Smart electric taxi path control

Patent metadata

Field	Value
Publication number	US-2016012736-A1
Application number	US-201414325565-A
Country	US
Kind code	A1
Filing date	Jul 8, 2014
Priority date	Jul 8, 2014
Publication date	Jan 14, 2016
Grant date	—

Abstract

An aircraft taxi control system may include a motor connected to drive a landing gear wheel of the aircraft. A motor controller may be connected to control speed of the motor. The system may also include an aircraft taxi route database, an aircraft position determination unit; an aircraft performance database and a processor configured to a) integrate signals from the aircraft taxi route database, the aircraft position determination unit and aircraft performance database, and b) produce a motor deceleration signal to the motor controller when the aircraft arrives at a predetermined distance from a predetermined location so that the aircraft arrives at the location traveling at a desired speed

First claim

1 . An aircraft taxi control system comprising:
at least one motor connected to drive at least one landing gear wheel of the aircraft; a motor controller connected to control speed of the at least one motor; an aircraft taxi route database; an aircraft position determination unit; an aircraft performance database; a processor configured to,
a) integrate signals from the aircraft taxi route database, the aircraft position determination unit and aircraft performance database, and
b) produce a motor deceleration signal, based on the signals integrated in step (a), to the motor controller when the aircraft arrives at a predetermined distance from a predetermined location so that the aircraft arrives at the predetermined location traveling at a desired speed without a need for manual speed adjustment by a pilot of the aircraft.

2 . The taxi control system of claim 1 wherein the predetermined location is a turning location.

3 . The taxi control system of claim 1 wherein the predetermined location is a hold location.

4 . The taxi control system of claim 1 further comprising a regenerative braking system wherein the processor is configured to produce a regenerative braking command in addition to the motor deceleration signal on an as needed basis so that the aircraft arrives at the predetermined location traveling at the desired speed.

5 . The taxi control system of claim 1 further comprising:
a nose wheel angle sensor; and
wherein the processor is configured to,
a) integrate signals from the aircraft taxi route database, the aircraft position determination unit, aircraft performance database, and the nose wheel angle sensor, and
b) produce a motor deceleration signal to the motor controller if the speed of the aircraft, during a turn, exceeds a safe speed for a sensed nose wheel angle.

6 . The taxi control system of claim 5 wherein the processor is configured to produce a regenerative braking command in addition to the motor deceleration signal on an as needed basis so that, during a turn, the aircraft does not exceed a safe speed for the sensed nose wheel angle.

7 . The taxi control system of claim 1 further comprising:
an obstacle sensor; and
wherein the processor is configured to,
a) integrate signals from the aircraft taxi route database, the aircraft position determination unit, aircraft performance database, and the obstacle sensor, and
b) produce a motor deceleration signal to the motor controller so that the aircraft maintains a desired separation from the obstacle.

8 . The taxi control system of claim 7 wherein the processor is configured to produce a regenerative braking command in addition to the motor deceleration signal on an as needed basis so that the aircraft maintains the desired separation from the obstacle.

9 . Apparatus for retrofitting an automated taxi control system onto an aircraft with a pre-existing friction brake system, the apparatus comprising:
at least one motor connected to drive at least one landing gear wheel of the aircraft; a motor controller connected to control speed of the at least one motor and the aircraft without employment of a pre-existing friction braking system; an aircraft taxi route database; an aircraft position determination unit; an aircraft performance database; a processor configured to,
a) integrate signals from the aircraft taxi route database, the aircraft position determination unit and aircraft performance database, and
b) produce a motor deceleration signal and a regenerative braking command to the motor controller when the aircraft arrives at a predetermined distance from a predetermined location so that the aircraft arrives at the predetermined location traveling at a desired speed without use of the pre-existing friction brake system,
wherein the motor deceleration signal and the regenerative braking command are based on the signals integrated in step (a).

10 . The apparatus of claim 9 wherein the predetermined location is a turning location.

11 . The apparatus of claim 9 wherein the predetermined location is a hold location.

12 . The apparatus of claim 9 further comprising a disengagement switch operable by a pilot actuation of the pre-existing friction brake system to suspend operation of the automated taxi control system.

13 . The apparatus of claim 9 further comprising a re-engagement switch operable by the pilot to resume operation of the automated taxi control system.

14 . (canceled)

15 . The apparatus of claim 9 further comprising a nose wheel angle sensor,
wherein the processor is configured to,
a) integrate signals from the aircraft taxi route database, the aircraft position determination unit, aircraft performance database, and the nose wheel angle sensor, and
b) produce a motor deceleration signals signal to the motor controller if the speed of the aircraft, during a turn, exceeds a safe speed for a sensed nose wheel angle.

16 . The taxi control system of claim 15 wherein the processor is configured to produce a regenerative braking command in addition to the motor deceleration signal on an as needed basis so that, during a turn, the aircraft does not exceed a safe speed for the sensed nose wheel angle.

17 . A method for controlling an aircraft during ground based operation comprising the steps:
propelling the aircraft with at least one motor connected to drive at least one landing gear wheel of the aircraft; controlling speed of the motor with a motor controller; providing information to a processor from;
a) an aircraft taxi route database.
b) an aircraft position determination unit. and
c) an aircraft performance database;
integrating signals in the processor from the aircraft taxi route database, the aircraft position determination unit and aircraft performance database, and producing a motor deceleration signal from the processor, based on the signals integrated in the processor, to the motor controller when the aircraft arrives at a predetermined distance from a turning location so that the aircraft arrives at the turning location traveling at a desired turning speed, wherein the motor deceleration signal is produced without manual speed adjusting of the aircraft by the pilot.

18 . The method of claim 17 further comprising the step of producing a regenerative braking command in addition to the motor deceleration signal on an as needed basis so that the aircraft arrives at the turning location traveling at the desired turning speed.

19 . The method of claim 17 further comprising:
integrating signals from a nose wheel angle sensor with signals from the aircraft taxi route database, the aircraft position determination unit, and the aircraft performance database; and
producing a motor deceleration signal to the motor controller if the speed of the aircraft, during a turn, exceeds a safe speed for a sensed nose wheel angle.

20 . The method of claim 17 further comprising the steps:
producing an obstacle-present signal;
sending the obstacle-present signal to the processor;
integrating, in the processor, the obstacle-present signal with the aircraft taxi route database, the aircraft position determination unit and the aircraft performance database, and
providing a motor deceleration signal to the motor controller so that the aircraft maintains a desired separation from the obstacle.

Assignees

• Honeywell Int Inc

Inventors

• Nutaro Joseph
• Jackson Patrick
• Sims Jay

Classifications

• G08G5/21

  located onboard the aircraft · CPC title

• G05D1/0083

  to help an aircraft pilot in the rolling phase · CPC title

• G08G5/51 Primary

  for control when on the ground, e.g. taxiing or rolling · CPC title

• B64C25/42

  Arrangement or adaptation of brakes · CPC title

• B64C25/405

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