A wing system is provided for an air vehicle, the air vehicle having a fuselage including a fuselage longitudinal axis. The wing system includes a set of wings, configured for transitioning between a stowed configuration and a deployed configuration. The set of wings includes a first said wing having a first wing tip, a first wing longitudinal axis, and a first pivot axis; and a second said wing having a second wing tip, a second wing longitudinal axis, and a second pivot axis. The first pivot axis and the second pivot axis are non-coaxial. In the stowed configuration, the first wing and the second wing are in overlying relationship such that at least a majority of a pressure surface of one wing is facing a suction surface of the other wing, and the first wing tip is spaced from the second wing tip by a first lateral spacing. In the deployed configuration, the first wing is oriented with respect to the second wing such that the first wing tip is spaced from the second wing tip by a second lateral spacing greater than the first lateral spacing. The transitioning includes a pivoting operation, including: pivoting the first wing about the first pivot axis between the stowed configuration and the deployed configuration; and, pivoting the second wing about the second pivot axis between the stowed configuration and the deployed configuration.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

A parasite aircraft for airborne deployment and retrieve includes a wing; a fuselage rotatably mounted to the wing; a dock disposed on top of the fuselage and configured to receive a maneuverable capture device of a carrier aircraft; a pair of tail members extending from the fuselage; and a plurality of landing gear mounted to the wing. A method of preparing a parasite aircraft for flight includes unfolding an end portion of a wing; unfolding an end portion of a tail member of the parasite aircraft; and rotating a fuselage of the parasite aircraft so that the fuselage is perpendicular to the wing. A method of preparing a parasite aircraft for storage includes rotating a fuselage of the parasite aircraft to be parallel with a wing of the parasite aircraft; folding an end portion of the wing; and folding an end portion of a tail member of the parasite aircraft.

One embodiment is an aircraft including first and second fuselages; a wing assembly connecting the first and second fuselages, wherein the first and second fuselages are parallel to one another; first and second forward propulsion systems tiltably attached to forward ends of the first and second fuselages; and first and second aft propulsion systems fixedly attached proximate aft ends of the first and second fuselages.

Provided is a flight control apparatus including a pair of sensors that are spaced apart in a vertical direction on a surface of a flying object which uses motive power of a power source powered by a battery to fly and that detect a physical quantity corresponding to a state of an airflow, and a control unit that controls a flight state of the flying object on the basis of a difference between outputs of the pair of sensors.

A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

An aircraft that can improve cruising speed by making the body shape of the airframe (especially, multicopter) into a shape that has less unnecessary positive lift force by the main body and less drag in the cruising posture of the airframe. An aircraft equipped with a plurality of rotary blades including a propeller and a motor, wherein the aircraft comprises a main body with an inverted airfoil shape. The main body has an attack angle that does not generate a lift force or produces a negative lift force during cruising. The main body has a positive attack angle of 12 degrees or less. Further, it is provided with a mounting unit on which a mounted object can be mounted. The mounting unit is connected to the main body via the connection unit.

A foldable wing with foldable trailing edge flap, that includes a main wing and a foldable trailing edge flap. The main wing includes a wing supporting skeleton and a plurality of skin supporting ribs. The foldable trailing edge flap includes a plurality of crank-shaped flap supporting ribs, a flexible flap skin, a connecting shaft, and a return spring. The plurality of crank-shaped flap supporting ribs are hinged with lower surfaces of corresponding plurality of skin supporting ribs through the connecting shaft to form a foldable trailing edge flap supporting skeleton that relies on the plurality of skin supporting ribs. The return spring makes an upper surface of a long side of each crank-shaped flap supporting rib attach closely to a lower surface of each skin supporting rib. The flexible flap skin is attached to an upper surface of the foldable trailing edge flap supporting skeleton.

A multirotor aircraft that includes a chassis, three or more vertical rotors, one or more free wings and one or more fixed horizontal rotor. The free wing is attached to the chassis by an axial connection so that the angle of the free wing is changed relative to the chassis according the flow of air over the free wing. The fixed horizontal rotor enables the multirotor aircraft to lower and climb while flying forward at a stable horizontal pitch of the chassis.

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.