Study of the closed-loop guidance law for boost phase with reentry constraints of maneuvering reentry vehicles

To provide the best conditions for a maneuvering entry vehicle which faces to the severe and difficult conditions for its control system in reentry phase,the closed-loop guidance law for boost phase with reentry constraints is investigated in this paper.Baced on the properties of elliptical trajectory,the reentry conditions of the vehicles,spherical geometry,and the fixed-point theorem,an algorithm for the ideal trajectory is proposed.In order to enter into the ideal trajectory with minimal energy,the nonlinear thrust vector control and the prediction guidance are adopted in the missile guidance control system.The simulation shows that the proposed design method provides a good flight performance for vehicles.