DocumentCode
486900
Title
Aircraft Guidance for Formation Flying based on Optimal Control Theory
Author
Fu, S.J.
Author_Institution
Flight Controls Research, Boeing Military Airplane Company, P.O. Box 7730, Wichita, Kansas 67277-7730
fYear
1987
fDate
10-12 June 1987
Firstpage
393
Lastpage
394
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;
fLanguage
English
Publisher
ieee
Conference_Titel
American Control Conference, 1987
Conference_Location
Minneapolis, MN, USA
Type
conf
Filename
4789349
Link To Document