识别能力。分析了共形光学系统整流罩热噪声的产生机理，利用红外黑体，对320 K~460 K的整流罩热噪声进行了测试。利用二元非线性回归分析法确定了二次曲面作为噪声修正模型，其曲面拟合的决定系数均值达到0.8683。在整流罩温度从460 K下降至320 K的过程中，对1 K温差的靶条成像，图像信噪比均值为7.2 dB。利用噪声修正模型对图像进行噪声修正后，图像信噪比均值提高至13.7 dB，使红外图像信噪比提高了6.5 dB。该结果为导引头目标识别跟踪系统的设计和光学系统的优化提供了部分依据。

When the optical dome of aerobat is initially subjected to aerodynamic flight conditions, the temperature of front surface rises rapidly. The thermal optical dome produces a sharp increase in background radiance on the focal plane detector, which can mask the target signal and decrease the ability of target tracking. Infrared conformal dome has demonstrated its capabilities as a prominent technique for supersonic aero thermal radiation effect. Aero thermal radiation effect of conformal infrared dome is described. The thermal noises of conformal dome are measured by infrared blackbody when dome temperature decreases from 460 K to 320 K. Quadratic surface as noise correction model decided by dualistic nolinear regression analysis is introduced, and the coefficient of determination of quadratic surface fitting is 0.8683. The mean signal noise ratio of the image is increased to 13.7 dB after noise correction by noise correction model. The signal noise ratio of infrared image increases 6.5 dB after noise correction. The result can meet the precision requirement of target tracking system and provide partial evidence for optics system optimization.