Modified braking systems and methods during taxi

Patent metadata

Field	Value
Publication number	US-12134465-B2
Application number	US-202117463968-A
Country	US
Kind code	B2
Filing date	Sep 1, 2021
Priority date	Sep 1, 2021
Publication date	Nov 5, 2024
Grant date	Nov 5, 2024

Abstract

A method of taxiing an aircraft may comprise: determining, via a brake controller, whether the aircraft is taxiing with a first thrust provided from a first side of the aircraft, a second thrust from a second side of the aircraft, or both the first thrust and the second thrust; and modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal deflection in response to the taxiing with the first thrust only.

First claim

What is claimed is:

1. A method of taxiing an aircraft, the method comprising:
receiving, via a brake controller, a first thrust angle of a first throttle and a second thrust angle of a second throttle;
determining, via the brake controller and based on the first thrust angle and the second thrust angle, whether the aircraft is taxiing with a first thrust from a first engine provided on a first side of the aircraft, a second thrust from a second engine provided on a second side of the aircraft, or both the first thrust and the second thrust; and
responsive to determining that the aircraft is taxiing with the first thrust only, modifying, via the brake controller, a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal displacement by controlling operation of a servo valve to supply, a first pressure at a first pedal displacement during taxiing with the first thrust only that is greater than a second pressure supplied at the first pedal displacement during normal taxiing.

2. The method of claim 1 , wherein modifying the first brake pressure comprises augmenting the first brake pressure over a predetermined range of pedal displacement.

3. The method of claim 2 , wherein the predetermined range of pedal displacement is above an idle pedal threshold.

4. The method of claim 1 , wherein modifying the first brake pressure supplied to the first brake is configured to counteract a yaw of the aircraft from the first thrust.

5. The method of claim 1 , wherein modifying the first brake pressure comprises modifying the first brake pressure by a pressure difference.

6. The method of claim 5 , wherein the pressure difference increases over a predetermined pedal displacement range extending from a smaller pedal displacement to a larger pedal displacement.

7. An article of manufacture including a tangible, non-transitory computer-readable storage medium having instructions stored thereon that, in response to execution by one or more processors, cause the one or more processors to perform operations comprising:
receiving a first thrust angle of a first throttle and a second thrust angle of a second throttle;
determining, based on the first thrust angle and the second thrust angle, that a first engine on a first side of an aircraft is being used for taxiing and a second engine on a second side of the aircraft is shut down or in an idle state for taxiing; and
responsive to determining that the first engine is being used for taxiing and the second engine is shut down or in the idle state for taxiing, modifying a first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal displacement by controlling operation of a servo valve to supply a first pressure at a first pedal displacement during taxiing with the first engine being used and the second engine being shut down or in the idle state that is greater than a second pressure supplied at the first pedal displacement during normal taxiing.

8. The article of manufacture of claim 7 , wherein the first thrust angle is associated with the first engine and the second thrust angle is associated with the second engine.

9. The article of manufacture of claim 8 , wherein the second thrust angle is approximately zero.

10. The article of manufacture of claim 7 , wherein modifying the first brake pressure includes augmenting the first brake pressure over a predetermined range of pedal displacement.

11. The article of manufacture of claim 10 , wherein the predetermined range of pedal displacement is above an idle pedal threshold.

12. The article of manufacture of claim 7 , wherein modifying the first brake pressure supplied to the first brake is configured to counteract a yaw of the aircraft from the first engine.

13. A brake system for an aircraft, comprising:
a first servo valve;
a first braking input device including a first pedal;
a second braking input device including a second pedal;
a first throttle corresponding to a first engine and a second throttle corresponding to a second engine;
a first brake assembly configured to be disposed on a first side of the aircraft, the first brake assembly configured to supply a first brake pressure through operation of the first servo valve in response to the first pedal being displaced;
a second brake assembly configured to be disposed on a second side of the aircraft, the second brake assembly configured to supply a second brake pressure in response to the second pedal being displaced; and
a brake controller configured to control the first brake pressure and the second brake pressure, the brake controller further configured to:
receive a first thrust angle of the first throttle and a second thrust angle of the second throttle,
determine, based on the first thrust angle and the second thrust angle, whether the aircraft is taxiing via thrust supplied only on the first side of the aircraft, supplied only on the second side of the aircraft, or supplied on both the first side and the second side of the aircraft, and
responsive to determining the aircraft is taxiing via thrust supplied only on the first side of the aircraft, modify the first brake pressure supplied to a first brake disposed on the first side of the aircraft as a function of pedal displacement by controlling operation of the first servo valve to supply a first pressure at a first pedal displacement during taxiing via thrust supplied only on the first side of the aircraft that is greater than a second pressure supplied at the first pedal displacement during normal taxiing.

14. The brake system of claim 13 , further comprising a second servo valve, the second servo valve corresponding to the second brake assembly.

15. The brake system of claim 13 , wherein modifying the first brake pressure supplied to the first brake is configured to counteract a yaw of the aircraft during taxiing.

16. The brake system of claim 13 , wherein the brake controller is further configured to determine the aircraft is taxiing.

Assignees

• Goodrich Corp

Inventors

• Georgin Marc

Classifications

• B60T8/1703

  for aircrafts · CPC title

• Y02T50/80

  Energy efficient operational measures, e.g. ground operations or mission management · CPC title

• B64C25/48

  differentially operated for steering purposes · CPC title

• B64C25/44 Primary

  Actuating mechanisms · CPC title

• B64C25/42 Primary

  Arrangement or adaptation of brakes · CPC title