NDLI: Transition flight control for Canard Rotor/Wing rotorcraft

Content Provider	IEEE Xplore Digital Library
Author	Tengfei Guo Honglun Wang Wendong Gai
Copyright Year	2011
Description	Author affiliation: Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, China (Tengfei Guo; Honglun Wang; Wendong Gai)
Abstract	Canard Rotor/Wing (CRW) Unmanned Aerial Vehicle (UAV) combines advantages of a helicopter for taking-off and hover, and a fixed-wing aircraft for high speed cruise. A key technology involved is control system design for transition flight. This paper describes flight characteristic of CRW UAV with achieving transition flight from helicopter mode to fixed-wing mode. Dynamic model is built and analyzed. Control strategy is proposed for three flight modes, including helicopter mode, conversion mode and fixed-wing mode. Then, flight control law is designed by modified nonlinear dynamic inversion technique. In addition, we succeed to allocate redundant control inputs for the CRW with generalized multiple control effectors. Finally, simulation has been done with MATLAB /SIMULINK toolbox. The CRW UAV accelerates from helicopter mode to fixed-wing mode. Meanwhile, control loops are closed on airspeed and altitude. Simulation results show that the designed controller could meet the requirements for transition flight control.
Starting Page	875
Ending Page	880
File Size	341349
Page Count	6
File Format	PDF
ISBN	9781457705359
e-ISBN	9781457705366
DOI	10.1109/AIMSEC.2011.6010405
Language	English
Publisher	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Publisher Date	2011-08-08
Publisher Place	China
Access Restriction	Subscribed
Rights Holder	Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subject Keyword	Transition flight control Atmospheric modeling Helicopters Rotors Canard Rotor/Wing Aerodynamics Acceleration Mathematical model Modeling Dynamic inversion Aerospace control
Content Type	Text
Resource Type	Article

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