A rotorcraft having pusher propeller generated power during autorotations. The rotorcraft has an engine powered mode and an autorotation mode. The rotorcraft includes an engine and a drivetrain configured to receive torque and rotational energy from the engine in the engine powered mode. A main rotor system is coupled to the drivetrain and is rotatable to generate lift and forward thrust for the rotorcraft in the engine powered mode. A pusher propeller is coupled to the drivetrain and is rotatable to generate forward thrust for the rotorcraft in the engine powered mode. In the autorotation mode, the pusher propeller is aerodynamically driven responsive to airflow therethrough and the drivetrain is configured to receive torque and rotational energy from the pusher propeller, thereby providing power to the main rotor system.

A rotorcraft having pusher propeller generated power during autorotations. The rotorcraft has an engine powered mode and an autorotation mode. The rotorcraft includes an engine and a drivetrain configured to receive torque and rotational energy from the engine in the engine powered mode. A main rotor system is coupled to the drivetrain and is rotatable to generate lift and forward thrust for the rotorcraft in the engine powered mode. A pusher propeller is coupled to the drivetrain and is rotatable to generate forward thrust for the rotorcraft in the engine powered mode. In the autorotation mode, the pusher propeller is aerodynamically driven responsive to airflow therethrough and the drivetrain is configured to receive torque and rotational energy from the pusher propeller, thereby providing power to the main rotor system.

Apparatuses and methods for activating a switch are provided. The switch is supported by one of a bracket and a panel and includes a switch body and a switch plunger that is moveably coupled to the switch body to activate and deactivate the switch. In one example, the apparatus includes a clamp body that is configured to be removably coupled to the one of the bracket and the panel and that has an opening formed therethrough. The apparatus further includes a rod portion having a first end portion that has a surface that includes a first concave surface. The rod portion is configured to be advanced through the opening. The surface interfaces with the switch plunger and moves the switch plunger to activate the switch when the clamp body is coupled to the one of the bracket and the panel and when the rod portion is advanced through the opening.

Apparatuses and methods for activating a switch are provided. The switch is supported by one of a bracket and a panel and includes a switch body and a switch plunger that is moveably coupled to the switch body to activate and deactivate the switch. In one example, the apparatus includes a clamp body that is configured to be removably coupled to the one of the bracket and the panel and that has an opening formed therethrough. The apparatus further includes a rod portion having a first end portion that has a surface that includes a first concave surface. The rod portion is configured to be advanced through the opening. The surface interfaces with the switch plunger and moves the switch plunger to activate the switch when the clamp body is coupled to the one of the bracket and the panel and when the rod portion is advanced through the opening.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative $\left(\frac{dN2i}{dt}\right)”,$
and automatically stopping the engine when the current derivative $\left(\frac{dN2i}{dt}\right)$
changes sign.

A method for stopping an engine of a rotorcraft in overspeed, the rotorcraft comprising at least one engine, the engine comprising a gas generator and a power assembly, the power assembly comprising at least one power turbine rotated by gases originating from the gas generator, the power assembly comprising at least one power shaft rotationally secured to the power turbine, the power assembly rotating about a longitudinal axis at a speed referred to as the “speed of rotation”. The method comprises steps consisting in measuring a current value of the speed of rotation, determining a time derivative of the current value of the speed of rotation, referred to as the “current derivative $\left(\frac{dN2i}{dt}\right)”,$
and automatically stopping the engine when the current derivative $\left(\frac{dN2i}{dt}\right)$
changes sign.

Embodiments of the present invention are an image exposure method and device for an unmanned aerial vehicle, and an unmanned aerial vehicle. The method comprises: firstly, acquiring the original image information about a target object, then obtaining the weighted image information according to the original image information, further obtaining the compensation amount of an automatic exposure according to the weighted image information, and finally adjusting an automatic exposure strategy according to the compensation amount of the automatic exposure. The method prevents an unmanned aerial vehicle from easily losing a target during the process of the unmanned aerial vehicle automatically following a moving object, even when encountering a change in light and shadow.

Embodiments of the present invention are an image exposure method and device for an unmanned aerial vehicle, and an unmanned aerial vehicle. The method comprises: firstly, acquiring the original image information about a target object, then obtaining the weighted image information according to the original image information, further obtaining the compensation amount of an automatic exposure according to the weighted image information, and finally adjusting an automatic exposure strategy according to the compensation amount of the automatic exposure. The method prevents an unmanned aerial vehicle from easily losing a target during the process of the unmanned aerial vehicle automatically following a moving object, even when encountering a change in light and shadow.

An autothrottle system to be interfaced with a full-authority digital engine control (FADEC) system having a command input that receives sensed power-control input (PCL) position signaling indicative of a manual throttle setting for an aircraft. The autothrottle system generates automated power command signaling that is synthesized to virtualize electrical characteristics of the sensed PCL position signaling such that the automated power command signaling is recognized by the FADEC system as sensed PCL position signaling.

An autothrottle system to be interfaced with a full-authority digital engine control (FADEC) system having a command input that receives sensed power-control input (PCL) position signaling indicative of a manual throttle setting for an aircraft. The autothrottle system generates automated power command signaling that is synthesized to virtualize electrical characteristics of the sensed PCL position signaling such that the automated power command signaling is recognized by the FADEC system as sensed PCL position signaling.