Aircraft ground lift dump flight control function

Patent metadata

Field	Value
Publication number	US-9665097-B2
Application number	US-201414896983-A
Country	US
Kind code	B2
Filing date	Jun 11, 2014
Priority date	Jun 14, 2013
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

A flight control system for an aircraft includes at least one flight control computer that carries out a ground lift dump function that selectively extends a spoiler located on a wing of the aircraft into an airflow passing over the wing. The at least one flight control computer includes arming logic that is responsive to an input signal indicative of an aircraft parameter to automatically arm the ground lift dump function during certain phases of operation of the aircraft. The at least one flight control computer includes spoiler deployment logic that is responsive to an arming signal from the aiming logic which indicates that the ground lift function is armed to deploy the spoiler into its extended position within the airflow passing over the wing of the aircraft to assist in stopping the aircraft while the aircraft is on the ground.

First claim

What is claimed is:

1. A flight control system for an aircraft, comprising:
at least one flight control computer that carries out a ground lift dump function that selectively extends a spoiler located on a wing of the aircraft into an airflow passing over the wing;
wherein the at least one flight control computer includes arming logic that is responsive to an input signal indicative of an aircraft parameter to automatically arm the ground lift dump function during certain phases of operation of the aircraft; and
wherein the at least one flight control computer includes spoiler deployment logic that is responsive to an arming signal from the arming logic which indicates that the ground lift function is armed to deploy the spoiler into its extended position within the airflow passing over the wing of the aircraft to assist in stopping the aircraft while the aircraft is on the ground.

2. The flight control system of claim 1 , wherein the spoiler comprises at least one of a ground spoiler and a multi-function spoiler.

3. The flight control system of claim 1 , wherein the certain phases of aircraft operation in which the ground lift dump function is automatically armed includes an on the ground phase after the aircraft has been in a flight phase.

4. The flight control system of claim 1 , wherein the certain phases of aircraft operation in which the ground lift dump function is automatically armed includes a takeoff condition of the aircraft such that the spoiler can be deployed into its extended position to assist in stopping the aircraft if the takeoff has been terminated prior to the aircraft taking off.

5. The flight control system of claim 1 , wherein the at least one flight control computer includes arming logic that is responsive to an input signal indicative of the aircraft parameter to automatically disarm the ground lift dump function during certain phases of aircraft operation.

6. The flight control system of claim 5 , wherein the certain phases of aircraft operation in which the ground lift dump function is automatically disarmed includes a taxi phase.

7. The flight control system of claim 5 , wherein the certain phases of aircraft operation in which the ground lift dump function is automatically disarmed includes a park phase.

8. The flight control system of claim 1 , wherein the spoiler deployment logic is also responsive to a signal from a lever in a cockpit in the aircraft, wherein the lever is movable by a pilot in the cockpit.

9. The flight control computer of claim 8 , wherein the spoiler deployment logic is responsive to the signal from the lever in the cockpit when the ground lift function is armed to move the spoiler into a position that is proportional to the amount of movement of the lever by the pilot in the cockpit, thereby affecting the amount of lift and drag on the wing of the aircraft.

10. The flight control system of claim 1 wherein the flight control computer comprises a portion of a fly-by-wire type of flight control system for the aircraft.

11. The flight control system of claim 1 , wherein the input signal comprises at least one of an aircraft altitude signal indicative of the height of the aircraft above ground, a weight on wheel signal indicative of a weight of the aircraft, and a wheel speed signal indicative of a speed of one or more wheels of the aircraft.

12. The flight control system of claim 1 ,
wherein the input signal comprises an aircraft altitude signal indicative of the height of the aircraft above ground, a weight on wheel signal indicative of a weight of the aircraft, and a wheel speed signal indicative of a speed of one or more wheels of the aircraft; and
wherein when the aircraft altitude signal is invalid and the weight on wheel signal does not give an indication of the weight of the aircraft, the spoiler deployment logic is operable to deploy the spoiler located on the wing in response to the wheel speed signal having a predetermined characteristic.

13. A method for implementing a ground lift dump function within a flight control system for an aircraft, the method comprising:
checking if the aircraft is in a taxi phase or a park phase and if so, then automatically disarming the ground lift dump function; and
checking if the aircraft is in one of a takeoff phase and in an in-flight phase and if so, then automatically arming the ground lift dump function.

14. The method of claim 13 , wherein automatically arming the ground lift dump function is based on at least one of an aircraft altitude signal indicative of the height of the aircraft above ground, a weight on wheel signal indicative of a weight of the aircraft, and a wheel speed signal indicative of a speed of one or more wheels of the aircraft.

15. The method of claim 14 , wherein when the aircraft altitude signal is invalid and the weight on wheel signal does not give an indication of the weight of the aircraft, deploying a spoiler located on a wing of the aircraft in response to the wheel speed signal having a predetermined characteristic.

16. The method of claim 13 , further comprising checking if a thrust command is in an idle condition and at least one main landing gear on the aircraft is on the ground and if so, then activating at least two ground lift spoilers on the aircraft into a fully deployed condition.

17. The method of claim 13 , further comprising checking if both of the main landing gears on the aircraft are on the ground and if so, then activating the at least two ground spoilers into the fully deployed condition and also activating at least some of a plurality of multi-function spoilers into a fully deployed condition.

18. The method of claim 13 , wherein if a result of the checking if the aircraft is in a takeoff phase or in an in-flight phase indicates that the aircraft is not in a takeoff phase or is not in an in-flight phase, then the method branching back to the step of checking if the aircraft is in a taxi phase or a park phase.

19. The method of claim 13 , wherein after automatically arming the ground lift dump function the method branches back to the step of checking if the aircraft is in a taxi phase or a park phase.

20. The method of claim 16 , wherein if a result of the checking if a thrust command is in an idle condition and at least one main landing gear on the aircraft is on the ground indicates that the thrust command is not in an idle condition and that the at least one main landing gear is not on the ground, then the method branching back to the step of checking if a thrust command is in an idle condition and at least one main landing gear on the aircraft is on the ground.

21. The method of claim 17 , wherein if as a result of the step of checking if both of the main landing gears on the aircraft are on the ground indicates that both of the main landing gears are not on the ground, then the method branching back to the step of checking if the aircraft is in a taxi phase or a park phase.

22. The method of claim 17 , wherein after the step of activating the at least two ground spoilers into the fully deployed condition and also activating at least some of a plurality of multi-function spoilers into a fully deployed condition, the method branching back to the step of checking if the aircraft is in a taxi phase or a park phase.

23. A computer program product for implementing a ground lift dump function with an aircraft flight control system, the computer program product comprising a non-transitory computer readable storage medium having

Assignees

• Bombardier Inc

Inventors

• Letang Antoine
• Chedaleux Florian
• Poudou Vincent
• Oberfeld Lawrence
• Palmer Eric

Classifications

• B64C13/503

  Fly-by-Wire · CPC title

• B64C13/22 Primary

  readily revertible to personal control · CPC title

• B64C13/12

  Dual control apparatus · CPC title

• G05D1/0061 Primary

  for transition from automatic pilot to manual pilot and vice versa · CPC title

• B64C9/323 Primary

  associated with wings · CPC title