Abstract:

The guidance law with impact angle constraint can enable missiles to hit the target in a designated direction, and the guidance law with impact time constraint can enable missiles to hit the target at a designated time. Compared with the traditional guidance approach (e.g. the proportional navigation guidance law), these guidance laws all result in additional maneuvers, which may cause the target to move out of the missile seeker’s field-of-view (even for a stationary target). To solve this problem, by utilizing the nonlinearity of the cosine function, proportional navigation guidance law with a biased item composed of the seeker field-of-view limit and impact angle constraint is constructed firstly, and the time-to-go estimation of this guidance law is derived. Then, by adding the feedback of the time-to-go error, a guidance law with seeker field-of-view limit and both impact angle and impact time constraints is proposed. Simulation results show the validity of the proposed approach.