Optimal guidance law of air to surface missile with terminal impact angle constraint

Abstract

With the change of arms combat, in recent years, the guided method of having the terminal angle constraint get an increasing attention. In considering the requirements conditions of aircraft hit the target having landing speed and speed dip, based the idea of the zero reentry vehicle and goals vision angular rate, designed for attacking ground fixed targets optimal reentry guidance law, That is to improve the accuracy of the missile, make the missile hit the target quickly, and put stringent requirements for the terminal angle constraint. The idea of using the optimal control theory, when the aircraft hit the target to meet the conditions of the terminal angle constraint, and ensure reentry vehicle maneuvering speed to loss minimum.