Abstract
A key research subject in the area of unmanned aerial vehicles (UAVs) is how to make them autonomous. Towards this goal, the most vital step is stabilizing the attitude of the vehicles. This paper presents the design of an autonomous control system for a hybrid UAV to enable it to carry out a stable hovering mission under external wind disturbances. The hovering capability of the hybrid UAV under windy conditions is analysed with computational fluid dynamics (CFD) and a control law is designed to stabilize the craft in the hovering position. The proposed hovering controller is verified with simulations and experiments. Finally, the flight control system is installed in a small prototype and a full transition flight test, including vertical take-off, transition from vertical flight to cruise, cruise, transition cruise to vertical mode and hover landing, is successfully accomplished.
Highlights
Today, unmanned aircraft systems are able to operate in a highly mechanized manner and perform intelligent navigation both indoors and out, even under conditions of weather disturbances
Design of aerial vehicles has long sought to develop vertical take-off and landing (VTOL) aircraft that are capable of performing an extended operational flight
The hovering capability of this hybrid unmanned aerial vehicles (UAVs) under windy conditions is analysed with computational fluid dynamics and a control law is de‐ signed to stabilize the aircraft in the hovering position
Summary
Today, unmanned aircraft systems are able to operate in a highly mechanized manner and perform intelligent navigation both indoors and out, even under conditions of weather disturbances. Design of aerial vehicles has long sought to develop vertical take-off and landing (VTOL) aircraft that are capable of performing an extended operational flight. Such aircraft need to hover at a particular position at a higher altitude for longer than is currently possible. The design and prototyping of a flight control system capable of vertical take-off and landing (VTOL) like a helicopter and longduration horizontal flight like an airplane is implemented This UAV is configured with the wing surface perpendic‐ ular to the ground during VTOL, with four rotors mounted on the wing, so that the wing and the rotors tilt simultane‐ ously during transition from VTOL to cruise mode.
Sign-in/Register to view highlights & summary Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
