Abstract A sliding mode terminal guidance law for KKV based on variable structure control theory is designed to intercept the high maneuver TBM target. The model of TBM maneuver target is established and a system model is also established according to the relative motion equations of the missile and the target. The terminal guidance law of the logitudinal plane is deduced using exponential reaching law. The simulation results show that the adaptive sliding mode guidance law has the advantages of fast response, strong robustness, small miss distance, and powerful interception result when intercepting maneuver TBM target..
Received: 22 November 2017
Published: 10 April 2018
2018, Vol. 1 
