Design of robust autopilot control system for missile withmovable nozzle thrust vector controlling

A new robust autopilot control system based on parameter space method and the quantitative feedback theory (QFT) was proposed on account of aerodynamic uncertainties and the control error of movable nozzle existing in missile with movable nozzle thrust vector controlling. Firstly, a linear mathematic model for missile with movable nozzle thrust vector control was established. Secondly, by taking different combination of bias into consideration, it can be considered as a multi-mode system. A loop of pseudo-angle of attack was designed basing on parameter space method. Lastly, a loop of normal acceleration control based on QFT was designed, by considering the loop of pseudo-angle of attack as generalized controlled object. Simulation results show that the autopilot has strong robust stability and good robust performance with aerodynamic uncertainties and the control error of movable nozzle.