EP-4737332-A2 - AN UNMANNED AERIAL VEHICLE

EP4737332A2EP 4737332 A2EP4737332 A2EP 4737332A2EP-4737332-A2

Abstract

The present invention provides an unmanned aerial vehicle comprising: a flight system for producing thrust to manoeuvre the unmanned aerial vehicle. The flight system comprises: one or more flight rotors defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor for driving the one or more flight rotors. The unmanned aerial vehicle further comprises: a cargo area for coupling to or receiving a load; and a load system for providing thrust additional to the thrust provided by the flight system to thereby lift a load coupled to or received in the cargo area and attached to the connection point. The load system comprises: a plurality gas turbine propulsion systems, wherein each gas propulsion system is provided at an angle with respect to the thrust direction of the flight rotors to direct a jet plume from each gas propulsion system away from a load coupled to or received in the cargo area; and a controller configured to control the flight system and load system.

Inventors

PRIOR, Stephen

Assignees

Hybrid Drones Limited

Dates

Publication Date: 20260506
Application Date: 20191206

Claims (15)

An unmanned aerial vehicle comprising: a flight system for producing thrust to manoeuvre the unmanned aerial vehicle comprising: one or more flight rotors defining a plane passing through each flight rotor and a thrust direction generally perpendicular to the plane; and one or more electric motor for driving the one or more flight rotors; a cargo area for coupling to or receiving a load; a load system for providing thrust additional to the thrust provided by the flight system to thereby lift a load coupled to or received in the cargo area and attached to a connection point, the load system comprising: a plurality of gas turbine propulsion systems, wherein each gas propulsion system is provided at an angle with respect to the thrust direction of the flight rotors to direct a jet plume from each gas propulsion system away from a load coupled to or received in the cargo area; and a controller configured to control the flight system and load system.
The unmanned aerial vehicle of claim 1, wherein the plurality of gas turbine propulsion systems are each angled by between 10 and 20 degrees from the thrust direction of the one or more flight rotors.
The unmanned aerial vehicle of claim 2, wherein the plurality of gas turbine systems are angled symmetrically such that a net thrust vector of the plurality of gas turbine systems is substantially perpendicular to the plane.
The unmanned aerial vehicle of any preceding claim, wherein the one or more flight rotors comprises two or more flight rotors, arranged at an outer periphery of the unmanned aerial vehicle.
The unmanned aerial vehicle of claim 4, wherein each gas turbine propulsion system is provided within a radius defined by the flight rotors.
The unmanned aerial vehicle of claim 5, wherein the radius is defined by an innermost point of each flight rotor.
The unmanned aerial vehicle of any of claims 4 to 6, wherein the two or more flight rotors comprises four or eight flight rotors.
The unmanned aerial vehicle of any preceding claim, wherein the gas turbine propulsion systems are arranged with N-fold rotational symmetry in the plane of the flight rotors around a centre of the unmanned aerial vehicle, wherein N is the number of gas turbine propulsion systems.
The unmanned aerial vehicle of any preceding claim, wherein each gas turbine propulsion system comprises a turbojet; turbofan; or turboprop.
The unmanned aerial vehicle of any preceding claim, further comprising: a load sensor in communication with the controller, the load sensor being configured to provide a signal indicative of the weight applied by a load coupled to or received in the cargo area and attached to the connection point; wherein the controller is configured to control the load system in response to the signal indicative of the weight applied to the connection point.
The unmanned aerial vehicle of claim 10, wherein the controller is configured to control the load system in a closed-loop control to balance the force provided by the load system and the weight applied to the connection point.
The unmanned aerial vehicle of any preceding claim, wherein the vehicle has a first mode of operation in which the flight system is operated to take-off and/or land the unmanned aerial vehicle and in which the load system in inactive.
The unmanned aerial vehicle of claim 12, wherein the vehicle has a second mode of operation in which the load system is activated to provide thrust equal to the weight of a load, and in which the flight system is used to generate thrust to manoeuver the unmanned aerial vehicle and load.
The unmanned aerial vehicle of any preceding claim, wherein the cargo area is provided at a centre of the unmanned aerial vehicle.
The unmanned aerial vehicle of any preceding claim, wherein the cargo area comprises the connection point and a tether, optionally wherein the tether is releasably attached to the unmanned aerial vehicle and/or to the load, optionally wherein the tether is remotely releasable, preferably via an electro-magnet.

