Flap support systems and methods for a wing of an aircraft
A system and a method include a crank pivotally coupled to a bracket of a main body of a wing of an aircraft. A drive link is pivotally coupled to the crank. A flap link is pivotally coupled to a carrier beam extending from a flap moveably coupled to the main body of the wing. A rocker bracket is pivotally coupled to the flap link and the drive link.
1. A system comprising:
an actuator;
a shaft coupled to the actuator;
a carriage configured to ride along the shaft;
a crank pivotally coupled to a bracket of a main body of a wing of an aircraft, the crank further coupled to the shaft, wherein the crank includes an extension beam having a first end pivotally coupled to the bracket, and a second end coupled to the carriage, wherein the first end of the extension beam connects to an angled beam that extends to a link beam that is parallel to the extension beam, and wherein the link beam connects to an end beam that connects to the second end of the extension beam;
a drive link pivotally coupled to the crank, wherein the drive link is pivotally coupled to the angled beam;
a flap link pivotally coupled to a carrier beam extending from a flap moveably coupled to the main body of the wing; and
a rocker bracket pivotally coupled to the flap link and the drive link.
2. The system of claim 1 , wherein the flap link pivotally connects to the carrier beam at a first pivotal connection, wherein the rocker bracket pivotally connects to the flap link at a second pivotal connection, wherein the rocker bracket pivotally connects to the drive link at a third pivotal connection, and wherein the rocker bracket pivotally connects to the main body of the wing at a fourth pivotal connection.
3. The system of claim 2 , wherein the system provides a first over-center condition when the flap is in a stowed position, and wherein the system provides a second over-center condition when the flap is in a fully deployed position.
4. The system of claim 3 , wherein the first pivotal connection, the second pivotal connection, and the fourth pivotal connection are disposed along a first line to provide the first over-center condition.
5. The system of claim 4 , wherein the crank pivotally connects to the bracket at a fifth pivotal connection, wherein the crank pivotally connects to the drive link at a sixth pivotal connection, and wherein the fifth pivotal connection, the sixth pivotal connection, and the third pivotal connection are disposed along a second line to provide the second over-center condition.
6. The system of claim 1 , wherein the rocker bracket is aft from the crank.
7. The system of claim 1 , wherein the rocker bracket has a triangular shape.
8. The system of claim 1 , wherein a forward apex of the carrier beam connects to an aft end of the link beam.
9. An aircraft comprising:
a fuselage;
wings extending from the fuselage, wherein the wings include a main body, and a flap moveably coupled to the main body; and
a system comprising:
an actuator;
a shaft coupled to the actuator;
a carriage configured to ride along the shaft;
a crank pivotally coupled to a bracket of the main body, the crank further coupled to the shaft, wherein the crank includes an extension beam having a first end pivotally coupled to the bracket, and a second end coupled to the carriage, wherein the first end of the extension beam connects to an angled beam that extends to a link beam that is parallel to the extension beam, and wherein the link beam connects to an end beam that connects to the second end of the extension beam;
a drive link pivotally coupled to the crank, wherein the drive link is pivotally coupled to the angled beam;
a flap link pivotally coupled to a carrier beam extending from the flap; and
a rocker bracket pivotally coupled to the flap link and the drive link.
10. The aircraft of claim 9 , wherein the flap link pivotally connects to the carrier beam at a first pivotal connection, wherein the rocker bracket pivotally connects to the flap link at a second pivotal connection, wherein the rocker bracket pivotally connects to the drive link at a third pivotal connection, and wherein the rocker bracket pivotally connects to the main body of the wing at a fourth pivotal connection.
11. The aircraft of claim 10 , wherein the system provides a first over-center condition when the flap is in a stowed position, and wherein the system provides a second over-center condition when the flap is in a fully deployed position.
12. The aircraft of claim 11 , wherein the first pivotal connection, the second pivotal connection, and the fourth pivotal connection are disposed along a first line to provide the first over-center condition.
13. The aircraft of claim 12 , wherein the crank pivotally connects to the bracket at a fifth pivotal connection, wherein the crank pivotally connects to the drive link at a sixth pivotal connection, and wherein the fifth pivotal connection, the sixth pivotal connection, and the third pivotal connection are disposed along a second line to provide the second over-center condition.
14. The aircraft of claim 9 , wherein the rocker bracket is aft from the crank.
15. The aircraft of claim 9 , wherein the rocker bracket has a triangular shape.
16. The aircraft of claim 9 , wherein a forward apex of the carrier beam connects to an aft end of the link beam.
17. A method comprising:
coupling a shaft to an actuator;
coupling a carriage to the shaft, wherein the carriage is configured to ride along the shaft;
pivotally coupling a crank to a bracket of a main body of a wing of an aircraft;
coupling the crank to the shaft;
pivotally coupling a drive link to the crank, wherein the crank includes an extension beam having a first end pivotally coupled to the bracket, and a second end coupled to the carriage, wherein the first end of the extension beam connects to an angled beam that extends to a link beam that is parallel to the extension beam, and wherein the link beam connects to an end beam that connects to the second end of the extension beam;
pivotally coupling a flap link to a carrier beam extending from a flap moveably coupled to the main body of the wing, wherein the drive link is pivotally coupled to the angled beam; and
pivotally coupling a rocker bracket pivotally to the flap link and the drive link.
18. The method of claim 17 , wherein the flap link pivotally connects to the carrier beam at a first pivotal connection, wherein the rocker bracket pivotally connects to the flap link at a second pivotal connection, wherein the rocker bracket pivotally connects to the drive link at a third pivotal connection, wherein the rocker bracket pivotally connects to the main body of the wing at a fourth pivotal connection, wherein the system provides a first over-center condition when the flap is in a stowed position, wherein the system provides a second over-center condition when the flap is in a fully deployed position, wherein the first pivotal connection, the second pivotal connection, and the fourth pivotal connection are disposed along a first line to provide the first over-center condition, wherein the crank pivotally connects to the bracket at a fifth pivotal connection, wherein the crank pivotally connects to the drive link at a sixth pivotal connection, and wherein the fifth pivotal connection, the sixth pivotal connection, and the third pivotal connection are disposed along a second line to provide the second over-center condition.
19. The method of claim 17 , wherein the rocker bracket is aft from the crank, and wherein the rocker bracket has a triangular shape.
20. The method of claim 17 , wherein a forward apex of the carrier beam connects to an aft end of the link beam.