TY - GEN
T1 - Robust LPV H∞ gain-scheduled hover-to-cruise conversion for a tilt-wing rotorcraft in the presence of CG variations
AU - Dickeson, Jeffrey J.
AU - Miles, David
AU - Cifdaloz, Oguzhan
AU - Wells, Valana
AU - Rodriguez, Armando
PY - 2007
Y1 - 2007
N2 - This paper describes the development and analysis of gain-scheduled, multi-variable H∞ control law for the conversion of a linear parameter varying (LPV) model of a High-Speed Autonomous Rotorcraft Vehicle (HARVee), an experimental tilt-wing aircraft. Tilt-wing aircraft combine the high-speed cruise capabilities of a conventional airplane with the vertical takeoff and station keeping abilities of a helicopter by rotating their wings at the fuselage. Changing between cruise and hover flight modes in mid-air is referred to as the conversion process, or simply conversion. A nonlinear aerodynamic model was previously developed that captures the unique dynamics of the tilt-wing aircraft. An H∞ design methodology was used to develop linear controllers along various operating points of a conversion trajectory. The development of these control systems was governed not only by performance specifications at each particular operating point, but also by the unique requirements of a gain-scheduled conversion control system. The performance of the resulting conversion closed-loop systems is analyzed in the frequency and time domains. Performance robustness with respect to variation in the location of the center of gravity (eg) has been studied.
AB - This paper describes the development and analysis of gain-scheduled, multi-variable H∞ control law for the conversion of a linear parameter varying (LPV) model of a High-Speed Autonomous Rotorcraft Vehicle (HARVee), an experimental tilt-wing aircraft. Tilt-wing aircraft combine the high-speed cruise capabilities of a conventional airplane with the vertical takeoff and station keeping abilities of a helicopter by rotating their wings at the fuselage. Changing between cruise and hover flight modes in mid-air is referred to as the conversion process, or simply conversion. A nonlinear aerodynamic model was previously developed that captures the unique dynamics of the tilt-wing aircraft. An H∞ design methodology was used to develop linear controllers along various operating points of a conversion trajectory. The development of these control systems was governed not only by performance specifications at each particular operating point, but also by the unique requirements of a gain-scheduled conversion control system. The performance of the resulting conversion closed-loop systems is analyzed in the frequency and time domains. Performance robustness with respect to variation in the location of the center of gravity (eg) has been studied.
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U2 - 10.1109/CDC.2007.4435028
DO - 10.1109/CDC.2007.4435028
M3 - Conference contribution
AN - SCOPUS:62749113472
SN - 1424414989
SN - 9781424414987
T3 - Proceedings of the IEEE Conference on Decision and Control
SP - 2773
EP - 2778
BT - Proceedings of the 46th IEEE Conference on Decision and Control 2007, CDC
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 46th IEEE Conference on Decision and Control 2007, CDC
Y2 - 12 December 2007 through 14 December 2007
ER -