A system and method for remote control of a mobile device is provided herein. The system includes a primary receiver for providing primary command and control of the mobile device; a secondary receiver for providing secondary command and control of the mobile device; the mobile device configured to respond to command and control signals sent by any of the primary receiver and the secondary receiver; and a relay platform for relaying the command and control signals throughout the system. The primary receiver may include an extended reality component.

A system and method for remote control of a mobile device is provided herein. The system includes a primary receiver for providing primary command and control of the mobile device; a secondary receiver for providing secondary command and control of the mobile device; the mobile device configured to respond to command and control signals sent by any of the primary receiver and the secondary receiver; and a relay platform for relaying the command and control signals throughout the system. The primary receiver may include an extended reality component.

Various embodiments of the present disclosure provide a parasail-assisted system for launching a fixed-wing aircraft into free flight and for retrieving a fixed-wing aircraft from free flight.

An unmanned aerial vehicle (UAV) for gas transport is disclosed. The UAV includes a fuselage enclosing a volume, and a gas reservoir enclosed within the fuselage, filling at least a majority of the volume. The gas reservoir is configured to receive and store a gas at a pressure no greater than 100 bar. The UAV also includes a propulsion system having at least one engine, each of the at least one engine coupled to a prop that is driven by the at least one engine using energy derived from the gas stored in the gas reservoir. The UAV also includes a control system communicatively coupled to the propulsion system and configured to operate the unmanned aerial vehicle to autonomously transport the gas. The UAV may have a footprint while on the ground, and the footprint of the UAV may be no larger than three standard parking spaces.

An aircraft having a fixed wing is operative to perform vertical takeoff and landing while positioned in a nose-down orientation. The aircraft has a fixed wing having a leading edge and a trailing edge; a propulsion system operative to selectively provide forward propulsion and rearward propulsion; and a controller operative to control operation of the propulsion system. The propulsion system provides rearward propulsion during takeoff of the aircraft to move the aircraft in a direction of the trailing edge of the fixed wing, and provides forward propulsion during flight of the aircraft to move the aircraft in a direction of the leading edge of the fixed wing. The aircraft maintains the wing substantially vertical with the trailing edge facing upwards during takeoff, and transitions to having the wing substantially horizontal during flight. A vertical landing procedure is also provided.

The aircraft comprises a fuselage defining a fuselage main axis. The fuselage comprises a docking system for fixing removable nacelles. The aircraft has wings equipped with tilting actuators for rotating wings about rotation axes parallel to the fuselage main axis and at least six propellers mechanically connected to the fuselage. The aircraft also has at least one cryo-hydrogen tank and at least one fuel cell for supplying power to the propellers, and

A capacitor for supplying power to the propellers, charged by at least one fuel cell. This capacitor stores electrical energy greater than the energy needed by all the propellers for ten seconds of hovering flight. Each propeller is equipped with a tilting actuator for rotating the propeller about a rotation axis making an angle of less than 45 degrees with a plane perpendicular to the fuselage main axis. The fuselage having a forward and a rear portion defining a forward to rear order of the propellers, in cruise flight, the two forward propellers are activated to provide vertical thrust, the intermediate propellers between the forward and rearmost propellers are not activated and the two rearmost propellers are activated to provide horizontal thrust.

The present disclosure provides a versatile drone and nest launching system. A hybrid UAV drone having fixed wings in addition to vertical take-off and landing capabilities is used to enable the launching nest to remain compact and of simple design with few moving parts, while also housing a drone capable of travelling long distances. The entire system is configured function autonomously, utilising a solar-powered charging pad installed on the nest to repeatedly recharge and relaunch depleted drones. Novel mounting systems for situating the nest in a variety of terrains are also disclosed.

A method for dynamically controlling the attitude of a rotary-wing drone. The method includes dynamically controlling the attitude of the drone when the drone is flying using lift of each of four wings of the drone, by controlling the attitude of the drone by sending differentiated commands to one or more propulsion units of the drone so as to rotate the drone about a roll axis and/or pitch axis and/or heading axis of the drone from a current angular position to a final angular position, the axes being defined in the reference point of the drone.

A rotary-wing drone includes a drone body that includes an electronic board controlling the piloting of the drone, and four link arms that include a rigidly connected propulsion unit. The link arms form lift-producing wings.

An unmanned aerial vehicle (UAV) includes lift rotors and control rotors. The lift rotors are mounted to the UAV and oriented to provide a first vertical thrust to the UAV. The control rotors are mounted to the UAV outboard of the lift rotors and oriented to provide a second vertical thrust to the UAV. The control rotors are each smaller than any of the lift rotors.