Sliding mode based attitude and acceleration controller for a velocity-varying skid-to-turn missile

Abstract

Sliding mode based roll-pitch-yaw integrated attitude and acceleration controller for a fin-controlled skidto-turn(STT) missile is proposed. In terms of aerodynamics, the missile model has severe nonlinearities and coupling effect between input channels and roll-pitch-yaw angles that make the controller design challenging. Moreover, the controller should be designed for the entire flight envelope consisting of boostphase and gliding-phase where rapid velocity variation exists, and therefore parametric robustness with respect to rapid velocity change is strongly required. The attitude autopilot controls the Euler angles of the missile, and is configured as a single-loop. On the other hand, the acceleration autopilot, which is of two-loop structure, is used for the control of STT maneuver. The proposed autopilots use multiple sliding surfaces to generate control inputs for multiple channels simultaneously. Numerical simulation is performed to verify the performance of the proposed controllers.

Integrated Pitch-Yaw Acceleration Autopilot Design for Varying-Velocity Man Portable Missile

“…The most significant variation of missile parameters is the missile velocity which changes rapidly as a result of missile subjection to sudden acceleration during boosting phase and deceleration in gliding phase due to aerodynamic drag [2]. One of the important air defense systems is the man-portable missile system in which the missile should be launched in low-speed and that results in a dramatic parameters' variation.…”

“…These works show a good performance whereas considering the missile velocity constant. In [2] a sliding mode based roll-pitch-yaw integrated attitude and acceleration autopilot for a time-varying velocity STT missile was proposed. It showed a good performance but it considered the velocity variation as a function of time.…”