Control of a Hybrid Helicopter with Wings

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This work investigates the design parameters and consequences in the control of a helicopter rotor combined with a pair of fixed wings. This hybrid vehicle has a light and aerodynamically efficient rotor that can achieve large pitch angles to allow forward flight. Because of the light stiff rotor and heavy wings, the hybrid vehicle exhibits couplings between the roll and pitch axes during hover flight. The rotor-wing interaction depends on a lot of parameters. In this paper, we utilize a simplified theoretic model and simulations in order to gain insight in the effect of
these parameters on the vehicle dynamics. Finally, a controller is designed that compensates undesired coupling between pitch and roll.
Original languageEnglish
Title of host publicationInternational Micro Air Vechicle Competition and Conference 2016
EditorsZ. Peng, F. Lin
Place of PublicationBeijing, PR of China
Number of pages8
Publication statusPublished - 17 Oct 2016
EventInternational Micro Air Vechicle Competition and Conference 2016 - Beijing, China
Duration: 17 Oct 201621 Oct 2016


ConferenceInternational Micro Air Vechicle Competition and Conference 2016
Abbreviated titleIMAV2016
Internet address


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