An aerial vehicle and a method of taking a measurement using a sensor mounted on an aerial vehicle. The aerial vehicle has one or more propellers and one car more motors which are selectively operable to drive the one or more propellers to rotate to cause the vehicle to fly. A sensor is mounted on the aerial vehicle. The method includes operating the one or more motors to drive the one or more propellers to cause the vehicle to fly. At a first time instant, the one or more motors are slowed down or turned off. When the one or more motors are slowed down or turned off, a measurement is taken using the sensor; at a second time instant, which is after the measurement has been taken using sensor, operating the one or more motors again to drive the one or more propellers to cause the vehicle to fly.

An autopilot recoupling system for a rotorcraft having an automatic flight control system with multiple layers of flight augmentation. The autopilot recoupling system includes an autopilot recoupling input operable to generate an autopilot recoupling signal. An autopilot recoupling signal processor is communicably coupled to the autopilot recoupling input. The autopilot recoupling signal processor is configured to receive the autopilot recoupling signal from the autopilot recoupling input and responsive thereto, determine a state of the automatic flight control system, activate a trim systems layer of the automatic flight control system if the trim systems layer is not active, engage an attitude retention systems layer of the automatic flight control system if the attitude retention systems layer is disengage and recouple an autopilot systems layer of the automatic flight control system.

An autopilot recoupling system for a rotorcraft having an automatic flight control system with multiple layers of flight augmentation. The autopilot recoupling system includes an autopilot recoupling input operable to generate an autopilot recoupling signal. An autopilot recoupling signal processor is communicably coupled to the autopilot recoupling input. The autopilot recoupling signal processor is configured to receive the autopilot recoupling signal from the autopilot recoupling input and responsive thereto, determine a state of the automatic flight control system, activate a trim systems layer of the automatic flight control system if the trim systems layer is not active, engage an attitude retention systems layer of the automatic flight control system if the attitude retention systems layer is disengage and recouple an autopilot systems layer of the automatic flight control system.

A method of fabricating a panel for a helicopter airframe configurable in a plurality of helicopter configurations comprises the following steps. Operational characteristics of the helicopter airframe are defined. A skin panel is provided, where the skin panel is configured according to the operational characteristics of the helicopter airframe. A brace region is defined relative to the skin panel based on the operational characteristics of the helicopter airframe and the plurality of helicopter configurations. A brace assembly is operatively connected to the skin panel within the brace region to form a blank panel assembly. Accessories are arranged relative to the blank panel assembly according on one of the helicopter configurations to obtain a configured panel assembly.

A method of fabricating a panel for a helicopter airframe configurable in a plurality of helicopter configurations comprises the following steps. Operational characteristics of the helicopter airframe are defined. A skin panel is provided, where the skin panel is configured according to the operational characteristics of the helicopter airframe. A brace region is defined relative to the skin panel based on the operational characteristics of the helicopter airframe and the plurality of helicopter configurations. A brace assembly is operatively connected to the skin panel within the brace region to form a blank panel assembly. Accessories are arranged relative to the blank panel assembly according on one of the helicopter configurations to obtain a configured panel assembly.

A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

A variable guide vane assembly has: variable guide vanes having airfoils extending from inner ends to outer ends, the variable guide vanes pivotable about respective spanwise axes between one or more open positions and a closed position, in the closed position, trailing edge regions of the airfoils sealingly engage leading edge regions of adjacent ones of the airfoils to block an air flow; an outer wall extending around the central axis, the outer ends of the variable guide vanes pivotably engaged to the outer wall; and an inner wall extending around the central axis, the inner ends of the variable guide vanes pivotably engaged to the inner wall, the inner wall defining inner faces distributed about the central axis, a shape of the inner faces complementary to a shape of the inner ends of the airfoils to form a seal when the variable guide vanes are in the closed position.

A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

A rotorcraft provided with a yaw motion control system comprising a fairing and a rotor provided with blades, the blades being arranged in the fairing and able to rotate about an axis of rotation of the rotor, the fairing comprising a casing defining an air stream, the air stream extending in a direction of flow of the air within the fairing from an intake section towards an outlet section. The rotorcraft comprises an ice protection system comprising at least one grille arranged upstream of the air stream in the air flow direction, the grille facing the intake section parallel to the axis of rotation and the casing, no grille facing at least one unprotected section of the intake section in a direction parallel to the axis of rotation.

An extension assembly for a rotor system for rotating a plurality of rotor blades about a rotor axis with a central rotor hub that defines the rotor axis includes a beam assembly and a first bearing assembly. The beam assembly is configured to attach to the central rotor hub and is positioned at least partially within a corresponding one of the plurality of rotor blades. The first bearing assembly is configured to be fastened to the beam assembly and to at least one of a leading edge or a trailing edge of the corresponding one of the plurality of rotor blades.