Abstract—A design of integrated pitch-yaw acceleration autopilot based on sliding mode control is proposed for roll-stabilized skid-to-turn (STT) varying-velocity man portable missile. This approach is suggested to achieve a good tracking performance in the presence of nonlinear aerodynamics, command dynamics, and missile parameters' variation during the entire flight envelope, including boosting phase, sustaining phase, and gliding phase where fast variation of velocity and parameters exists. Thus, robustness against quick variation of velocity and parameters is exceedingly required. The presented autopilot consists of two-loop structure with an additional proportional gain that switches according to time of the boosting phase, controls STT maneuver. It employs multiple sliding surfaces to generate control signals for pitch-yaw channels simultaneously. The missile model considers the velocity variation, the gravity effect, the missile parameters' variation, and the environmental conditions. Finally, Numerical simulation is established to evaluate performance of the proposed acceleration autopilot.
Index Terms—Acceleration autopilot, flight control system, man portable missile, sliding mode control.
A. Awad and H. P. Wang are with Sino-French International Joint Laboratory of Automatic Control and Signal Processing (LaFCAS), Automation School, Nanjing University of Science and Technology, China (e-mail: ahmed_eyssa@hotmail.com, hp.wang@njust.edu.cn).
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Cite: A. Awad and H. P.Wang, "Integrated Pitch-Yaw Acceleration Autopilot Design for Varying-Velocity Man Portable Missile," International Journal of Modeling and Optimization vol. 6, no. 1, pp. 11-17, 2016.
