Two-side optimal problem of pursuit-evasion conflicts is studied in this paper, and a new missile guidance law for air defense missile intercepting maneuver target is developed. The guidance law could be called as Reduced Sensitivity Guidance Law (RSGL), which is based on the differential game theory and the capacity of target maneuver. The mathematical model of RSGL is solved by riccati equation method. According to the target acceleration estimation values processed by kalman filter method, the missile's terminal guidance of RSGL parameters can be modified to improve the guidance performance, which with low sensitivity to time-to-go estimation error. Compared to the simulation results under the same situation, RSGL has higher performance than the augmented proportional navigation (APN) and the minimum effort guidance law (MEL) with less miss distance and lower acceleration of pursuit missile.
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