Structural mechanism for unlocking and engaging a controllable surface on a hinged platform (Wing)

• US 7,665,690 B2
• Filed: 12/04/2007
• Issued: 02/23/2010
• Est. Priority Date: 12/29/2005
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Sheahan, James J. Jr., Morris, Charles E.
• Primary Examiner(s): Dinh; Tien
• Assistant Examiner(s): Sanderson; Joseph W
• Application Number:
  US11/949,980
• Publication Number:
  US 20080087763A1
• Time in Patent Office: 812 Days
• Field of Search: 244/49, 244/99.2, 244/3.29, 92/19, 745/27, 192/69.91
• US Class Current: 244/49
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft
• CPC Class Codes: B64U 20/50 Foldable or collapsible UAVs with frangible components B64U20/30
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep

Abstract

A structural mechanism for an aircraft includes a support, a hinged surface, and a hinge assembly joining the hinged surface to the support. An actuation system includes an actuator shaft engaged to the hinges and lying coincident with a hinged-surface hinge axis and extending through the aligned center passageways of the hinges of the hinge assembly. A lock is selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock. An actuator structure is controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and is controllably operable to rotate the actuator shaft about the hinged-surface hinge axis.

Claims

1. A structural mechanism comprising:

an air vehicle support surface;

a hinged surface affixed to the air vehicle support surface;

a hinge assembly joining the hinged surface to the air vehicle support surface so that the hinged surface may pivot relative to the air vehicle support surface, wherein the hinge assembly comprises at least one hinge, and wherein the at least one hinge have center passageways therethrough linearly aligned along a hinged-surface hinge axis;

an actuation system comprising

an actuator shaft lying coincident with the hinged-surface hinge axis and extending through the aligned center passageways of the hinges of the hinge assembly, wherein the actuator shaft is engaged to the at least one hinge,

a lock selectively operable to lock the hinged surface to the support when the actuator shaft engages the lock,

an actuator structure

controllably operable to move the actuator shaft longitudinally along the hinge-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and

controllably operable to rotate the actuator shaft about the hinged-surface hinge axis; and

an actuator controller for the actuator structure.

2. The structural mechanism of claim 1, wherein the air vehicle support surface is a deployable wing.

3. The structural mechanism of claim 2, further including:

a retention pin-receiver recess in the actuator shaft,

a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and

a retention pin driver that drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess.

4. The structural mechanism of claim 2, further including:

a retention pin-receiver recess in the actuator shaft,

a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and

a retention pin driver that

drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess, and

controllably withdraws the retention pin from the pin-receiver recess.

5. The structural mechanism of claim 1, wherein the air vehicle support surface has a thickness of 3 inches or less.

6. The structural mechanism of claim 1, wherein the air vehicle support surface extends from a fuselage of an air vehicle.

7. The structural mechanism of claim 6, wherein the air vehicle support surface is a deployable wing.

8. The structural mechanism of claim 1, wherein the at least one hinge comprises at least two spaced-apart hinges.

9. The structural mechanism of claim 1, wherein

each of the hinges of the at least one hinge comprises an interior hinge spline, and

the actuator shaft comprises an exterior shaft spline for each of the interior hinge splines, wherein the exterior shaft splines are positioned to engage the respective interior hinge splines to permit movement of the actuator shaft longitudinally along the hinged-surface hinge axis between the first shaft axial position and the second shaft axial position, while continuing to maintain the engagement between the interior hinge splines and the exterior shaft splines.

10. The structural mechanism of claim 1, wherein the lock comprises:

an exterior locking spline and a compatible interior locking spline.

11. The structural mechanism of claim 1, wherein the actuator structure comprises:

an engagement linear device controllably operable to move the actuator shaft longitudinally along the hinge surface hinge axis between the first shaft axial position and the second shaft axial position, and

a rotational actuator engaged to the actuator shaft, whereby the actuator shaft may be controllably rotated.

12. The structural mechanism of claim 1, wherein the actuator controller defines a zeroed pivotable position of the hinged surface when the actuator shaft is in the first shaft axial position.

13. The structural mechanism of claim 1, further including:

a retention mechanism that retains the actuator shaft in the second shaft axial position.

14. The structural mechanism of claim 1, further including:

a controllable retention mechanism that controllably retains the actuator shaft in the second shaft axial position, and controllably allows the actuator shaft to return to the first shaft axial position.

15. An aircraft comprising:

a body of an air vehicle;

a folding surface joined to the body of the air vehicle, wherein the folding surface is movable from a stowed position to a deployed position;

a control surface;

a hinge assembly joining the control surface to the folding surface so that the control surface may pivot relative to the folding surface, wherein the hinge assembly comprises at least two spaced-apart hinges and wherein the at least two spaced-apart hinges have passageways therethrough linearly aligned along a control-surface hinge axis;

an actuation system comprising

an actuator shaft lying coincident with the control-surface hinge axis and extending through the passageways of the hinges of the hinge assembly, wherein the actuator shaft is engaged to each hinge of the at least two the hinges,

a lock selectively operable to lock the control surface to the folding surface when the actuator shaft engages the lock,

an actuator structure

controllably operable to move the actuator shaft longitudinally along the control-surface hinge axis between a first shaft axial position wherein the actuator shaft engages the lock and the at least two spaced-apart hinges, and a second shaft axial position wherein the actuator shaft does not engage the lock but does engage the hinges, and

controllably operable to rotate the actuator shaft about the control-surface hinge axis; and

an actuator controller for the actuator structure.

16. The aircraft of claim 15, wherein

each of the at least two spaced-apart hinges comprises an interior hinge spline, and

the actuator shaft comprises an exterior shaft spline for each of the interior hinge splines, wherein the exterior shaft splines are positioned to engage the respective interior hinge splines to permit movement of the actuator shaft longitudinally along the control-surface hinge axis between the first shaft axial position and the second shaft axial position, while continuing to maintain the engagement between the interior hinge splines and the exterior shaft splines.

17. The aircraft of claim 15, wherein the actuator structure comprises:

an engagement linear device controllably operable to move the actuator shaft longitudinally along the control-surface hinge axis between the first shaft axial position and the second shaft axial position, and

a rotational actuator engaged to the actuator shaft, whereby the actuator shaft may be controllably rotated.

18. The aircraft of claim 15, wherein the actuator controller defines a zeroed pivotable position of the control surface when the actuator shaft is in the first shaft axial position.

19. The aircraft of claim 15, further including:

a retention mechanism that retains the actuator shaft in the second shaft axial position.

20. The aircraft of claim 15, further including:

a controllable retention mechanism that controllably retains the actuator shaft in the second shaft axial position, and controllably allows the actuator shaft to return to the first shaft axial position.

21. The aircraft of claim 15, further including:

a retention pin-receiver recess in the actuator shaft,

a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and

a retention pin driver that drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess.

22. The aircraft of claim 15, further including:

a retention pin-receiver recess in the actuator shaft,

a retention pin in the body, wherein the retention pin is disposed to engage the pin-receiver recess when the actuator shaft is in the second shaft axial position, and

a retention pin driver that

drives the retention pin into the pin-receiver recess when the retention pin is aligned with the pin-receiver recess, and

controllably withdraws the retention pin from the pin-receiver recess.

23. The aircraft of claim 15, wherein the folding surface has a thickness of 3 inches or less.

24. The aircraft of claim 15, wherein the lock comprises:

an exterior locking spline and a compatible interior locking spline.