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Pitch Control by LQR for Fixed Wing Aircraft During Microburst Encounter

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Document pages: 10 pages

Abstract: In this study, a linear mathematical model representing longitudinal flightdynamics of an airplane is developed and responses of the aircraft during amicroburst encounter are investigated. The effects of microburst that areacting on the aircraft are attempted to be suppressed with the elevator controlsurface of the aircraft, which is controlled by Linear Quadratic Regulatormethod. To illustrate the effectiveness of the proposed control method,numerous numbers of simulation studies is performed. As a result of thesimulations, it is observed that effects of microburst on the pitching angleand altitude are significantly attenuated by the proposed control method. Inaddition, it is confirmed that the elevator control surface movement whichprovides the necessary controller input is within the physical capabilities ofthe aircraft.

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