A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted at a fixed rotational axis and has a pair of flanges, each flange having an aperture, and a channel extending aft from the pair of flanges. A fuse pin is received through the aperture in each flange. A coupler link is attached to an actuator at a first end and pivotally engaged to the carrier beam by the fuse pin. Extension of the coupler link by the actuator rotates the carrier beam from a stowed position to a deployed position. Responsive to a moment induced on the flap and carrier beam by a ground contact load, the fuse pin is frangible to shear releasing the coupler link to translate into the channel.

A flap support mechanism includes a carrier beam on which a flap is mounted. The carrier beam is rotatably mounted at a fixed rotational axis and has a pair of flanges, each flange having an aperture, and a channel extending aft from the pair of flanges. A fuse pin is received through the aperture in each flange. A coupler link is attached to an actuator at a first end and pivotally engaged to the carrier beam by the fuse pin. Extension of the coupler link by the actuator rotates the carrier beam from a stowed position to a deployed position. Responsive to a moment induced on the flap and carrier beam by a ground contact load, the fuse pin is frangible to shear releasing the coupler link to translate into the channel.

A method for controlling a control surface multirod actuator arrangement and the arrangement including: a first and a second multirod actuator configured to move or clamp around a first set of piston rods; a third multirod actuator configured to move or clamp around a second set of piston rods; a control unit configured to control motion of the first set of piston rods in a first motion mode and to control motion of the second set of piston rods in a second motion mode. Steps are moving at least one piston rod of first set of piston rods and/or clamping in parked position at least one piston rod of the second set of piston rods.

A method for controlling a control surface multirod actuator arrangement and the arrangement including: a first and a second multirod actuator configured to move or clamp around a first set of piston rods; a third multirod actuator configured to move or clamp around a second set of piston rods; a control unit configured to control motion of the first set of piston rods in a first motion mode and to control motion of the second set of piston rods in a second motion mode. Steps are moving at least one piston rod of first set of piston rods and/or clamping in parked position at least one piston rod of the second set of piston rods.

A hybrid fly/drive vehicle capable of being converted between a flying mode in which it is capable of flying in air and a road riding mode in which it is capable of driving on a road in normal traffic, includes an arrangement to allow the engine to be pedal-controlled in road riding mode and lever-controlled in flying mode, and further includes pedals for engine control and possibly clutch actuation in road riding mode and for rudder control in flying mode, which pedals also actuate the brakes in flying mode.

A hybrid fly/drive vehicle capable of being converted between a flying mode in which it is capable of flying in air and a road riding mode in which it is capable of driving on a road in normal traffic, includes an arrangement to allow the engine to be pedal-controlled in road riding mode and lever-controlled in flying mode, and further includes pedals for engine control and possibly clutch actuation in road riding mode and for rudder control in flying mode, which pedals also actuate the brakes in flying mode.

An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.

An aircraft wing with a wing structure and a spoiler movable between a stowed configuration and a deployed configuration are disclosed. The spoiler includes an actuator configurable between an engaged mode and a disengaged mode. When the actuator is in the engaged mode, the actuator can restrict movement of the spoiler and move the spoiler between the stowed configuration and deployed configuration. In the disengaged mode, the actuator allows free movement of the spoiler, such that the spoiler may pop up due to reduced air pressure on the aircraft wing.

A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.

A spoiler for an aircraft wing is movable between a stowed configuration and a deployed configuration in a “pop-up” manner. The spoiler includes a hinged top flap movable between a first position and a second position, wherein in the first position the hinged top flap is constrained by an actuator, and in the second position the hinged top flap is unconstrained by the actuator. When the hinged top flap is in the second position, airflow over the top surface of the aircraft wing acts to pull the spoiler into the deployed position.