为实现探测器组件固联于弹体且导引头结构小型化，采用了由特殊棱镜与反射镜组成的光学滑环式光机结构设计。光学系统的前镜组、反射镜嵌入内框架，实现 ±90.扫描运动；内框架、特殊棱镜组件嵌入外框架，实现 360.扫描运动，进而使光学系统具有前半球的跟踪视场。设计结果表明光学系统在-70℃～＋90℃温度范围内调制传递函数接近衍射极限，成像清晰，满足光、机、热一体化设计要求。实验结果显示，研制的光学系统其焦距 60 mm，视场大小为 3.，在 20 lp/mm处，轴上视场的调制传递函数（MTF）高于 0.7。系统实现了探测器组件固联于弹体及光机系统小型化的目的。

In order to fix the detector module to the structure and miniaturize the seeker, a deflected opto-mechanical system was presented. The seeker has 360. rolling angle and ±90. pitching angle. Firstly, the anterior lens and the mirror are embedded into the inner frame; secondly, the pitching frame and special prism were embedded into the outer frame, then the combination of rolling and pitching realizes the front hemisphere searching field. The pitching mirror and rolling special prism could transfer target energy to the posterior lens and the missile body，and the fixed detector module will detect it. The analysis shows that the modulation transfer function of the system is close to the diffraction limit when working temperature changing from -70℃ to 90℃. The optical system fulfills the integrated design requirements of optical, structure and thermalization.