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.

The invention relates to a mechanical non-return mechanism for an aircraft application, wherein the aircraft application can be part of a flight control. The non-return mechanism comprises at least one drag brake, at least one main brake, and at least one ball ramp mechanism.

A flight control computer (FCC) for a rotorcraft includes a processor and a non-transitory computer-readable storage medium storing a program to be executed by the processor, with the program including instructions for providing main rotor overspeed protection. The instructions for providing the main rotor overspeed protection include instructions for monitoring sensor signals indicating a main rotor RPM, determining a target operating parameter, determining one or more flight parameters in response to a relationship between the main rotor RPM and the target operating parameter indicating a main rotor overspeed condition. Determining the one or more flight parameters includes determining a setting for a flight control device of the rotorcraft that changes the main rotor RPM, controlling positioning of a pilot control according to the flight parameters, and controlling the flight control device of the rotorcraft according to positioning of the pilot control.

A variable camber wing for mounting to a vehicle chassis has an actuator shaft and a static pin extending from the chassis. The wing's nose segment defines a proximal edge and a distal edge and has a channel therethrough between the proximal and distal edges, an arcuate aperture therethrough aft of the channel, and a second aperture therethrough aft of the arcuate aperture. The wing has a first linkage defining a clevis on a proximal end and hingeably connected to the nose segment. The clevis can rotatably engage with the static pin extending through the arcuate aperture. A second linkage defines a second clevis on a proximal end and a distal edge. The second linkage is configured to hingeably connect to the first linkage.

A multi-slice hinge-line actuator includes a plurality of actuator slices mounted around a common axis of rotation and arranged to be rotated around the axis of rotation by a drive means in response to a control signal, the slices spaced axially along the axis of rotation. Each actuator slice has a first attachment means for attachment to a relatively fixed structure and a second attachment means for attachment to a moveable structure to be moved by the actuator in response to the control signal. The actuator also includes means for monitoring a strain pattern in the actuator at a plurality of locations along the axial direction of the actuator.

A multi-slice hinge-line actuator includes a plurality of actuator slices mounted around a common axis of rotation and arranged to be rotated around the axis of rotation by a drive means in response to a control signal, the slices spaced axially along the axis of rotation. Each actuator slice has a first attachment means for attachment to a relatively fixed structure and a second attachment means for attachment to a moveable structure to be moved by the actuator in response to the control signal. The actuator also includes means for monitoring a strain pattern in the actuator at a plurality of locations along the axial direction of the actuator.

An electronic device is provided, including a device shell and a flight photographing device. The device shell is provided with an opening and an inner cavity. The opening communicates with the inner cavity. The flight photographing device is movably arranged on the device shell. The flight photographing device is capable of extending out of the device shell through the opening or retracting into the device shell. In a case that the flight photographing device is located outside the device shell, the flight photographing device is separable from the device shell.

An electronic device is provided, including a device shell and a flight photographing device. The device shell is provided with an opening and an inner cavity. The opening communicates with the inner cavity. The flight photographing device is movably arranged on the device shell. The flight photographing device is capable of extending out of the device shell through the opening or retracting into the device shell. In a case that the flight photographing device is located outside the device shell, the flight photographing device is separable from the device shell.

A multi-rotor aircraft comprising a controller, an annular airframe, at least two first rotor units and at least two actuation components. Wherein, the annular airframe comprises at least two frames and at least two connecting units, the adjacent frames are movably connected by the connecting unit; the first rotor units are arranged on the annular airframe and are electrically connected with the controller, the first rotor units are used to provide lift for the multi-rotor aircraft to fly; the actuation components are arranged on the annular airframe and are electrically connected with the controller; when the multi-rotor aircraft flies, the actuation components are used for driving the adjacent frames to move away from each other or to move close to each other, so as to enlarge or reduce the enclosed area of the annular airframe respectively.

A multi-rotor aircraft comprising a controller, an annular airframe, at least two first rotor units and at least two actuation components. Wherein, the annular airframe comprises at least two frames and at least two connecting units, the adjacent frames are movably connected by the connecting unit; the first rotor units are arranged on the annular airframe and are electrically connected with the controller, the first rotor units are used to provide lift for the multi-rotor aircraft to fly; the actuation components are arranged on the annular airframe and are electrically connected with the controller; when the multi-rotor aircraft flies, the actuation components are used for driving the adjacent frames to move away from each other or to move close to each other, so as to enlarge or reduce the enclosed area of the annular airframe respectively.