Control method and apparatus for an aircraft when taxiing

Patent metadata

Field	Value
Publication number	US-2016167772-A1
Application number	US-201514965592-A
Country	US
Kind code	A1
Filing date	Dec 10, 2015
Priority date	Dec 10, 2014
Publication date	Jun 16, 2016
Grant date	—

Abstract

A method of controlling the motion of a turning aircraft during taxiing on the ground, the aircraft having a steerable landing gear, for example a nose landing gear, operating in a free-to-caster mode, includes (a) ascertaining the rotational position (θ) of the steerable landing gear relative to the longitudinal axis (L) of the aircraft (b) receiving a control instruction that would, if effected, continue turning of the aircraft in the same direction away from the longitudinal axis, and (c) modifying the control instruction so that the angle between the rotational position of the steerable landing gear and the longitudinal axis will be lower than the angle that would otherwise be observed had the control instruction been effected and not so modified. The risk of damage to the steerable landing gear through over-steering may thus be reduced.

First claim

The invention is:

1 . A method of controlling the motion of an aircraft having a longitudinal axis during taxiing on the ground, wherein the aircraft comprises:
a steerable landing gear comprising one or more wheels positioned at a fore end of the aircraft, the steerable landing gear operating in a free-to-caster mode during performance of the method, one or more left main landing gears, each comprising one or more wheels and being positioned rearwardly and to the left of the steerable landing gear, and one or more right main landing gears each comprising one or more wheels and being positioned rearwardly and to the right of the steerable landing gear, and the method comprises the following steps, performed whilst the aircraft is turning in a direction away from the longitudinal axis of the aircraft, the rotational position of the steerable landing gear being non-parallel to the longitudinal axis:
ascertaining the rotational position of the steerable landing gear relative to the longitudinal axis of the aircraft,
receiving a control instruction that would, if effected, continue turning of the aircraft in the direction away from the longitudinal axis, and
if the rotational position is greater than a threshold angle, modifying the control instruction so that the angle between the rotational position of the steerable landing gear and the longitudinal axis will be lower than the angle that would otherwise be observed had the control instruction been effected and not so modified;
whereby the risk of damage to the steerable landing gear through over-steering is reduced.

2 . The method according to claim 1 , wherein the amount by which the control instruction is modified is greater at a first angle between the rotational position of the steerable landing gear and the longitudinal axis than at a second angle between the rotational position of the steerable landing gear and the longitudinal axis, the first angle being greater than the second angle, which is greater than the threshold angle.

3 . The method according to claim 1 , wherein, between the threshold angle and a higher angle, the amount by which the control instruction is modified increases monotonically with increasing angle between the rotational position of the steerable landing gear and the longitudinal axis.

4 . The method according to claim 3 , wherein, between the threshold angle and the higher angle, the amount by which the control instruction is modified increases proportionally with increasing angle between the rotational position of the steerable landing gear and the longitudinal axis.

5 . The method according to claim 1 , wherein the control instruction received comprises an instruction to effect differential braking to the main landing gears.

6 . The method according to claim 1 , wherein the control instruction received comprises an instruction to effect at least one of (a) differential braking to the main landing gears and (b) differential thrust from left and right engines of the aircraft,
such that there is an imbalance between the forces to be applied to the left of the aircraft as compared to the right of the aircraft, and the step of modifying the control instruction includes reducing the imbalance by changing the control instruction insofar as it affects the left of the aircraft and also reducing the imbalance by changing the control instruction insofar as it affects the right of the aircraft.

7 . The method according to claim 1 , wherein the control instruction received comprises an instruction that would effect braking and turning of the aircraft and wherein the step of modifying the control instruction results in substantially the same overall amount of braking, but reduced turning.

8 . The method according to claim 1 , wherein the aircraft is configured such that the steerable landing gear is operable in a directly steerable mode, the command instructions for controlling the rotational position of the steerable landing gear being provided by means of a human-operated moveable steering device in the cockpit, and wherein the control instruction received originates from a human operator of the aircraft operating the same human-operated moveable steering device.

9 . The method according to claim 1 , wherein the control instruction received is provided from an electronic aircraft control system seeking to effect a desired amount of turning.

10 . The method according to claim 1 , wherein the control instruction received is provided as a result of a human operator seeking to effect steering of the aircraft by means of performing one or more of the following actions:
(a) changing the thrust provided by one or more engines for providing forward thrust during flight, (b) changing the amount of braking applied to one or more of the main landing gears, and (c) changing an aerodynamic surface on the aircraft.

11 . An aircraft steering control system for controlling the steering of an aircraft when taxiing and the aircraft nose landing gear is in free-to-caster mode, the control system comprising
a module for ascertaining the angle of the rotational position of the steerable landing gear relative to the longitudinal axis of an aircraft; and a control unit configured to modify a control instruction to effect reduced steering of the aircraft in the event that the angle ascertained by said module meets certain criteria, so as to reduce the risk of excessive steering.

12 . The aircraft including a control system according to claim 11 , the control system being arranged to control the steering of the aircraft.

13 . A non-transitory memory device storing a computer program product configured to cause, when the computer program is executed, a computer implemented aircraft steering control system to perform the step of modifying of the control instruction as claimed in the method of claim 1 .

14 . A method to control turning of an aircraft during taxiing including:
ascertaining a desired rotational position of a steerable landing gear of the aircraft relative to a longitudinal axis of the aircraft to achieve a desired turning movement of the aircraft; if the desired rotational position is greater than a threshold rotational position, determining a second rotational position for the steerable landing gear, wherein the second rotational position sets an angle of the steerable landing gear relative to the longitudinal axis which is smaller than an angle of the steerable landing gear relative to the longitudinal axis corresponding to the desired rotational position; rotating the steerable landing gear to the second rotational position, and turning the aircraft due to the steerable landing gear being set at the second rotational position.

15 . The method of claim 14 wherein the steerable landing gear is at a forward region of a fuselage of the aircraft and aligned with the longitudinal axis.

16 . The method of claim 14 wherein the aircraft includes at least two main landing gears rearward of the steerable landing gear and each offset from the longitudinal axis.

Assignees

• Airbus Operations Ltd
• Airbus Operations Sas

Inventors

• Howell George
• Romana Louis-Emmanuel

Classifications

• B64C25/405

  Powered wheels, e.g. for taxing · CPC title

• B64C25/34

  wheeled type, e.g. multi-wheeled bogies · CPC title

• B64C25/48

  differentially operated for steering purposes · CPC title

• B64C25/50 Primary

  Steerable undercarriages; Shimmy-damping · CPC title

• G05D1/0202

  specially adapted to aircraft · CPC title