An unmanned aerial vehicle
An unmanned aerial vehicle
The present invention provides an unmanned aerial vehicle (UAV) comprising a flight system 4 for producing thrust to manoeuvre the UAV. The flight system comprises a flight rotor 42, driven by an electric motor 44, the rotor defining a plane passing through the flight rotor and a thrust direction generally perpendicular to the plane. The unmanned aerial vehicle further comprises a cargo area for coupling to or receiving a load and a load system 6 for providing thrust additional to the thrust provided by the flight system to lift a load attached to a connection point 8. The load system comprises a gas turbine propulsion system 62 and a controller 10 configured to control the fight system and load system. The controller is subdivided into a flight system controller and a load system controller which are independent of one another. There may be a plurality of gas turbine propulsion systems arranged with an N-fold rotational symmetry in the plane of the flight rotors around a centre of the UAV, where N is the number of gas turbine engine propulsors.
GB2578083
Intellectual Property Office
22 April 2020
Prior, Stephen
9c753e49-092a-4dc5-b4cd-6d5ff77e9ced
Grubisic, Angelo
94e5f6ea-9b65-4c81-bfa1-f0e29e8bbaf4
Prior, Stephen and Grubisic, Angelo
(Inventors)
(2020)
An unmanned aerial vehicle.
GB2578083.
Abstract
The present invention provides an unmanned aerial vehicle (UAV) comprising a flight system 4 for producing thrust to manoeuvre the UAV. The flight system comprises a flight rotor 42, driven by an electric motor 44, the rotor defining a plane passing through the flight rotor and a thrust direction generally perpendicular to the plane. The unmanned aerial vehicle further comprises a cargo area for coupling to or receiving a load and a load system 6 for providing thrust additional to the thrust provided by the flight system to lift a load attached to a connection point 8. The load system comprises a gas turbine propulsion system 62 and a controller 10 configured to control the fight system and load system. The controller is subdivided into a flight system controller and a load system controller which are independent of one another. There may be a plurality of gas turbine propulsion systems arranged with an N-fold rotational symmetry in the plane of the flight rotors around a centre of the UAV, where N is the number of gas turbine engine propulsors.
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More information
Published date: 22 April 2020
Identifiers
Local EPrints ID: 487168
URI: http://eprints.soton.ac.uk/id/eprint/487168
PURE UUID: 34dbf0d9-6664-45a0-8017-34370bcca01a
Catalogue record
Date deposited: 14 Feb 2024 17:43
Last modified: 18 Mar 2024 03:24
Export record
Contributors
Inventor:
Angelo Grubisic
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