Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door and a door support bracket attached to the landing gear door. The support bracket is attached to aircraft structure for pivotal movement about a pivot axis between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly is operatively connected to the door support bracket for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly which assists in pivotal movement of the door support bracket and the gear door supported thereby from the closed condition into the opened condition thereof.

Landing gear doors may be opened in an emergency event, e.g., a failure of the normal landing gear actuation system that requires a gravity free-fall deployment. The retractable aircraft landing gear door actuation mechanism will include a landing gear door and a door support bracket attached to the landing gear door. The support bracket is attached to aircraft structure for pivotal movement about a pivot axis between a closed condition whereby the landing gear door covers an aircraft landing gear when retracted relative to the aircraft structure, and an opened condition whereby the landing gear door is moved laterally and upwardly relative to the aircraft landing gear when extended relative to the aircraft structure. A gear door actuation assembly is operatively connected to the door support bracket for moving the door support bracket and the gear door supported thereby between the closed and opened conditions thereof. The gear door actuation assembly will include an over-the-center spring assembly which assists in pivotal movement of the door support bracket and the gear door supported thereby from the closed condition into the opened condition thereof.

An aircraft landing gear is disclosed including a main leg, a foldable stay and a lock link configured to hold the foldable stay in position when the landing gear is extended. The foldable stay includes a first stay member and a second stay member, and the landing gear is configured such that the second stay member rotates in a first direction from a first position to a second position as the landing gear moves from a retracted configuration to an extended configuration. An end stop is arranged such that in the event the lock link fails, the second stay member rotates in the first direction from the second position to a third position in which the stay contacts the end stop thereby preventing further movement of the second stay member in the first direction and wherein the foldable stay goes over centre as the second stay member moves from the first position to the third position.

An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.

An emergency extension system for extending at least one aircraft undercarriage, the emergency extension system comprising both electromechanical actuators, each electromechanical actuator having an identification component arranged to allocate an identifier to said electromechanical actuator, which identifier depends in particular on a function performed by said electromechanical actuator, and also an electrical card having a delay component arranged to delay actuation of a the electromechanical actuator by an actuation delay that depends on the identifier allocated to the electromechanical actuator, the electromechanical actuators of the emergency extension system thus being arranged to be actuated in succession in an actuation sequence that is defined by the actuation delays.

The present invention relates to an actuator in a landing gear system of an aircraft, comprising: an electric drive for driving the actuator and first drive electronics for controlling the electric drive that are connected to the drive via an electric line, with second drive electronics for controlling the electric drive that are connected to the drive via an electric line, with the first drive electronics and the second drive electronics being redundant with respect to one another.

The present invention relates to an actuator in a landing gear system of an aircraft, comprising: an electric drive for driving the actuator and first drive electronics for controlling the electric drive that are connected to the drive via an electric line, with second drive electronics for controlling the electric drive that are connected to the drive via an electric line, with the first drive electronics and the second drive electronics being redundant with respect to one another.

Some embodiments provide apparatuses configured to deploy a landing gear of an aircraft, comprising: a landing gear coupler configured to couple with the landing gear; a release link configured to cooperate the landing gear coupler with a drive shaft that is configured to drive the landing gear between a stowed position and a deployed position; an override driver cooperated with the landing gear coupler; wherein the release link is configured to releasably maintain a relative position of landing gear coupler relative to the drive shaft, and the release link is configured to disengage a coupling between the drive shaft and the landing gear coupler such that the landing gear coupler is configured to move independent of the drive shaft; and wherein the override driver is configured to drive the landing gear coupler to the deployed position.

Some embodiments provide apparatuses configured to deploy a landing gear of an aircraft, comprising: a landing gear coupler configured to couple with the landing gear; a release link configured to cooperate the landing gear coupler with a drive shaft that is configured to drive the landing gear between a stowed position and a deployed position; an override driver cooperated with the landing gear coupler; wherein the release link is configured to releasably maintain a relative position of landing gear coupler relative to the drive shaft, and the release link is configured to disengage a coupling between the drive shaft and the landing gear coupler such that the landing gear coupler is configured to move independent of the drive shaft; and wherein the override driver is configured to drive the landing gear coupler to the deployed position.

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 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.