A landing gear assembly for an aircraft includes an energy absorber and a land-contact assembly attached to the energy absorber. A retraction assembly is attached to the energy absorber via a pivot point. A trigger assembly is coupled to the energy absorber and the retraction assembly. The trigger assembly is configured to retract the land-contact assembly from an extended position to retracted position in response to a piston of the energy absorber reaching a maximum stroke position in which the trigger assembly triggers an actuator to actuate from a locked position to an unlocked position to release the retraction assembly in a controlled manner which rotates the energy absorber and the land-contact assembly to the retracted position. The maximum stroke position of the piston is beyond normal-operation stroke positions of the piston. A landing gear system and a method of activating the landing gear system utilizes the trigger assembly.

An emission-capturing apparatus includes a tank having an inlet and an outlet. The apparatus further includes a muffler fluidly coupled with the outlet to intercept fluid exiting the outlet, permit passage of gas through the muffler, and inhibit passage of liquid through the muffler. The apparatus further includes a hose having a tank end and a coupler end. The tank end is coupled to the inlet. The apparatus further includes a coupler coupled to the coupler end of the hose. The coupler has a drain hole. The coupler is configured to be coupled to a surface having an ejection port, to completely cover the ejection port when the coupler is coupled to the surface and to support the coupler end of the hose in a position to receive an emission when the drain hole is aligned with the ejection port.

An actuator assembly includes an actuation member, a release member, and a source of pressurized gas, wherein during a normal mode of operation, the actuation member and the release member are engaged to move in unison, and wherein during an emergency mode of operation, pressurized gas automatically decouples the actuation member from the release member to move separately. In accordance with yet other aspects of the present disclosure, an electro-mechanical actuator includes an electro-mechanical drive system and an integrated backup system operated by a gas generator, wherein when the backup system is activated, the electro-mechanical drive system is decoupled and the actuator moves to a predetermined position and mechanically locks in place.

An actuator assembly includes an actuation member, a release member, and a source of pressurized gas, wherein during a normal mode of operation, the actuation member and the release member are engaged to move in unison, and wherein during an emergency mode of operation, pressurized gas automatically decouples the actuation member from the release member to move separately. In accordance with yet other aspects of the present disclosure, an electro-mechanical actuator includes an electro-mechanical drive system and an integrated backup system operated by a gas generator, wherein when the backup system is activated, the electro-mechanical drive system is decoupled and the actuator moves to a predetermined position and mechanically locks in place.

The invention relates to a latching box for selectively retaining a movable element such as an undercarriage or a hatch in position, the box comprising a body carrying: a hook pivotally mounted about a first pivot axis between an engaged position and a disengaged position relative to the movable element; a locking member pivotally mounted about a second pivot axis parallel to the first pivot axis to pivot between a position for blocking the hook in the engagement position and a release position for releasing the hook; and at least one cam actuator in which the cam co-operates operationally with the locking member to move it towards the release position. The cam of the actuator is a cylindrical cam mounted to rotate about an axis of rotation orthogonal to the first and second pivot axes.

The invention relates to a latching box for selectively retaining a movable element such as an undercarriage or a hatch in position, the box comprising a body carrying: a hook pivotally mounted about a first pivot axis between an engaged position and a disengaged position relative to the movable element; a locking member pivotally mounted about a second pivot axis parallel to the first pivot axis to pivot between a position for blocking the hook in the engagement position and a release position for releasing the hook; and at least one cam actuator in which the cam co-operates operationally with the locking member to move it towards the release position. The cam of the actuator is a cylindrical cam mounted to rotate about an axis of rotation orthogonal to the first and second pivot axes.

A system for moving an aircraft door from an open position towards a closed position. The system includes an aircraft door actuator, an input receiving primary power from a primary power supply to power movement of the aircraft door from the open position towards the closed position, a secondary power supply to power the aircraft door actuator to move the aircraft door from the open position towards the closed position, and a controller configured to cause the secondary power supply to power the aircraft door actuator to cause the aircraft door actuator to move the aircraft door from the open position towards the closed position, on the basis of a determination that insufficient primary power is available from the primary power supply via the input to move the aircraft door from the open position towards the closed position.

A system for moving an aircraft door from an open position towards a closed position. The system includes an aircraft door actuator, an input receiving primary power from a primary power supply to power movement of the aircraft door from the open position towards the closed position, a secondary power supply to power the aircraft door actuator to move the aircraft door from the open position towards the closed position, and a controller configured to cause the secondary power supply to power the aircraft door actuator to cause the aircraft door actuator to move the aircraft door from the open position towards the closed position, on the basis of a determination that insufficient primary power is available from the primary power supply via the input to move the aircraft door from the open position towards the closed position.

An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.