Aircraft control systems to enable shared input controls. A single inceptor may provide outputs to control both land-based aircraft controls and air-based aircraft controls to reduce the number of inceptors required. In an example a side-stick provides control of both pitch and aircraft nose-wheel steering. Active inceptor technology may be utilised to provide feedback to the operator on the control system state.

Aircraft control systems to enable shared input controls. A single inceptor may provide outputs to control both land-based aircraft controls and air-based aircraft controls to reduce the number of inceptors required. In an example a side-stick provides control of both pitch and aircraft nose-wheel steering. Active inceptor technology may be utilised to provide feedback to the operator on the control system state.

An aircraft nose landing gear assembly is disclosed including two wheels, motors, brakes, and a controller. The wheels are separated by a steering axis and independently rotatable about a rotation axis in a rotation direction. The motors and brakes are each arranged to selectively engage a respective wheel. The motors and brakes supplement and resist rotation of the respective wheel in the rotation direction, respectively. On the basis of an indication to the controller of rotation of the two wheels in the rotation direction, the controller is arranged to: cause one motor to engage its respective wheel and supplement rotation, and cause the brake associated with the other wheel to engage the other wheel and resist rotation. Engagement of the motor and brake causes the wheels to pivot about the steering axis during a turning event.

An aircraft nose landing gear assembly is disclosed including two wheels, motors, brakes, and a controller. The wheels are separated by a steering axis and independently rotatable about a rotation axis in a rotation direction. The motors and brakes are each arranged to selectively engage a respective wheel. The motors and brakes supplement and resist rotation of the respective wheel in the rotation direction, respectively. On the basis of an indication to the controller of rotation of the two wheels in the rotation direction, the controller is arranged to: cause one motor to engage its respective wheel and supplement rotation, and cause the brake associated with the other wheel to engage the other wheel and resist rotation. Engagement of the motor and brake causes the wheels to pivot about the steering axis during a turning event.

A sensor network for use in an aircraft, including a plurality of wireless nodes. A first wireless node of the plurality of wireless nodes is arranged to communicate with at least one other wireless node of the plurality of wireless nodes. The communication is via a secure communications channel and is on the basis of a control message received at the first wireless node. The at least one other wireless node is arranged to perform an operation on the basis of the control message.

A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.

A nose-wheel steering system is disclosed. In various embodiments, the system includes an actuator; a strut; and a gearing mechanism operably coupling the actuator to the strut, the gearing mechanism including a steering collar attached to the strut, and idler gear engaged with the actuator and a pinion having a first gear engaged with the idler gear and a second gear engaged with the steering collar.

A nose-wheel steering system is disclosed. In various embodiments, the system includes an actuator; a strut; and a gearing mechanism operably coupling the actuator to the strut, the gearing mechanism including a steering collar attached to the strut, and idler gear engaged with the actuator and a pinion having a first gear engaged with the idler gear and a second gear engaged with the steering collar.

A torque link assembly for a landing gear includes a lower torque link and an upper torque link that releasably engage first and second quick release pin assemblies. The pin assemblies each include a housing attached to one of the torque links, and a locking pin member extending through the housing. The locking pin member includes a rod portion and a pin portion, and is slidable between an engaged position and a disengaged position for hingedly connecting/disconnecting the torque links. One of the housing and the locking pin member includes a channel having a longitudinal portion and a circumferential portion, and the other has a guide pin that engages the channel. The guide pin is in the longitudinal portion of the channel when moving between the engaged and disengaged positions, and is retained in the disengaged position when the guide pin is in the circumferential portion of the channel.

A torque link assembly for a landing gear includes a lower torque link and an upper torque link that releasably engage first and second quick release pin assemblies. The pin assemblies each include a housing attached to one of the torque links, and a locking pin member extending through the housing. The locking pin member includes a rod portion and a pin portion, and is slidable between an engaged position and a disengaged position for hingedly connecting/disconnecting the torque links. One of the housing and the locking pin member includes a channel having a longitudinal portion and a circumferential portion, and the other has a guide pin that engages the channel. The guide pin is in the longitudinal portion of the channel when moving between the engaged and disengaged positions, and is retained in the disengaged position when the guide pin is in the circumferential portion of the channel.