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• W2186493889 abstract "This paper presents a robust controller design for the planar vertical takeoff and landing aircraft dynamics. The controller design is based on a linearized PVTOL dynamics in terms of state and control quantities deviated from their equilibrium. The controller state-feedback gain is constructed by solving LMI conditions to maximize convergence rate while subject to the magnitude constraints on control efforts and regulated outputs. The robustness against the parasitic coupling between rolling moment and lateral force is addressed during the phase of controller design. The design results are verified and demonstrated through time-response simulations for controllers constructed according to specified quantities of the parasitic coupling. The vertical/short takeoff and landing (V/STOL) aircraft has the capability of high mobility and maneuverability, and is especially suitable to operate in a poor runway condition such as the deck of a military vessel and an informal temporary runway. The types of V/STOL aircraft, such as the AV-8B Harrier produced by McDonnell Douglas (1) and the F-35 Joint Strike Fighter (JSF) produced by Lockheed Martin allied with Boeing (2), are among the main stream applications at present. The Harrier is powered by one Rolls Royce Pegasus F402-RR-408 turbo-fan engine with exhaust nozzles equipped in each side of the fuselage to provide the gross thrust for the aircraft. The nozzles are capable of rotating together from the aft position forward approximately 100 degrees. This change in the direction of thrust allows the aircraft to operate in the two modes of wing-borne forward flight and jet-borne hovering as well as the transition between them. In order to perform motion in lateral direction, the aircraft is equipped with reaction control valves in the nose, tails, and wingtips. By using the high pressure flow from compressor of engine, these valves produce moments around the center of mass to change attitude. On the other hand, The JSF is equipped by a modified Pratt & Whitney F119-PW-100 engine configured with shaft-driven lift fan, roll ducts and a three-bearing swivel main engine nozzle. The lift fan in the front part of frame and the main engine nozzle when swiveled vertically provide the lift force for aircraft maneuvering in a low air speed. The roll ducts in the both sides of wingtips are used for providing necessary moment for attitude handling. In this paper, the hovering operation of the V/STOL aircraft is considered, in which the upward thrust from the main engine nozzles is manipulated by throttle for aircraft vertical motion. For attitude changing of the Harrier or JSF aircrafts, if the high pressure air from the reaction control valves or ducts induces an unexpected force component in the lateral direction, the system dynamics will exhibit non-minimum phase characteristics in case the force moves the aircraft into a lateral direction opposite to the attitude intention. Then this time delay will cause non-minimum" @default.
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• W2186493889 date "2008-01-01" @default.
• W2186493889 modified "2023-09-27" @default.
• W2186493889 title "The Maximizing Convergence Rate Control for V/STOL Aircraft with Input Saturation" @default.
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