A lock system for a landing gear assembly may comprise a housing and a hook configured to rotate relative to the housing. A lock pin may be configured to translate into a rotational path of the hook. An electromechanical actuator may be configured to translate the lock pin.

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.

Described are systems and methods for a nacelle auxiliary landing gear to be utilized as an alternative landing gear in the event of main landing gear non-deployment. The systems described herein include a nacelle auxiliary landing gear that includes a nacelle auxiliary landing gear strut and a nacelle auxiliary landing gear wheel, coupled to the nacelle auxiliary landing gear strut, wherein at least a first portion of the nacelle auxiliary landing gear wheel is configured to be disposed outside of a nacelle of an aircraft propulsor. The nacelle auxiliary landing gear strut is coupled to a core engine. Techniques for use of the nacelle auxiliary landing gear are also described herein.

Described are systems and methods for a nacelle auxiliary landing gear to be utilized as an alternative landing gear in the event of main landing gear non-deployment. The systems described herein include a nacelle auxiliary landing gear that includes a nacelle auxiliary landing gear strut and a nacelle auxiliary landing gear wheel, coupled to the nacelle auxiliary landing gear strut, wherein at least a first portion of the nacelle auxiliary landing gear wheel is configured to be disposed outside of a nacelle of an aircraft propulsor. The nacelle auxiliary landing gear strut is coupled to a core engine. Techniques for use of the nacelle auxiliary landing gear are also described herein.

The invention relates to a hydraulic circuit for operating an aircraft landing gear comprising: a general valve (1) for admitting a supply pressure into the circuit; distributors (4, 6) for supplying undercarriages and/or landing gear doors operating actuators (3) or release actuators for hooks (5) maintaining the undercarriages and/or the doors in the retracted position; a depressurization valve (102) for, in an open position, allowing the selective distribution of supply pressure to an extension chamber (3A) or a retraction chamber (3B) of each operating actuator by the distributors, and, in a depressurization position, forcing the return of a retraction chamber of each operating cylinder. According to the invention, the depressurization valve is returned (105) in a stable manner to the depressurization position, and is moved into the open position only in response to the presence of supply pressure downstream of the general valve.

An aircraft landing gear control system 1000 configured to be operably connected to one or more landing gear systems 30, 40 of an aircraft. The aircraft landing gear control system includes a controller 20 configured to: send at least one output for initiating operation of the one or more landing gear systems; determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and determine at least one remedial action to be taken, when the controller determines that the at least one landing gear system has failed to operate correctly.

An aircraft landing gear control system 1000 configured to be operably connected to one or more landing gear systems 30, 40 of an aircraft. The aircraft landing gear control system includes a controller 20 configured to: send at least one output for initiating operation of the one or more landing gear systems; determine whether at least one landing gear system of the one or more landing gear systems has failed to operate correctly in response to the at least one output; and determine at least one remedial action to be taken, when the controller determines that the at least one landing gear system has failed to operate correctly.

A method 300 for deploying an aircraft landing gear including: receiving an aircraft landing gear deployment signal 310, receiving an aircraft position signal indicative of a distance of the aircraft from an aircraft landing site 320, receiving one or more flight signals indicating one or more dynamic conditions or parameters relating to the flight of the aircraft 330, determining, based at least on the one or more flight signals, a first aircraft position, relative to the aircraft landing site, at which the landing gear deployment should commence 340, and deploying the landing gear (a) when the aircraft reaches the first aircraft position, in the event that the deployment signal is received before the aircraft reaches the first aircraft position, or (b) immediately, in the event that the deployment signal is received when the aircraft has passed the first aircraft position 350.

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.