Rapid flap deflection for high lift transients

Patent metadata

Field	Value
Publication number	US-11613344-B2
Application number	US-202117189363-A
Country	US
Kind code	B2
Filing date	Mar 2, 2021
Priority date	May 8, 2017
Publication date	Mar 28, 2023
Grant date	Mar 28, 2023

Abstract

A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.

First claim

What is claimed is:

1. A wing configured to produce lift in a fluid medium flow, said wing comprising:
a fore-element comprising a fore-element leading edge and a fore-element trailing edge;
an aft-element comprising an aft-element leading edge pivotably connected in a span-wise direction to said fore-element trailing edge, and said aft-element comprising an aft-element trailing edge;
a pivotable linkage operatively connecting said aft-element leading edge to said fore-element trailing edge; and
an actuator configured to deflect said aft-element through a predetermined deflection angle about said pivotable linkage relative to said fore-element within a predetermined time less than or equal to two convective periods, wherein one convective period corresponds to a time it takes for said fluid medium to flow from said fore-element leading edge to said aft-element trailing edge, wherein said predetermined time is less than or equal to one convective period, wherein the predetermined deflection angle is greater than 10 degrees.

2. The wing of claim 1 , wherein a chord length of said aft-element is greater than 20% of a chord length of said wing,
wherein said chord length of said wing extends from said fore-element leading edge to said aft-element trailing edge, and
wherein said chord length of said aft-element extends from said aft-element leading edge to said aft-element trailing edge.

3. The wing of claim 2 , wherein said chord length of said wing is longer after deflection of said aft-element through said predetermined deflection angle about said pivotable linkage relative to said fore-element than before deflection.

4. The wing of claim 2 , wherein said chord length of said wing is shorter after deflection of said aft-element through said predetermined deflection angle about said pivotable linkage relative to said fore-element than before deflection.

5. The wing of claim 1 , wherein said wing is one of an airfoil and a hydrofoil.

6. The wing of claim 1 , wherein said fore-element leading edge further comprises a deflectable leading-edge flap configured to deflect through a predetermined leading-edge deflection angle relative to said fore-element within a leading-edge predetermined time less than or equal to two convective periods.

Assignees

• Us Gov Air Force
• Us Air Force

Inventors

• Ol Michael V
• Medina Alberto

Classifications

• Y02T50/10

  Drag reduction · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B63B1/28

  with movable hydrofoils · CPC title

• B64C3/48

  by relatively-movable parts of wing structures · CPC title

• B64C9/16

  at the rear of the wing · CPC title