A Linear Quadratic Integral Design Approach for the Automatic Control System of a Launch Vehicle

Abstract

This paper presents a design approach for the automatic flight control system of a launch vehicle using a linear quadratic integral technique together with a fixed gain Kalman filter. Its purpose is to analyse the stability and tracking robustness performances of the control system designed via this approach when atmospheric disturbances, modeling uncertainties and structural flexible modes of the launcher are taken into account.

Research on automatic flight control system flight mode operation logic

“…The auto-flight software flight mode operation control function requires a man-machine operation function to receive manual input signals, and FMS input signals, make complex logical judgments according to the current state of the aircraft, and finally, form a flight mode operation control request sent to the control law and feedback the mode operation request to the pilot through FMCP windows, FMCP indicators, and PFD displays. A good flight mode operation control logic design needs to meet the needs to not misunderstand pilots, ensure the safety and availability of auto-flight system functions, and reduce the pilot's work burden at critical moments, so it is necessary to study the automatic flight mode operation control logic [1][2][3]11,12] .…”