An optimal terminal guidance law with both interception and impact angle constraint is derived according to simplified missile movement equation and Lagrange method.

Based on analyzing the missile and target motion dynamics, the fuzzy rules are established according to design expert experience of optimal guidance law and characteristics of measurement noise disturbances.

By using the steepest ascent method,the optimal guidance law is gained to solve this kind of problem: the final time is undefined and there are constrains.

An optimal sliding-mode guidance law which is robust to parameter perturbations and external disturbance is proposed for the space interception problem of maneuvering target,and an intelligent method of the guidance law is studied.

The Optimum Intermediate Guidance Law of Long Distance Air-to-Air Missile;