A simple, safe, and inexpensive flight control system in an aircraft. An anti-torque system for a rotary-wing aircraft has an airfoil with a first surface extending from a first trailing edge and a leading edge, and a second surface extending from a second trailing edge to join the first surface at the leading edge. The airfoil has a first moveable deflector panel pivotally coupled to the first trailing edge, and a second moveable deflector panel pivotally coupled to the second trailing edge. Means are provided to pivot the deflector panels in unison about their respective pivot axes to alter the direction of travel of the airflow downstream of the pivot axes over the surfaces of the deflector panels, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. The flight control system may be arranged within a fixed-wing aircraft.

An example rotational joint assembly for a robotic medical system, the rotational joint assembly comprising at least one arm segment and a rotational joint provided at one end of the arm segment. The rotational joint is to allow the arm segment to rotate about a rotational axis. The rotational joint comprising a brake to lock rotation of the arm segment at the rotational joint and an actuator to selectively engage or disengage the brake. The actuator comprising a cam having two stable regions separated by two transition regions, the two stable regions comprising a first stable region corresponding to engagement of the brake and a second stable region corresponding to disengagement of the brake.

An example rotational joint assembly for a robotic medical system, the rotational joint assembly comprising at least one arm segment and a rotational joint provided at one end of the arm segment. The rotational joint is to allow the arm segment to rotate about a rotational axis. The rotational joint comprising a brake to lock rotation of the arm segment at the rotational joint and an actuator to selectively engage or disengage the brake. The actuator comprising a cam having two stable regions separated by two transition regions, the two stable regions comprising a first stable region corresponding to engagement of the brake and a second stable region corresponding to disengagement of the brake.

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 method for monitoring remaining useful life (RUL) of an actuation system in a vehicle that includes receiving position data of the actuation system from a position sensor, maintaining a total distance traveled for the actuation system, and calculating the RUL of the actuation system. The calculating includes estimating force data using an output variable estimator, determining motor torque, weighing the estimated force data using a confidence level, predicting a total life of the actuation system based on the weighted force data, and comparing the predicted total life with the total distance traveled to determine the remaining useful life.

A method for monitoring remaining useful life (RUL) of an actuation system in a vehicle that includes receiving position data of the actuation system from a position sensor, maintaining a total distance traveled for the actuation system, and calculating the RUL of the actuation system. The calculating includes estimating force data using an output variable estimator, determining motor torque, weighing the estimated force data using a confidence level, predicting a total life of the actuation system based on the weighted force data, and comparing the predicted total life with the total distance traveled to determine the remaining useful life.

An assembly comprising a first part and a second part, the assembly comprising a disconnectable coupling system provided with a mechanical fuse for securing the first part and the second part according to an axis of movement up to a breaking threshold. The assembly comprises at least one single-use friction brake interposed between the first part and the second part, the friction brake braking a movement of the first part with respect to the second part after the mechanical fuse has broken.

An actuator system for actuating movement of a control surface of an aircraft wing includes a common input rail connectable to a means for providing movement to said input rail. The system also includes: a plurality of rotary geared actuators “RGAs”; a common output rail connectable to said control surface; wherein each of said plurality of RGAs is connected to said input rail by an individual input clutch and also connected to said output rail by an individual output clutch, and wherein the input clutch functions independently of the output clutch.

Example flap actuation systems and related methods are disclosed herein. An example flap actuation system includes a first actuator, a second actuator, a first drive arm coupled to the first actuator and to a flap, a second drive arm coupled to the second actuator and to the flap, a first cam, and a first output shaft. The first cam is to couple to the first drive to enable the first actuator to actuate the flap via the first drive arm. The example flap actuation system includes a second cam and a second output shaft. The first cam is to be uncoupled from the first drive arm in response to a failure of the first actuator. The second actuator is to actuate the flap via the first drive arm and the second drive arm in response to the failure of the first actuator.

A screw actuator having a screw shaft and a nut arrangement is described herein, the nut arrangement comprising: a primary nut; a first secondary nut having a first thread; a second secondary nut having a second thread; and a first attachment means. The first nut, first secondary nut, and second secondary nut are connected to the first attachment means with a first, initial, axial spacing between the first and second secondary nuts. The first secondary nut is mounted to the first attachment means via bearings that allow the first secondary nut to rotate relative to the first attachment. The first secondary nut is connected to the second secondary nut via a screw thread connection having a pitch lower than a pitch of a screw thread of the screw actuator shaft.