Aircraft autonomous pushback
AssigneeAirbus Operations GmbH
InventorsJames Morris, Antonio Colosimo
Life of this patent
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Abstract
The invention provides methods and systems for controlling speed of an aircraft during an autonomous pushback manoeuvre, i.e. under the aircraft's own power without a pushback tractor. The method includes applying a torque to at least one landing gear wheel of the aircraft, the torque being in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel. The torque applied does not exceed a limit for ensuring aircraft longitudinal stability. For longitudinal stability the torque applied should not cause the aircraft to risk a tip-over event.
Claims44
A method of controlling speed of an aircraft during backwards motion of the aircraft when in contact with the ground, the method comprising:
- applying a torque to at least one landing gear wheel of the aircraft, the torque is in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel,
- wherein the torque applied does not exceed a limit for ensuring aircraft longitudinal stability,
- wherein the step of applying torque to the landing gear wheel comprises applying a braking torque to the wheel using a friction brake assembly,
- wherein the method further comprises the steps of:
- measuring the aircraft speed,
- comparing the measured aircraft speed to a predetermined threshold limit, the predetermined threshold limit is that at which the aircraft longitudinal stability is not ensured, and
- displaying a warning indication in the aircraft cockpit when the measured speed exceeds that predetermined threshold limit.
An autonomous pushback braking system for an aircraft, comprising:
- a wheel drive system for driving one or more of the aircraft's landing gear wheels in rotation, wherein the wheel drive system is operable to drive the wheel in rotation to effect backwards motion of the aircraft when in contact with the ground, a friction brake assembly for applying a braking torque to at least one landing gear wheel of the aircraft, the torque is in a direction opposite to the backwards rolling direction of rotation of the landing gear wheel, and wherein the torque applied does not exceed a limit for ensuring aircraft longitudinal stability, wherein a measured aircraft speed is compared to a predetermined threshold limit at which the aircraft longitudinal stability is not ensured, and wherein a warning indication is displayed in the aircraft cockpit when the measured speed exceeds that predetermined threshold limit.
Dependencies are inferred from the claim text.