A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.

A landing gear actuation system is disclosed herein. The landing gear actuation system includes an attachment point integral to a movable member, a flexible pull member having a first end coupled to the attachment point, and a motor configured to move the flexible pull member, wherein the movement of the flexible pull member moves the attachment point and the movable member.

Aircraft power system is disclosed having a hydraulic reservoir, a bi-directional hydraulic pump for pumping hydraulic fluid to and from the reservoir, and an electric motor. The electric motor is connectable to a first driveable component of the aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft. The hydraulic pump is connectable to the first driveable component of the aircraft such that the hydraulic pump is arranged to pump hydraulic fluid from the reservoir to drive the first driveable component of an aircraft. Thus, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the hydraulic pump.

Aircraft power system is disclosed having a hydraulic reservoir, a bi-directional hydraulic pump for pumping hydraulic fluid to and from the reservoir, and an electric motor. The electric motor is connectable to a first driveable component of the aircraft such that the electric motor is arranged to drive the first driveable component of the aircraft. The hydraulic pump is connectable to the first driveable component of the aircraft such that the hydraulic pump is arranged to pump hydraulic fluid from the reservoir to drive the first driveable component of an aircraft. Thus, in a first driveable mode of operation, the first driveable component is driven by both the electric motor and the hydraulic pump.

A device for filling a hydraulic circuit of an electro-hydrostatic system provided with a discharge valve and a filling valve includes a vacuum generator designed to be connected to the discharge valve via a first shut-off valve in order to eliminate the air or gases present in the circuit, and a source for supplying pressurised hydraulic fluid, which source is designed to be connected to the filling valve via a second shut-off valve and to the discharge valve and the first shut-off valve via a third shut-off valve in order to fill the hydraulic fluid circuit.

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.

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.

An example valve includes a housing, a sleeve disposed within the housing and having a first end and a second end opposite the first end, and the sleeve includes a plurality of sleeve protrusions at the first end and a plurality of fluid flow channels are formed between adjacent sleeve protrusions, a seal carrier disposed within the sleeve and having a carrier protrusion that extends from the second end of the sleeve and abuts against an interior surface of the housing, and an end cap mounted to the housing such that the plurality of sleeve protrusions abut against the end cap.

A landing gear for an aircraft includes a landing strut having proximal and distal ends with the proximal end couplable to the fuselage of the aircraft. The landing strut includes a gas chamber, a liquid chamber, a cylinder and a piston that is movable relative to the cylinder between extended and retracted positions. A wheel is coupled to the distal end of the landing strut. A force sensor is disposed between an extend stop surface of the piston and the chamber. Pressurized gas in the gas chamber biases the piston to the extended position such that the force sensor experiences a preload force. The force sensor is configured to detect a reduction in the preload force during a landing maneuver responsive to contact between the wheel and a landing surface.

A landing gear for an aircraft includes a landing strut having proximal and distal ends with the proximal end couplable to the fuselage of the aircraft. The landing strut includes a gas chamber, a liquid chamber, a cylinder and a piston that is movable relative to the cylinder between extended and retracted positions. A wheel is coupled to the distal end of the landing strut. A force sensor is disposed between an extend stop surface of the piston and the chamber. Pressurized gas in the gas chamber biases the piston to the extended position such that the force sensor experiences a preload force. The force sensor is configured to detect a reduction in the preload force during a landing maneuver responsive to contact between the wheel and a landing surface.