Methods and systems for deploying adjacent trailing edge flaps

Patent metadata

Field	Value
Publication number	US-11014649-B2
Application number	US-201716311356-A
Country	US
Kind code	B2
Filing date	Jun 27, 2017
Priority date	Jun 29, 2016
Publication date	May 25, 2021
Grant date	May 25, 2021

Abstract

Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

First claim

What is claimed is:

1. A trailing edge flap system for a wing of an aircraft, the system comprising:
a first flap assembly including a first flap movably coupled to a structure of the aircraft wing, the first flap assembly having a first stiffness;
a second flap assembly including a second flap movably coupled to the structure of the aircraft wing, the second flap being disposed adjacent the first flap, the second flap assembly having a second stiffness, the first stiffness of the first flap assembly being lower than the second stiffness of the second flap assembly;
one or more data processors operatively coupled to cause deployment of the first flap and of the second flap; and
non-transitory machine-readable memory storing instructions executable by the one or more data processors and configured to cause the one or more data processors to: using data representative of a flap deployment command, generate an output for causing deployment of the first flap by a first deployment amount and for causing deployment of the second flap by a second deployment amount where the first deployment amount of the first flap is greater than the second deployment amount of the second flap;
wherein the greater first deployment amount is adapted to at least partially compensate for a deflection of the first flap assembly relative to the second flap assembly when the first flap is deployed and subjected to an aerodynamic load.

2. The system as defined in claim 1 , wherein a deployment difference between the first deployment amount and the second deployment amount is adapted to improve continuity between the first flap and the second flap when the first flap and the second flap are deployed and subjected to the aerodynamic load.

3. The system as defined in claim 1 , wherein the instructions are configured to cause the one or more data processors to generate the output for causing simultaneous deployment of the first flap and second flap.

4. The system as defined in claim 1 , wherein the first flap is double-slotted and second flap is single-slotted.

5. The system as defined in claim 1 , wherein the first flap is disposed inboard of the second flap relative to the aircraft wing.

6. The system as defined in claim 5 , wherein an outboard edge of the first flap and an inboard edge of the second flap are substantially parallel when the first flap and the second flap are substantially retracted.

7. The system as defined in claim 1 , wherein a first trailing edge portion of the aircraft wing defined by the first flap is non-parallel to a second trailing edge portion of the aircraft wing defined by the second flap.

8. The system as defined in claim 1 , wherein the second flap is configured for generally streamwise deployment relative to the aircraft wing.

9. The system as defined in claim 1 , wherein:
the first flap assembly comprises one or more first tracks for guiding the deployment of the first flap; and
the second flap assembly comprises one or more second tracks for guiding the deployment of the second flap, the one or more first tracks and the one or more second tracks being at least partially embedded in the first flap and second flap respectively.

10. The system as defined in claim 1 , wherein the instructions are configured to cause the one or more data processors to determine the first deployment amount of the first flap based on an operating parameter of the aircraft.

11. The system as defined in claim 1 , wherein the instructions are configured to cause the one or more data processors to determine the first deployment amount of the first flap based on an airspeed of the aircraft.

12. An aircraft comprising the system as defined in claim 1 .

13. A system for deploying adjacent trailing edge flaps movably coupled to an aircraft wing where the adjacent trailing edge flaps are part of different flap assemblies having different stiffnesses, the system comprising:
one or more data processors operatively coupled to cause deployment of a first flap and of a second flap where the first flap is adjacent the second flap and where the first flap is part of a first flap assembly having a first stiffness and the second flap is part of a second flap assembly having a second stiffness where the first stiffness of the first flap assembly is lower than the second stiffness of the second flap assembly; and
non-transitory machine-readable memory storing instructions executable by the one or more data processors and configured to cause the one or more data processors to: using data representative of a flap deployment command, generate an output for causing deployment of the first flap by a first deployment amount and for causing deployment of the second flap by a second deployment amount where the first deployment amount of the first flap is greater than the second deployment amount of the second flap;
wherein the greater first deployment amount is adapted to at least partially compensate for a deflection of the first flap assembly relative to the second flap assembly when the first flap is deployed and subjected to an aerodynamic load.

14. The system as defined in claim 13 , wherein a deployment difference between the first deployment amount and the second deployment amount is adapted to improve continuity between the first flap and the second flap when the first flap and the second flap are deployed and subjected to the aerodynamic load.

15. The system as defined in claim 13 , wherein the instructions are configured to cause the one or more data processors to generate the output for causing simultaneous deployment of the first flap and second flap.

16. The system as defined in claim 13 , wherein the instructions are configured to cause the one or more data processors to determine the first deployment amount of the first flap based on an operating parameter of the aircraft.

17. The system as defined in claim 13 , wherein the instructions are configured to cause the one or more data processors to determine the first deployment amount of the first flap based on an airspeed of the aircraft.

18. An aircraft comprising the system as defined in claim 13 .

19. A method for deploying adjacent trailing edge flaps movably coupled to an aircraft wing during flight where the adjacent trailing edge flaps are part of different flap assemblies having different stiffnesses, the method comprising:
deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount; and
deploying a second flap adjacent the first flap by a second deployment amount, the second flap being part of a second flap assembly having a second stiffness, the first stiffness of the first flap assembly being lower than the second stiffness of the second flap assembly and the first deployment amount of the first flap being greater than the second deployment amount of the second flap;
wherein the greater first deployment amount is adapted to at least partially compensate for a deflection of the first flap assembly relative to the second flap assembly when the first flap is deployed and subjected to an aerodynamic load.

20. The method as defined in claim 19 , wherein a deployment difference between the first deployment amount and the second deployment amount is adapted to improve continuity between the first flap and the second flap when the first flap and the second flap are deployed and subjected to the aerodynamic load.

21. The method as defined in claim 19 , wherein the first flap is double-slotted and second flap is single-slotted.

Assignees

• Bombardier Inc

Inventors

• Akel Iyad
• Budnitsky Dmitry
• Smith Howard Ian
• Hanson Thomas

Classifications

• B64C9/16 Primary

  at the rear of the wing · CPC title

• B64C13/24

  Transmitting means · CPC title

• B64C13/26

  without power amplification or where power amplification is irrelevant · CPC title

• B64C13/16 Primary

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C9/20

  by multiple flaps · CPC title