基于扩张状态观测器的反预警滑模制导律

Aiming at the special roles of the early warning airplane, the concept of striking the early warning airplanes by using the height and speed advantages of near space hypersonic flight vehicles is proposed, and the anti-early-warning guidance law is designed. For the maneuverings of the early warning airplane, they are regarded as external disturbances, and expanded into new states by using the extended state observer. This could make the system have real-time observations and dynamic compensations for the disturbances, which effectively solves the problem of the large overloads at the end of the interception. At the same time, the impact angle is constrained when the targets are attacked, and then the sliding mode guidance law with the impact angle constraint is designed. Compared with the traditional trajectory shaping guidance law, the results of the proposed guidance law show the superiorities of the lower overloads and line-of-sight angular velocities during the flight.