Elastomeric transition for aircraft control surface

• US 6,145,791 A
• Filed: 01/09/1998
• Issued: 11/14/2000
• Est. Priority Date: 01/09/1998
• Status: Expired due to Fees

• Current Assignee: Northrop Grumman Corporation
• Original Assignee: Northrop Grumman Corporation
• Inventors: Miller, Nicholas F. Jr., Diller, Joseph B.
• Primary Examiner(s): Barefoot, Galen L.
• Application Number:
  US09/059,725
• Time in Patent Office: 1,040 Days
• Field of Search: 244/213-215, 244/219, 244/75 R, 244/130
• US Class Current: 244/215
• CPC Class Codes: B64C 3/48 by relatively-movable parts of wing structures
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof

Abstract

Elastomeric transition sections (118, 124) are mounted between the upper and lower portions of a wing (100) and a control surface (102) hinged thereto. The elastomeric transition sections include elastomeric material (126) having a plurality of holes (128) formed therethrough. Flexible rods (134, 136) are secured to either the wing or the control surface and extend through the holes (128) in the elastomeric material (126). The elastomeric transition sections provide a smooth aerodynamic transition between the wing and the control surface while permitting the control surface to pivot about the hinge axis (108) to perform the control function.

Claims

1. An aircraft wing assembly, comprising:

a main wing portion;

a control surface having a forward end, an inboard edge and an outboard edge, the forward end being attached to the main wing portion for movement of the control surface relative to the main wing portion; and

a single elastomeric transition section joining the main wing portion to the forward end, the inboard edge and the outboard edge of the control surface, for mitigating aerodynamic discontinuities occurring therebetween.

2. The aircraft wing assembly of claim 1 wherein:

the main wing portion has top and bottom portions;

the control surface has top and bottom portions; and

the elastomeric transition section joins the top portion of the main wing portion to the top portion of the control surface, and joins the bottom portion of the main wing portion to the bottom portion of the control surface.

3. The aircraft wing assembly of claim 2 wherein:

the elastomeric transition section has upper and lower elastomeric transition sections;

the upper elastomeric transition section joins the top portion of the main wing portion to the top portion of the control surface; and

the lower elastomer transition section joins the bottom portion of the main wing portion to the bottom portion of the control surface.

4. The aircraft wing assembly of claim,1 wherein the elastomeric transition section has a plurality of rods extending therethrough for structurally supporting the elastomeric transition section.

5. The aircraft wing assembly of claim 4 wherein selected ones of the rods are attached to the main wing portion.

6. The aircraft wing assembly of claim 4 wherein selected ones of the rods are attached to the control surface.

8. The aircraft wing assembly of claim 1 wherein the control surface further includes inboard and outboard edges, and the elastomeric transition section joins the top portion of the main wing portion to the top portion of the control surface at the inboard edge, and joins the bottom portion of the main wing portion to the bottom portion of the control surface at the inbord edge.

7. An aircraft wing assembly, comprising:

a main wing portion having top and bottom portions;

a control surface having top and bottom portions and a forward end, the forward end being attached to the main wing portion for movement of the control surface relative to the main wing portion; and

a single elastomeric transition section joins the top portion of the main wing portion to the top portion of the control surface at forward end, and joins the bottom portion of the main wing portion to the bottom top portion of the control surface at the forward end, for mitigating aerodynamic discontinuities occurring therebetween.

9. The aircraft wing assembly of claim 7 wherein the elastomeric transition section having a plurality of rods extending therethrough, for structurally supporting the elastomeric transition section.

10. The aircraft wing assembly of claim 9 wherein selected ones of the rods are attached to the main wing portion.

11. The aircraft wing assembly of claim 9 wherein selected ones of the rods are attached to the control surface.