A drive system for driving a movable flow body is disclosed having a drive unit, a shaft, a torque sensing device, a no-back friction unit, and an axial bearing. The drive unit is coupled with the shaft to rotate the shaft, the torque sensing device is coupled with at least one of the drive unit and the shaft to detect a torque transferred from the drive unit into the shaft, the no-back friction unit is arranged between the axial bearing and an axial support means of the shaft, such that an axial load of the shaft is supported by the axial bearing, and the no-back friction unit is configured to substantially not counteract a rotation of the shaft in a first direction of rotation of the shaft and to apply a friction-induced additional torque to the shaft in an opposite second direction of rotation.

The present invention relates to a force application device for a control stick of an aircraft comprising a shaft and a control lever configured to rotate the shaft about a first axis, the device comprising: a magnetic brake comprising a braking part configured to be connected to the shaft, and a volume containing a rheological fluid in contact with the braking part, of variable shear resistance as a function of a magnetic field applied to the rheological fluid, a force feedback motor configured to exert a resistive force opposing the rotation of the shaft about the first axis, a motor power source, a movable magnetic element biased towards a position close to the magnetic brake, and distancing means configured to maintain the movable magnetic element in a position away from the magnetic brake, when such distancing means are powered by the power source.

A self-activated no-back device includes a housing, an input shaft, an output shaft, a reactor hub, first grooves, a brake hub, second grooves, a plurality of balls, a reactor plate, a brake pack, a reactor spring, and a load spring. The first grooves are formed on an interior side of the reactor hub interior side, and the second grooves are formed in an interior side of the brake hub. Each second groove is aligned with a different first groove to define a plurality of groove pairs. Each ball is positioned in a different one of the groove pairs. One side of the reactor plate contacts the reactor hub. The brake pack is selectively contacted by the brake hub. The reactor spring supplies a spring force to the reactor plate, and the load spring supplies a spring force to the brake pack.

A flying car that does not require complex transformation between a car and an aircraft, the flying car can quickly take off from a land, such as road or parking, and can land on the road or parking. The flying car is of triangular shape having a broad front and narrow rear. Three motorized members are coupled to three corners of a frame of the flying car. Each of the three motorized members includes a wheel assembly that includes a wheel and a wheel frame, an inner ring and an outer ring coupled to each other, and both mounted to the wheel frame. A fan mounted on the inner ring and one or more turbines mounted on the outer ring.

Disclosed is a force sensation generation device comprising a frame (10), suitable for attachment to a frame (2) of an aircraft. The device is configured to be joined to an aircraft control mechanism and to provide frictional resistance to the movement of the aircraft control mechanism. The device includes two frictional interfaces defined by two rotatable and two fixed surfaces. Application of sufficient force to the device will overcome the frictional forces at the frictional interfaces.

Disclosed is a force sensation generation device comprising a frame (10), suitable for attachment to a frame (2) of an aircraft. The device is configured to be joined to an aircraft control mechanism and to provide frictional resistance to the movement of the aircraft control mechanism. The device includes two frictional interfaces defined by two rotatable and two fixed surfaces. Application of sufficient force to the device will overcome the frictional forces at the frictional interfaces.

A system and method for testing no-back systems. In one embodiment, the system and method includes multiple actuators that are driven in an asynchronous manner as to impart internal forces that mimic external loads on the system. The actuators can be monitored to determine whether the no-back systems are performing as expected when loads are applied to the actuators.

A compact, efficient, and reliable electromechanical actuator that is capable of driving heavy loads at a high rate of speed and also capable of resisting large back driving forces. The actuator resists tension and compression back driving forces in a static state as well as when the actuator extends and retracts. The back driving forces are resisted even if the electronics (e.g., motor) fail.

A compact, efficient, and reliable electromechanical actuator that is capable of driving heavy loads at a high rate of speed and also capable of resisting large back driving forces. The actuator resists tension and compression back driving forces in a static state as well as when the actuator extends and retracts. The back driving forces are resisted even if the electronics (e.g., motor) fail.

For sealing at the transition between high-lift devices and fairings, a shutter assembly can be installed in a high-lift system, thereby forming the shutter arrangement. The shutter assembly includes the shutter panel and possibly the driving member. The shutter assembly can be installed in the high-lift system, to form any embodiment of the shutter arrangement. The shutter arrangement covers the trunnion opening and is moveable in correspondence with the movement of the high-lift device in a continuous and strictly monotone manner.