Singular trajectories for time-optimal half-loop maneuvers of a high alpha fighter aircraftConsideration is given to the problem of deriving a time-optimal open-loop control for the half-loop maneuver of a high-alpha aircraft, with initial conditions Mach 0.6 and 15,000 feet. Pontriagin's maximum principle is used to derive candidate optimal solutions. Using the two-point boundary-value algorithm, the flight path angle is maximized for various increasing specified final times until a final time of 13.6 sec yields a 180-deg flight-path angle. As the final time increased from 0.0 to 13.6 sec, the optimization process revealed 13 distinct switching structures of the control law, of which 11 contained singular arcs, and two had double singular arcs.
Document ID
19890065321
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hoffman, Eric (Georgia Inst. of Tech. Atlanta, GA, United States)
Stalford, Harold (Georgia Institute of Technology Atlanta, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 89-3614
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference