Garrett, Frederick Earl2014-03-142014-03-141988-09-15etd-04122010-083818http://hdl.handle.net/10919/42053The primary purpose of this study is to develop a nonlinear feedback control law for the F / A-I8 fighter aircraft that performs a fast half-loop maneuver. This feedback law is developed using a singular perturbation approach. A secondary purpose of this study is to establish a baseline for time optimal half-loop maneuvers. The singular perturbation approach makes it possible to develop a state feedback control law which rotates the velocity vector through one hundred and eighty degrees at a maximum equilibrium pitch rate with a nearly constant angle of attack. The response of the aircraft to the control law is compared to simulations of half-loop maneuvers generated at NASA Langley Research Center.xix, 223 leavesBTDapplication/pdfIn CopyrightLD5655.V855 1988.G377Airplanes, MilitarySingular perturbations (Mathematics)Thesishttp://scholar.lib.vt.edu/theses/available/etd-04122010-083818/