NMPC-Based Autopilot Design for Air-to-Air Missiles

Abstract

In this paper, an overload autopilot based on generalized extended state observer, predictive function control and improved barrier interior-point method is designed to solve the problems of model nonlinearity, time variability and control constraints in attitude control of air-to-air missile. Firstly, the dynamic model of missile is established. Then, the generalized extended state observer is used to observe and compensate lumped disturbance in the system, and the controller is designed by predictive function control. The optimization problem with control constraints is designed and transformed into a quadratic programming problem, which is quickly solved by an improved barrier inte-rior-point method, the control performance can be guaranteed and the real-time performance can be improved. Finally, the effectiveness and feasibility of the scheme are verified by simulation.

Keywords

• |autopilot|predictive function control|generalized extended state observer|barrier interior-point method|air-to-air missile