Abstract:

A new cooperative guidance to control impact time and impact angle for multimissiles is proposed. The guidance consists of two stages: the first stage is to control the time accurately and to control the angle approximately, and the second stage is to control the angle accurately. In the first stage, the impact time control problem is transformed into a range tracking problem, and the equations of the relationship between missile and target are transformed into a secondorder nonlinear model; then the timetogo of each missile is estimated, based on which the desired impact time is determined; finally, the timescale separation method is used to design the desired low speed subsystem and fast speed subsystem. Nonlinear dynamic inversion controllers are designed for the two subsystems respectively, and in the above design an approximate control to the impact angle is considered. In the second phase, the variable structure guidance law is applied to control the impact angle accurately. In addition, a new approach to determine the impact time is also proposed that considers the impact angle constraints. Simulation results validate the proposed approach.

Key words: automatic control technology, impact time control, impact angle control, time scale separation, dynamic inversion, variable structure