Wing pivot structure

• US 5,337,974 A
• Filed: 04/15/1992
• Issued: 08/16/1994
• Est. Priority Date: 04/15/1992
• Status: Expired due to Term

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Steffier, Wayne S., Rumberger, William E.
• Primary Examiner(s): Peters, Jr., Joseph F.
• Assistant Examiner(s): Ellis, Christopher P.
• Application Number:
  US07/868,508
• Time in Patent Office: 853 Days
• Field of Search: 244/46, 244/39, 244/45 R, 244/49, 244/7 R, 244/7 A, 244/7 C, 244/2, 416/142, 416/143
• US Class Current: 244/49
• CPC Class Codes: B64C 3/40 Varying angle of sweep
• CPC Class Codes: B64C 3/56 Folding or collapsing to reduce overall dimensions of aircraft

Abstract

An aircraft wing pivot structure is described which provides a flexible ring attached to the aircraft wing at flexible wing attachment points by spherical bearings. The ring is attached to the fuselage of the aircraft by pins fixed to the fuselage and fittings partially enclosing sliding shoes formed at the bottom edge of the ring to allow rotation of the wing. The wing is locked in the flight position by retractable pins connected to the primary fuselage attachment fittings. The ring is a unitary stainless structure which accepts wing strains induced by flight loads by flexing at the wing attachment points. The use of a flexible ring eliminates truss-like members mounted on spherical bearings used in conventional designs. The elimination of a substantial number of components by the use of a flexible ring substantially reduces the weight of the aircraft and improves the reliability.

Claims

1. In an aircraft having a wing and a fuselage with a longitudinal axis, said wing being rotatable on a wing pivot device between a flight position with the wing span approximately orthogonal to the fuselage longitudinal axis and a stowed position with the wing span approximately parallel to the longitudinal axis of the fuselage, said wing pivot device comprising:

a pivot ring attached to said fuselage for rotation on said fuselage about a vertical axis;

at least one forward wing attachment member formed on the upper edge of said ring for attaching the leading portion of said wing to said ring;

at least one aft wing attachment member formed on the upper edge of said ring for attaching the trailing portion of said wing to said ring;

at least one forward primary fuselage attachment member formed on the lower edge of said ring for attaching the forward portion of said ring to the fuselage;

at least one aft primary fuselage attachment member formed on the lower edge of said ring for attaching the aft portion of said ring to the fuselage;

wing attachment assemblies connected to each of said wing attachment members for attaching said ring to said wing;

primary fuselage attachment assemblies fixed to said fuselage and connected in sliding engagement

with the lower edge of said ring, said primary attachment assemblies allowing said ring to rotate about a vertical axis of said fuselage;

removable locking means connected to said primary fuselage attachment assemblies for selectively locking said wing to the fuselage at the primary fuselage attachment members in the flight position; and

means for rotating said ring about a vertical axis.

2. The wing pivot device according to claim 1 wherein the ring is a unitary structure.

3. The wing pivot device according to claim 2 wherein said ring is a metallic unitary structure.

4. The wing pivot device according to claim 3 wherein said ring is stainless steel.

5. The wing pivot device according to claim 2 wherein each of said wing attachment members is vertically aligned with one of said primary fuselage attachment members and is connected to the fuselage attachment member by a radially flexible column.

6. The wing pivot device according to claim 5 wherein said ring is connected to said wing and said fuselage by means of spherical bearings.

7. The wing pivot device according to claim 5 and further comprising:

a slider member formed along the lower edge of said ring, said slider portion being a widened portion of said ring and extending from the inside and outside peripheral surfaces of said ring;

shoe portions formed at the upper edge of said primary fuselage attachment assemblies, said shoe partially enclosing the upper surface of said ring slider member for allowing sliding rotation of said ring on said fuselage.

8. The wing point device according to claim 7 and further comprising a plurality of secondary fuselage attachment assemblies attached to said fuselage and arranged around the perimeter of said ring between said primary fuselage attachment points.

9. The wing attachment device according to claim 8 wherein each of said secondary fuselage pivot points includes a shoe portion at its upper edge, said shoe portion partially enclosing the upper surface of said ring slider member for allowing sliding rotation of said ring on said fuselage.

10. The wing pivot device according to claim 9 wherein two forward wing attachment members are provided and two aft wing attachment members are provided on said ring, said forward and aft wing attachment members being approximately equally spaced around the perimeter of the upper edge of the ring.

11. In an aircraft having a wing and a fuselage with a longitudinal axis, said wing being rotatable between a flight position with the wing span approximately orthogonal to the axis of said fuselage and a stowed position with the wing span approximately parallel to the axis of the fuselage, said wing pivot device comprising:

a pivot ring attached to said wing at two forward points and two aft points on said wing at wing attachment points on the upper edge of said ring;

a fuselage attachment slider formed on the lower surface of said ring, said slider forming a widened portion of said ring and extending from the inside and outside surfaces of the ring;

four primary fuselage attachment points on the lower edge of said ring, each of said fuselage attachment points being vertically aligned with one of said wing attachment points on the upper edge of said ring;

four primary fuselage attachment assemblies fixed to the fuselage and aligned with the fuselage attachment points of the ring when the ring is in the flight position, said fuselage attachment assemblies being in sliding engagement with the fuselage attachment slider to allow rotational sliding of the ring with respect to the fuselage;

a primary attachment pin located in each of said fuselage attachment assemblies for locking said ring in the flight position through the fuselage attachment points of the ring;

means for removing the primary attachment pins from engagement with the fuselage attachment points of the ring to allow rotation of the wing to the stowed position; and

means for rotating the wing from the flight position to the stowed position.

12. The wing pivot device according to claim 11 and further comprising a columnar member connecting each wing attachment point to a corresponding fuselage attachment point, said columnar member being stiff in tension, compression and torsion and soft in restraint in a direction radial from the center of the ring.

13. The wing pivot device according to claim 12 and further comprising a plurality of secondary fuselage attachment assemblies, each secondary fuselage attachment assembly comprising a shoe which partially encloses the fuselage attachment slider in slidable engagement to allow the wing to rotate with respect to the fuselage.

14. The wing pivot device according to claim 13 and further comprising a spherical bearing in each of the wing attachment points and fuselage attachment points to provide angular movement between the attachment points and their respective attachment assemblies.

15. The wing pivot device according to claim 14 wherein said ring is a unitary structure.

16. The wing pivot device according to claim 15 wherein said ring is a metallic unitary structure.

17. The wing pivot device according to claim 16 wherein said ring is stainless steel.