An amphibious cargo carrying unmanned aerial vehicle (UAV) having a fuselage, two wings and two frames, in which a cargo hold is arranged at the lower end of the fuselage, the cargo hold is provided with a cargo chamber for cargo carrying, and the cargo hold can touch the water surface at the same time. When taking off or landing on the water surface, the hollow structure of the cargo chamber can provide additional buoyancy. The two wings are symmetrically arranged on both sides of the fuselage, the two frames are correspondingly arranged on the two wings, and the buoyancy parts can be detachably arranged on the two frames to provide buoyancy.

Embodiments of the present application are a UAV foot stand and a UAV. The UAV foot stand includes a main body, a mounting board, and a support structure, where one end of the main body is provided with a lightening cavity, one end of the main body that is provided with the lightening cavity extends outward to form the mounting board, the support structure is fixed to the main body, and the support structure at least partially extends into the lightening cavity and is connected to an inner wall of the lightening cavity, so as to increase rigidity of the main body.

Embodiments of the present application are a UAV foot stand and a UAV. The UAV foot stand includes a main body, a mounting board, and a support structure, where one end of the main body is provided with a lightening cavity, one end of the main body that is provided with the lightening cavity extends outward to form the mounting board, the support structure is fixed to the main body, and the support structure at least partially extends into the lightening cavity and is connected to an inner wall of the lightening cavity, so as to increase rigidity of the main body.

An aircraft has a supporting structure and a shell that can be filled with a gas and which is tensioned by the supporting structure. The supporting structure includes a plurality of rod or tube-shaped sections which define a circular, oval or polygonal main clamping plane for the shell.

A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

A vertical take-off and landing (VTOL) aircraft, that may be incorporated into a personal automobile, comprises a rectangular wing including an upper wing section having a right upper wing side and a left upper wing side, a lower wing section having a right lower wing side and left lower wing side, a right vertical wing section coupled to the right upper wing side and to the right lower wing side, and a left vertical wing section coupled to the left upper wing side and to the left lower wing side, the upper wing section having an upper wing cross section with a first asymmetrical airfoil shape configured to cause lift when in forward flight, the lower wing section having a lower wing cross section with a second asymmetrical airfoil shape for causing lift when in forward flight, each of the right vertical wing section and the left vertical wing section having a vertical wing cross section with a symmetrical shape to cause lateral stability when in forward flight; two elevons on at least one of the upper wing section and the lower wing section; at least one rudder on each of the right vertical wing section and the left vertical wing section; a support frame coupled to the rectangular wing; and a propulsion system coupled to the support frame.

A vertical take-off and landing (VTOL) aircraft has a first drivable configuration in which the pilot seat is positioned between the wings and facing the direction of forward travel. The VTOL may be driven in the first configuration as a normal automobile. In the first configuration the wings are aligned with the direction of forward travel and their surfaces are vertically oriented. In the first configuration, the VTOL may also attain altitude and be maneuvered using thrust from propulsion sources. In a second configuration, the pilot seat is rotated 90 degrees from the direction of forward travel to a direction of forward flight. Forward flight is achieved using thrust to rotate the wings from the vertical orientation to a lift-providing orientation. In concert with the rotation of the wings, the pi lot seat is counter-rotated to maintain the seat facing the direction of forward flight.

Provided is a flight vehicle that makes it possible to prevent electricity generation by a fuel cell from being stopped in flight even when a mistaken operation is conducted. The flight vehicle including a fuel cell and a propeller, the propeller to be driven by electric power generated by the fuel cell, the flight vehicle including: a stop device giving an instruction to stop the generation of electricity by the fuel cell; a control unit processing stopping of the generation of electricity by the fuel cell; a leg part grounding when the flight vehicle lands, to support a load of the flight vehicle; and a sensor detecting the load applied to the leg part, wherein the control unit permits the stopping of the generation of electricity based on signals from the stop device and the sensor only if a predetermined amount of the load is applied to the leg part.

A vertical takeoff and landing (VTOL) UAV having a UAV main body, two rear landing gears and two front landing gears; the two rear landing gears are fixedly connected to both sides of the rear bottom of the UAV main body, respectively; the two front landing gears are rotatably connected to both sides of the front bottom of the UAV main body, respectively. One end of the front landing gear away from the UAV main body is provided with a locating block. Rotating the front landing gear enables the locating block mounted on the front landing gear to get close to or away from the UAV main body.