Title :
Aircraft Guidance for Formation Flying based on Optimal Control Theory
Author_Institution :
Flight Controls Research, Boeing Military Airplane Company, P.O. Box 7730, Wichita, Kansas 67277-7730
Abstract :
Application of Linear Quadratic Regulator (LQR) theory to aircraft guidance and control for formation flying is discussed in this paper. Based on a second order mathematical model, the guidance law provides the reference acceleration command to the flight and propulsion control system of the wingman aircraft.
Keywords :
Acceleration; Aerospace control; Aircraft propulsion; Mathematical model; Military aircraft; Optimal control; Radar tracking; Regulators; Turning; Velocity control;
Conference_Titel :
American Control Conference, 1987
Conference_Location :
Minneapolis, MN, USA