Description

The present invention relates to an unmanned aerial vehicle which is designed to lift and carry heavy loads. In particular, loads of up to and exceeding 100 kg are anticipated. The vehicle may be able to carry such loads distances up to 10 km. Unmanned aerial vehicles are generally well known, and include drones, rotorcopters, quadcopters, octocopters and the like. Such vehicles are typically provided with an electric motor which drives one or more rotors. The electric motor allows good mobility and manoeuvrability. However, it is difficult to generate a large lift thrust with these conventional vehicles. In particular, as the payload ratio grows there is a diminishing return in practical range as the required source of electrical power must vastly increase in size. Typically lithium ion batteries are used as a source of electrical power for the electric motors. Such lithium ion batteries can store energy at approximately 2.5 MJ/kg. Therefore, the electrically driven rotors result in a relatively poor endurance and flight range for loads above a minimal weight. This limitation is not an issue for many applications where there is little or no load to be lifted. Given the ease of use of drones in remote locations and inaccessible terrain there is a need for drones which are able to assist in heavy lifting. Such assistance may be useful in construction, military deployment or extraction and operations, rescue operations, commercial delivery, or the like. There is therefore a need for an improved drone which can assist with heavy lifting. An unmanned aerial vehicle according to a first embodiment of the present invention is provided according to claim 1. The unmanned aerial vehicle comprises: a flight system for providing thrust to manoeuvre the unmanned aerial vehicle comprising: one or more flight rotors defining a thrust direction and a plane generally perpendicular to the thrust direction; and one or more electric motors for driving the one or more flight rotors. The unmanned aerial vehicle further comprises a cargo area for coupling to or receiving a load; and a load system for providing thrust additional to the thrust provided by the flight system to thereby lift a load attached to the connection point comprising: a first gas turbine propulsion system. The unmanned aerial vehicle further comprises a controller configured to control the flight system and load system. This unmanned aerial vehicle allows the electric flight rotors to be used for the high precision manoeuvrability required for general flight while the gas turbine propulsion system is used to provide lift for lifting a heavy load. This therefore allows the unmanned aerial vehicle to lift a heavy load while maintaining manoeuvrability during flight. The load system may comprise a plurality of gas turbine propulsion systems. A plurality of gas turbine propulsion systems can increase the amount of thrust available to lift the load. The gas turbine propulsion systems may be arranged with N-fold rotational symmetry in the plane of the flight rotors around a centre of the unmanned aerial vehicle, wherein N is the number of gas turbine propulsion systems. The rotational symmetry of the gas turbine propulsion systems allows these systems to balance one another and provide a force simply to aid in the lifting of the load which not affecting the flight of the unmanned aerial vehicle. Each gas propulsion system may be provided at an angle with respect to the thrust direction of the flight rotors. The angle directs the gas propulsion systems to counteract the load and not affect the flight of the vehicle. Additionally, the jet plume does not impinge upon any load being carried. Each gas turbine propulsion system may comprise a ducted fan for producing the additional thrust in the form of its exhaust gas jet. Thrust in the form of exhaust gas jet is a thrust to weight efficient manner of generating additional lift. The gas turbine propulsion system may comprise a turbojet; turbofan; or turboprop. These gas turbine propulsion systems are good methods to generate additional lift for a relatively low weight. The flight system may comprise two or more rotors, arranged at an outer periphery of the unmanned aerial vehicle, preferably the flight system comprises four or eight rotors. Having the rotors arranged around the periphery of the unmanned aerial vehicle allows for enhanced manoeuvrability of the vehicle. Each gas turbine propulsion system may be provided within a radius defined by the rotors. As the gas turbine propulsion systems is provided within the radius defined by the rotors the force it generates can be more easily balanced. An unmanned aerial vehicle according to a second embodiment of the present invention is provided according to claim 9. The unmanned aerial vehicle comprises: a flight system for providing thrust to manoeuvre the unmanned aerial vehicle; a cargo area for coupling to or receiving a load; a load system for providing thrust additio