Design of terminal guidance law of near space interceptor based on adaptive sliding mode variable structure control

The rapid development of hypersonic vehicles in near space poses a great challenge to the existing air defense system. In order to effectively intercept near space hypersonic vehicles, the interception terminal guidance method of the near space hypersonic vehicle is mainly studied. The traditional guidance law is affected by the relevant parameter settings, the problem of relatively large missed target often occurs in the case of target maneuvering. By using the adaptive sliding mode variable structure guidance law, the interceptor can automatically adjust the guidance parameters, and adaptively track the target aircraft. Meanwhile, the Lyapunov theorem proves the stability of the guidance law. The simulation results show that the interceptor acceleration instruction and line-of-sight angular rate are kept within the controllable range, which verifies the effectiveness of the method and lays a reliable theoretical foundation for engineering applications.