MISSILE AUTOPILOT CONTROLLED BY AERODYNAMIC LIFT AND DIVERT THRUSTERS VIA SECOND-ORDER SLIDING MODE

摘要

A new approach to the design of a kinetic-kill longitudinal autopilot steering the missile trajectory by the combination of aerodynamic lift and divert-thrusters and with its attitude oriented by attitude-thrusters is presented. The pitch plane autopilot design is based on high order sliding mode control. A robust high accuracy tracking of the missile normal acceleration guidance command is achieved in presence of considerable model uncertainties created by the interactions between the airflow and the thruster’s jets. Results of the computer simulation demonstrate excellent robust high accuracy tracking performance of the proposed design.