Abstract: A single acting actuator for an aircraft landing gear assembly is disclosed having a piston mounted in a cavity and moveable relative to a housing between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers. At least one of the pressure chambers is associated with first and second outlets, with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.

Abstract: A sensor and method for sensing gas absorbed in hydraulic fluid in an aircraft shock absorber are disclosed. The hydraulic fluid and a gas are in fluid communication with each other. The sensor may be incorporated in the shock absorber or in servicing apparatus such as a servicing cart. The amount of gas absorbed in the hydraulic fluid is provided as a parameter which in combination with other parameters allows a user an improved means to determine the maintenance state of the shock absorber and to derive servicing actions.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: An aircraft control system 100 operably connected to a landing gear and a landing gear bay door of an aircraft 400. The system includes: a user interface 10 to receive manual inputs of first and second requests and a landing gear controller 20 configured to: receive a first indication indicative of user-operation of the user interface to input the first request, and to initiate movement of the landing gear bay door from a closed position to an open position on the basis of the first indication without initiating movement of the landing gear between an extended position and a retracted position; and receive a second indication indicative of user-operation of the user interface to input the second request, and to initiate movement of the landing gear between the extended position and the retracted position on the basis of the second indication.

Abstract: A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position.

Abstract: An system (10) for an aircraft (1) including a controller (100) configured to receive at least one signal during a take-off procedure of the aircraft. The signal includes information representative of at least one parameter of the aircraft. The controller is configured to determine whether a current or future aircraft climb rate associated with the take-off procedure meets a criterion, on the basis of the at least one signal. The controller is configured to determine at least one remedial action to be taken, such as performance of at least a portion of a procedure to retract a landing gear of the aircraft, when the controller determines that the aircraft climb rate does not meet the criterion.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: A method of operating a landing gear controller for an aircraft, including: the landing gear controller receiving one or more signals from at least one position sensor. The one or more signals indicate a position of one of a landing gear bay door and a landing gear when the landing gear bay door or the landing gear, respectively, is part way through a range of travel between two limits of travel. The method may also include the landing gear controller controlling movement of the other of the landing gear bay door and the landing gear on the basis of the one or more signals.

Abstract: 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.

Abstract: A single acting actuator for an aircraft landing gear assembly is disclosed having a piston mounted in a cavity and moveable relative to a housing between a retracted position and an extended position, the piston dividing the cavity into first and second pressure chambers. At least one of the pressure chambers is associated with first and second outlets, with the actuator being arranged such that, in respect of the relative movement in which the pressure chamber is the decreasing volume pressure chamber, in a first stage of the relative movement the first and second outlets are open thereby allowing actuator fluid to flow out of the pressure chamber through the first and second outlets and in a second stage of the relative movement the second outlet is open but the first outlet is closed, thereby acting to slow the relative movement of the piston with respect to the housing.

Abstract: An aircraft control system 100 operably connected to a landing gear and a landing gear bay door of an aircraft 400. The system includes: a user interface 10 to receive manual inputs of first and second requests and a landing gear controller 20 configured to: receive a first indication indicative of user-operation of the user interface to input the first request, and to initiate movement of the landing gear bay door from a closed position to an open position on the basis of the first indication without initiating movement of the landing gear between an extended position and a retracted position; and receive a second indication indicative of user-operation of the user interface to input the second request, and to initiate movement of the landing gear between the extended position and the retracted position on the basis of the second indication.

Abstract: 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.

Abstract: A landing gear system 100 for an aircraft including: a landing gear 130 that is movable between an extended position and a retracted position, the landing gear includes an extendible strut 136; a position sensor 140 configured to detect a position of a part of the extendible strut and output a signal indicative of the position; and a landing gear controller 150 that is communicably connected to the position sensor and is configured, in use, to: receive the signal from the position sensor; and, on the basis of the signal, determine that the strut has extended and the landing gear is in contact with the ground and automatically cause performance of at least a portion of a procedure to move the landing gear from the extended position to the retracted position

Abstract: A detection system 100 for detecting the integrity of an uplock system of a landing gear system 10. The detection system 100 includes: an uplock sensor 110 configured to detect whether the uplock is in the unlocked state or the locked state and to issue a first signal indicating whether the uplock is in the unlocked state or the locked state; one or more sensors 120 configured to detect a parameter of the landing gear system and to issue a second signal to indicate the parameter detected; and a controller 130 configured to issue a warning when the controller determines, based on the first signal and the second signal, that the uplock is in the locked state and the parameter detected indicates that the element is not in the first position, the warning indicating a loss of integrity of the uplock.

Abstract: The present invention provides an actuator comprising an actuator body, a piston relatively moveable within the actuator body, and a rod attached to the piston and extending out of the actuator body, the actuator body comprising a port for conveying actuator fluid, wherein the actuator also has a damping control portion provided with damping control fluid containing magnetic particles, wherein the piston or the rod is adjacent the damping control fluid, and a first electrical coil associated with the damping control portion, such that an electrical current supplied to the first electrical coil induces a magnetic field and causes the effective viscosity of the damping control fluid to increase, thus increasing the damping effect of the damping control fluid on the piston or rod. The invention also provides an aircraft assembly, such as a landing gear assembly, an aircraft and a method of operating an actuator.

Abstract: A landing gear controller (120) to control extension and retraction of a landing gear for an aircraft, the landing gear controller (120) configured to cause, during an aircraft take-off or landing procedure, a landing gear extension and retraction system (110) to perform only a first portion of a landing gear extension or retraction process, on the basis of a status of the aircraft and prior to receiving a command for the landing gear to be extended or retracted.

Abstract: The present invention provides an actuator comprising an actuator body, a piston relatively moveable within the actuator body, and a rod attached to the piston and extending out of the actuator body, the actuator body comprising a port for conveying actuator fluid, wherein the actuator also has a damping control portion provided with damping control fluid containing magnetic particles, wherein the piston or the rod is adjacent the damping control fluid, and a first electrical coil associated with the damping control portion, such that an electrical current supplied to the first electrical coil induces a magnetic field and causes the effective viscosity of the damping control fluid to increase, thus increasing the damping effect of the damping control fluid on the piston or rod. The invention also provides an aircraft assembly, such as a landing gear assembly, an aircraft and a method of operating an actuator.