Abstract

An unmanned aerial vehicle is disclosed. The vehicle comprises: a primary altimeter (202) configured to indicate an altitude of the vehicle in flight based on time taken for an electromagnetic signal emitted from the vehicle to return to the vehicle, and a secondary altimeter (204) configured to indicate an altitude of the vehicle in flight based on a measured ambient pressure. The vehicle also comprises a controller (210) configured to obtain one or more altitude signals from the primary altimeter and the secondary altimeter, and, in a first mode, select the altitude of the vehicle based on the signals from the primary altimeter, and in a second mode, select the altitude of the vehicle based on the signals from the secondary altimeter. The controller is configured to switch from the first mode to the second mode in response to a change in the orientation or trajectory of the vehicle.

IPC Classes  ?

• G01C 5/00 - Measuring heightMeasuring distances transverse to line of sightLevelling between separated pointsSurveyors' levels
• G01C 5/06 - Measuring heightMeasuring distances transverse to line of sightLevelling between separated pointsSurveyors' levels by using barometric means
• G01S 13/88 - Radar or analogous systems, specially adapted for specific applications
• G01S 17/933 - Lidar systems, specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft

Abstract

Unmanned Aerial Vehicle and Components of an Unmanned Aerial Vehicle The present disclosure relates to the field of unmanned aerial vehicle technology. An aspect provides an unmanned aerial vehicle comprising: a body; a gas turbine engine disposed at least partially within the body; wings coupled to the body; and, one or more air ducts, each air duct comprising an inlet and an outlet, wherein: the inlet is disposed outside of the body, the inlet configured to receive air as the unmanned aerial vehicle moves due to operation of the gas turbine engine; the outlet disposed at an inlet of the gas turbine engine, the outlet configured to discharge air into the inlet of the gas turbine engine.

IPC Classes  ?

• B64D 27/14 - Aircraft characterised by the type or position of power plants of gas-turbine type within, or attached to, fuselages
• B64U 50/12 - Propulsion using turbine engines, e.g. turbojets or turbofans
• B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes

Abstract

A dolly vehicle for detachably coupling to an unmanned aerial vehicle, UAV, for launching the UAV, is disclosed herein. The dolly vehicle comprises: a support frame having a front end and a rear end; a cradle coupled to the supporting frame at a position between the front end and the rear end, the cradle configured to receive and hold the UAV; at least two drivable structures coupled to the support frame; a driving means configured to drive the at least two drivable structures; and a steerable structure coupled to the supporting frame.

IPC Classes  ?

• B64F 1/10 - Ground or aircraft-carrier-deck installations for launching aircraft using self-propelled vehicles
• B64U 70/93 - Portable platforms for use on a land or nautical vehicle

Abstract

A fuel tank for an unmanned aerial vehicle is disclosed herein. The fuel tank comprises a primary bladder configured to be housed inside the fuselage of the unmanned aerial vehicle. The primary bladder comprises a series of baffles for reducing slosh of fuel in the bladder when the unmanned aerial vehicle changes direction.

IPC Classes  ?

• B64D 37/08 - Internal partitioning
• B60K 15/077 - Fuel tanks with means modifying or controlling distribution or motion of fuel, e.g. to prevent noise, surge, splash or fuel starvation
• B64D 37/22 - Emptying systems facilitating emptying in any position of tank
• B64U 50/11 - Propulsion using internal combustion piston engines

Abstract

A drone comprising: wings; a body comprising a coupling region with a constant cross- sectional shape; and a saddle coupled to the wings and comprising a body coupling portion arranged to be coupled to the coupling region of the body to secure the wings to the body of the drone. The body coupling portion has a shape corresponding to the cross-sectional shape of the coupling region of the body.

IPC Classes  ?

• B64U 10/25 - Fixed-wing aircraft
• B64U 20/40 - Modular UAVs

Abstract

A land-launched unmanned aerial vehicle (UAV) is disclosed. The UAV has a liquid-fuelled gas turbine engine configured to facilitate cruise flight of the UAV. The UAV has a high wing arrangement. The UAV is configured to be detachably coupled to and launched from a dolly vehicle on a runway. Also disclosed is a UAV having a dry operating mass between 27 kg and 35 kg. Also disclosed is a UAV having a cylindrical fuselage, a high-wing mounted on an upper surface of the cylindrical fuselage, an empennage arranged behind the high-wing and having a twin tail arrangement, and a canard arrangement arranged in front of the high-wing. Other aspects include: a dolly vehicle for detachably coupling to the UAV; methods of controlling the dolly vehicle; methods of launching a UAV from a dolly vehicle; a drone system including the UAV and the dolly vehicle; and a UAV having a wing detachable from the fuselage.

IPC Classes  ?

• B64F 1/10 - Ground or aircraft-carrier-deck installations for launching aircraft using self-propelled vehicles
• B64U 70/93 - Portable platforms for use on a land or nautical vehicle
• B64U 10/25 - Fixed-wing aircraft
• B64U 30/14 - Variable or detachable wings, e.g. wings with adjustable sweep detachable
• B64U 50/12 - Propulsion using turbine engines, e.g. turbojets or turbofans