Double over center crankshaft flap mechanism

Patent metadata

Field	Value
Publication number	US-11260958-B2
Application number	US-201916560773-A
Country	US
Kind code	B2
Filing date	Sep 4, 2019
Priority date	Sep 4, 2019
Publication date	Mar 1, 2022
Grant date	Mar 1, 2022

Abstract

A flap actuation mechanism incorporates a flap bracket attached to a flap and coupled to an underwing structure with a pivotal coupling. A crankshaft is configured for over center rotation and has aligned inboard and outboard crank arms extending from axially spaced inboard and outboard journals disposed in the underwing structure and configured to rotate about a rotation axis of the inboard and outboard journals. A crank pin is connected between the inboard and outboard crank arms. An actuating rod has a first end rotatably coupled to the crank pin and a second end coupled to the flap bracket. Rotation of the crankshaft displaces the actuating rod to cause rotation of the flap bracket and the flap.

First claim

What is claimed is:

1. A flap actuation mechanism, comprising:
a flap bracket attached to a flap and coupled to an underwing structure with a pivotal coupling;
a crankshaft configured for over center rotation having
aligned inboard and outboard crank arms extending from axially spaced inboard and outboard journals disposed in the underwing structure and configured to rotate about a rotation axis of the inboard and outboard journals;
a crank pin connected between the inboard and outboard crank arms; and,
an actuating rod, having a first end rotatably coupled to the crank pin and a second end coupled to the flap bracket, wherein rotation of the crankshaft displaces the actuating rod to cause rotation of the flap bracket and the flap.

2. The mechanism of claim 1 , wherein rotation of the crankshaft causes forward and aft movement of the actuating rod to cause rotation of the flap bracket and the flap between a stowed position and a deployed position.

3. The mechanism of claim 1 , wherein the inboard and outboard journals are spaced apart such that, during rotation of the crankshaft, a forward portion of the actuating rod can pass through the rotation axis and between the inboard and outboard journals.

4. The mechanism of claim 1 , wherein the second end of the actuating rod is coupled to the bracket at a predetermined distance from the pivotal coupling, and the inboard and outboard crank arms have an arm length that is not less than ¼ of the predetermined distance.

5. The mechanism of claim 1 , wherein a drive torque applied for rotation of the crankshaft is translated into an applied linear force by the actuating rod to the flap bracket to cause rotation of the flap between a stowed position and a deployed position.

6. The mechanism of claim 5 wherein one of the inboard and outboard journals has an internal spline and a rotary actuator supplies the drive torque, said rotary actuator having an output shaft configured to engage the internal spline.

7. The mechanism of claim 6 , wherein a second end of the actuating rod is coupled to the flap bracket at a predetermined distance from the pivotal coupling, and the inboard and outboard crank arms have an arm length that is not less than a predetermined fraction of the predetermined distance to provide a mechanical advantage between actuator force and the applied linear force of the actuating rod to rotate the flap.

8. The mechanism of claim 1 wherein the actuating rod is coupled to the crank pin with a split bearing and the actuating rod includes a rod cap configured to secure the split bearing and actuating rod to the crank pin.

9. The mechanism of claim 1 further comprising inboard and outboard roller bearings configured to receive the inboard and outboard journals, said inboard roller bearing disposed in the inboard and outboard ribs.

10. The mechanism of claim 9 further comprising at least one reaction ring received in a mating aperture in one of the inboard and outboard ribs and one of said inboard and outboard roller bearings is received in the at least one reaction ring.

11. The mechanism of claim 10 further comprising an inboard rub pad engaged between the inboard crank arm and an inner surface of the at least one reaction ring and an outboard rub pad engaged between the outboard crank arm and an inboard surface of the outboard rib.

12. The mechanism of claim 11 wherein the mating aperture has a diameter configured to receive the crankshaft within the inboard and outboard crank arms.

13. The mechanism of claim 12 wherein the outboard roller bearing is inserted in a receiving aperture in the outboard rib and the outboard nib pad, crankshaft, inboard rub pad, the inboard roller bearing and the at least one reaction ring are configured to be sequentially received through the mating aperture.

14. The mechanism of claim 10 wherein the at least one reaction ring is multi-faceted, keyed or scalloped to engage the mating aperture to react torsion.

15. The mechanism of claim 14 wherein the at least one reaction ring is octagonal.

16. An operating flap system for an aircraft, said system comprising:
a wing having an underwing flap support element comprising an underwing structure including an inboard rib and an outboard rib forming a clevis having a slot;
a flap bracket attached to a flap and rotatably coupled to the underwing structure with an axle extending between the inboard and outboard ribs;
a crankshaft configured for over center rotation having
aligned inboard and outboard crank arms extending from axially spaced inboard and outboard journals configured to rotate about a rotation axis, said inboard journal having an internal spline;
a crank pin connected between inboard and outboard crank arms;
inboard and outboard roller bearings configured to receive the inboard and outboard journals, said outboard roller bearing disposed in a receiving aperture in the inboard rib;
a reaction ring received in a mating aperture in the inboard rib said inboard roller bearing received in the reaction ring, said reaction ring being multi-faceted, keyed or scalloped to engage the mating aperture to react torsion, said reaction ring having a keyed or splined cylindrical flange;
an inboard rub pad engaged between the inboard crank arm and an inner surface of the reaction ring and an outboard rub pad engaged between the outboard crank arm and an inboard surface of the outboard rib;
a rotary actuator received on the splined cylindrical flange and having an output shaft configured to engage the internal spline; and,
an actuating rod extending through the slot and having a first end rotatably coupled to the crank pin with a split ball bearing secured with a rod cap and a second end coupled to the flap bracket, wherein rotation of the crankshaft displaces the actuating rod from a stowed position aligned with the rotation axis over a range of extension to a deployed position with the crankshaft rotated substantially 180° causing rotation of the flap bracket and the flap.

17. A method for deployment of a flap, said method comprising:
providing drive torque to a crankshaft;
rotating the crankshaft in a first direction to drive an actuating rod from a stowed position wherein the actuating rod is aligned with a rotation axis of the crankshaft, said actuating rod having a first end rotatably coupled to a crank pin of the crankshaft and a second end coupled to a flap bracket, wherein rotation of the crankshaft displaces the actuating rod to cause rotation of the flap bracket and the flap; and,
rotating the flap bracket with the actuating rod to extend a flap.

18. The method of claim 17 wherein the step of rotating the crankshaft includes driving the actuating rod to a deployed position with the crankshaft rotated substantially 180°.

19. The method of claim 18 further comprising continuing to rotate the crankshaft in the first direction from 180° to 360° to retract the flap.

20. The method of claim 17 further comprising rotating the crankshaft in a reverse direction to retract the flap.

Assignees

• Boeing Co

Inventors

• Tsai Kevin R
• Gruner Bryan J

Classifications

• B64C9/16 Primary

  at the rear of the wing · CPC title

• B64C13/30

  using cable, chain, or rod mechanisms · CPC title

• B64C9/18

  by single flaps · CPC title

• B64C9/02 Primary

  Mounting or supporting thereof · CPC title

• B64C2009/143

  comprising independently adjustable elements for closing or opening the slot between the main wing and leading or trailing edge flaps · CPC title