Elastomeric transition for aircraft control surface
AssigneeNorthrop Grumman Corporation
InventorsJoseph B. Diller, Nicholas F. Miller, Jr.
Life of this patent
Estimating the term…
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.
Claims11
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.
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.
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.
Dependencies are inferred from the claim text.