In order to solve the contradiction between terminal angular control and precision control, an optimal guidance law is proposed using flight mechanics and optimal control theory with miss distance and minimum energy as performance index.

The results of numeric simulation indicate that optimal guidance law has the smaller controlled energy and the shorter miss distance compared with classical proportional navigation.

Simulation results show that compared with optimal guidance law, the guidance precision of adaptive proportional guidance law is less affected by initial velocity inclination angle and guidance order delay and order updating frequency, but is more affected by signal measurement with jam.

Based on modeling of semi-active radar guided surface-to-air missile,a conclusion was given on guided precision of proportional navigation,extended proportional navigation and modern optimal guidance law at different parameters based on both theory and simulation analysis.

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;

A suboptimal guidance law for satellite guided bombs using a genetic algorithm;

A suboptimal guidance law is designed based on single neuron to command satellite guided bombs to move with a small fall angle.