Trajectory Planning for Reentry Maneuverable Ballistic Missiles

摘要

A trajectory planning scheme is proposed to satisfy the requirements of maneuver and terminal guidance constraints in the reentry flight for ballistic missiles. The reentry interface circle with the target point as its center is determined according to the range of the reentry phase. Then, a reference reentry point on the reentry interface circle is obtained as the terminal for the boost and unpowered trajectory planning, and the Newton iteration algorithm is employed to design the corresponding flight program. The reentry trajectory is divided into the pull-up, transition, horizontal flight and reentry phases. The optimal control and feedback control methods are used to deduce the reentry guidance law for each phase according to their trajectory characteristics. Simulations demonstrate that the generated trajectories can satisfy the requirements of maneuver, terminal guidance constraints and terminal precision.