A VTOL (vertical take-off and landing) box-wing aerial vehicle with multirotor to provide VTOL flight includes a detachable cabin, centered fuselage, a pair of first wings extending outward from the upper portion of the fuselage and a pair of second wings extending outwardly and from the lower portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joints the first wing and second wing at the tip to form the box-wing. The pylon includes heading control rudder. Secured to the wing or pylon or both wing and pylon, an overhead boom extending longitudinally to support a plurality of lift rotors or tiltable rotors for VTOL flight. Finally, the fuselage mounted push rotor or the overhead boom mounted tiltable rotors propel the vehicle forward to generate lift from the wings. Furthermore, the wings are equipped with elevators and ailerons for flight control.

Provided is a vibration control system for a compound helicopter with a rotor and a fixed wing. The fixed wing includes a movable flap that is mounted on a rear edge of the fixed wing. The vibration control system periodically moves the movable flap so as to periodically change lift of the fixed wing such that vibration aerodynamically generated by the fixed wing is in anti-phase with vibration caused by rotation of the rotor.

The present invention is directed to systems and methods for redundant flight control configured for use in an aircraft. More specifically, a system is provided that includes a plurality of actuators that are configured to move a flight component of an aircraft such that one actuator is configured to move the flight component if the other actuator fails to move the flight component upon receipt of an attitude command from a pilot control.

The present invention is directed to systems and methods for redundant flight control configured for use in an aircraft. More specifically, a system is provided that includes a plurality of actuators that are configured to move a flight component of an aircraft such that one actuator is configured to move the flight component if the other actuator fails to move the flight component upon receipt of an attitude command from a pilot control.

The invention relates to a flight system having at least two actuated flapping wings (2), an actuated tail unit (9), a control device and an exoskeleton (1) for at least one person. The exoskeleton (1) is movable independently of the flapping wings (2). The control device is configured to receive motion sensor signals from the exoskeleton (1) and to use the motion sensor signals to define specified movement signals and to control the flapping wings (2) and/or the tail unit (9) by way of the specified movement signals. The specified movement signals can be defined such that the movements of the flapping wings (2) and/or of the tail unit (9) follow those of the exoskeleton (1).

The invention relates to a flight system having at least two actuated flapping wings (2), an actuated tail unit (9), a control device and an exoskeleton (1) for at least one person. The exoskeleton (1) is movable independently of the flapping wings (2). The control device is configured to receive motion sensor signals from the exoskeleton (1) and to use the motion sensor signals to define specified movement signals and to control the flapping wings (2) and/or the tail unit (9) by way of the specified movement signals. The specified movement signals can be defined such that the movements of the flapping wings (2) and/or of the tail unit (9) follow those of the exoskeleton (1).

Systems and methods for optically measuring a position of a measurement surface relative to a reference position. The system is a wireless network comprising a centrally located data acquisition computer and a multiplicity of remotely located sensor modules mounted at different locations within wireless communication range of a central receiver. Each sensor module is mounted to a clamp that is made specific to a control surface location and embedded with an RFID tag to denote clamp location. The optical components of the sensor modules are selected to enable indication of the linear position of a measurement surface relative to a reference position and then broadcast the measurement results. The broadcast results are received by the central receiver and processed by the data acquisition computer, which hosts human interface software that displays measurement data.

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.

An exemplary anti-torque system for a rotorcraft includes a fan located inside of a channel that extends inside of a fuselage from an inlet proximate a forward end of the tail boom to an outlet at an aft end of the tail boom, the outlet is oriented to direct airflow from the channel onto a rudder coupled to a trailing edge of a vertical stabilizer.

An exemplary anti-torque system for a rotorcraft includes a fan located inside of a channel that extends inside of a fuselage from an inlet proximate a forward end of the tail boom to an outlet at an aft end of the tail boom, the outlet is oriented to direct airflow from the channel onto a rudder coupled to a trailing edge of a vertical stabilizer.