Abstract: A pedal cartridge for an aircraft. The pedal cartridge is connectable to a pedal mechanism and includes: a pedal. The pedal includes a pedal axle receiving portion configured to receive a pedal axle of the pedal mechanism such that the pedal is rotatably connectable to the pedal axle. The mechanism also includes a first rotation sensor component, the first rotation sensor component configured to interact with a second rotation sensor component of the pedal mechanism to permit rotation of the pedal about the pedal axle to be detected.

Abstract: An apparatus for adjusting aircraft inceptor trim includes an inceptor centring device mechanically coupled to a control shaft that rotates in response to inceptor inputs. The inceptor centring device includes an inceptor centring spring preloaded with a preload force to provide a first biasing force to bias the control shaft to an inceptor neutral position. The apparatus has a trim mechanism, mechanically coupled to the inceptor centring device, and includes a trim locking device having a locked state and an unlocked state. A resistance force of the trim mechanism with the trim locking device in the unlocked state is less than the preload force, such that when the trim mechanism is in the unlocked state, actuation of the inceptor adjusts the position of the inceptor centring device to alter the degree of trim.

Abstract: A cockpit control inceptor for an aircraft includes an armrest configured to receive the forearm of a user and to be operated by the forearm of the user in at least one direction. A first end of the armrest is coupled to a handle; wherein the armrest is connected to a fixed part of the cockpit control inceptor, wherein the armrest is configured to move relative to the fixed part of the cockpit control inceptor to provide a first aircraft control command.

Abstract: A control mechanism for an aircraft includes: a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable and being connectable to an inceptor; an inceptor connector connected to the translatable part of the conversion mechanism; a differential device connected to the rotatable part of the conversion mechanism, the conversion mechanism being configured to reversibly convert translational motion of the inceptor connector to rotational motion of the differential device; an adjustment member connected to the differential device; and a control member connected to the differential device; wherein the differential device is configured such that the adjustment member is maintainable in position during an aircraft control process to permit: translation of the inceptor connector from a translational neutral position; and corresponding movement of the control member, to control the aircraft through the differential device.

Abstract: An apparatus for adjusting aircraft inceptor trim includes an inceptor centring device mechanically coupled to a control shaft that rotates in response to inceptor inputs. The inceptor centring device includes an inceptor centring spring preloaded with a preload force to provide a first biasing force to bias the control shaft to an inceptor neutral position. The apparatus has a trim mechanism, mechanically coupled to the inceptor centring device, and includes a trim locking device having a locked state and an unlocked state. A resistance force of the trim mechanism with the trim locking device in the unlocked state is less than the preload force, such that when the trim mechanism is in the unlocked state, actuation of the inceptor adjusts the position of the inceptor centring device to alter the degree of trim.

Abstract: An aircraft flight control apparatus includes a control input device comprising a moveable control input component and a feeling feedback apparatus. A processing apparatus is arranged to use user information to determine a control input profile and generate at least one aircraft control signal and/or control the feeling feedback apparatus to apply force to the control input component. The processing apparatus is arranged to generate the at least one aircraft control signal and/or control the feeling feedback apparatus based at least partially on the control input profile.

Abstract: A control mechanism for an aircraft includes: a conversion mechanism having a translatable part and a rotatable part, the translatable part being reversibly translatable and being connectable to an inceptor; an inceptor connector connected to the translatable part of the conversion mechanism; a differential device connected to the rotatable part of the conversion mechanism, the conversion mechanism being configured to reversibly convert translational motion of the inceptor connector to rotational motion of the differential device; an adjustment member connected to the differential device; and a control member connected to the differential device; wherein the differential device is configured such that the adjustment member is maintainable in position during an aircraft control process to permit: translation of the inceptor connector from a translational neutral position; and corresponding movement of the control member, to control the aircraft through the differential device.

Abstract: A pedal cartridge for an aircraft. The pedal cartridge is connectable to a pedal mechanism and includes: a pedal. The pedal includes a pedal axle receiving portion configured to receive a pedal axle of the pedal mechanism such that the pedal is rotatably connectable to the pedal axle. The mechanism also includes a first rotation sensor component, the first rotation sensor component configured to interact with a second rotation sensor component of the pedal mechanism to permit rotation of the pedal about the pedal axle to be detected.

Abstract: A brake rod for a steering/braking mechanism includes a rod body having a longitudinal axis, a rod end at a first end of the rod body, the rod end having a bore therethrough having a bore axis arranged generally perpendicular to the rod longitudinal axis, and a rod end shield mounted to the rod and extending in a longitudinal direction axially beyond the rod end.

Abstract: A positioning and position maintaining device comprises a solenoid having an armature and an electromagnetic holder. The solenoid is arranged to effect positioning of an object upon translation of the armature and the electromagnetic holder is arranged to effect position maintaining in order to maintain the object in the position effected by the solenoid. An apparatus for aircraft autopilot and manual control feel-force control switching comprises an autopilot mechanism and the positioning and position maintaining device. The positioning and position maintaining device is arranged to engage the autopilot mechanism and maintain the engagement thereof. A method of switching between autopilot and manual control in an aircraft is also envisaged.

Abstract: A brake rod for a steering/braking mechanism includes a rod body having a longitudinal axis, a rod end at a first end of the rod body, the rod end having a bore therethrough having a bore axis arranged generally perpendicular to the rod longitudinal axis, and a rod end shield mounted to the rod and extending in a longitudinal direction axially beyond the rod end.

Abstract: A positioning and position maintaining device comprises a solenoid having an armature and an electromagnetic holder. The solenoid is arranged to effect positioning of an object upon translation of the armature and the electromagnetic holder is arranged to effect position maintaining in order to maintain the object in the position effected by the solenoid. An apparatus for aircraft autopilot and manual control feel-force control switching comprises an autopilot mechanism and the positioning and position maintaining device. The positioning and position maintaining device is arranged to engage the autopilot mechanism and maintain the engagement thereof. A method of switching between autopilot and manual control in an aircraft is also envisaged.