A Sliding Mode Guidance Law with ESO for Near Space Interceptor

Abstract

Considering the autopilot dynamic characteristics of the near space interceptor and the target maneuver, a novel sliding mode guidance law is proposed based on the extended state observer (ESO). Firstly, the ESO is constructed to estimate the target acceleration of the disturbances for the guidance system, and the disturbance estimated values are employed as the feed-forward compensation term to obtain the robustness of the target maneuver and system disturbances. Then, a novel sliding mode guidance law based on the ESO is given. Finally, simulation results for the near space interceptor guidance system show that the proposed guidance law can not only overcome the effect of the autopilot dynamic delay and target maneuver, but also ensure the accurate guidance results.