An Improved Integral Proportional Guidance Law Based on Optimization and Variable Proportional Factors

Abstract

For image guided missile, in order to avoid frame collision, the maximum needed frame-angle of the seeker should not exceed the maximum available frame-angle in flight. Subjected to diameter and volume of the seeker, the required frame-angle needs to be reduced. By combination signal of frame-angle, three different improved guidance laws are discussed. By using of special developed optimization scheme, the integral proportional guidance is selected finally for its best effect. For purpose of reducing required overload of the missile, further improvement of the guidance law is generated by using variable proportional factors. The simulation results show that after using of the final improved guidance law, the maximum required frame-angle is reduced by 1.5, the required overload of the missile at the beginning of tracking is reduced from 5.8 to 2.4. According to the results, the effectiveness of the improved guidance law is verified.

Three-dimensional optimal sliding mode guidance with impact angle constraint

“…In some cases, in order to obtain a better combat effectiveness the terminal impact angle of guidance law should have a constraint of specific range in terms of the target characteristics [1][2]. Furthermore, due to the poor guidance performance of classic proportion navigation guidance law (PNGL) for maneuvering target, especially in the closing segment of predicted impact point (PIP), the PNGL can produce a large miss distance.…”