Adaptive Sliding Mode Guidance Law Considering Input Saturation and Autopilot Lag
Received Date: July 05, 2019; Published Date: July 11, 2019
In this article, a guidance law is developed using the sliding mode control theory. The law will have a good guidance performance when intercepting a maneuvering target under considering the input saturation and autopilot lag. Regarding the target acceleration as unknown bounded external disturbance, the adaptive control is designed to estimate the upper bound of the disturbance in such a way that it is not required to be known in advance. A sliding mode estimator is also presented to estimate the line-of-sight angle rate which the guidance law is required. According to the Lyapunov theory, the guidance law can be converted to zero is proved. Several simulations include 100 Monte-Carlo are made to valid the effectiveness of proposed guidance law.
Keywords:Guidance law; Adaptive sliding mode; Missile; Input saturation