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US 7,322,547 B2Granted
Aerospace vehicle leading edge slat devices and corresponding methods
AssigneeThe Boeing Company
InventorChristopher A. Konings
Life of this patent
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Abstract
Aerospace vehicle leading edge slat devices and corresponding methods are generally disclosed herein. One aspect of the invention is directed toward an aerospace vehicle system that includes an airfoil having a leading edge. The system further includes a first flow body fixedly coupled to the airfoil to form at least one gap between the leading edge of the airfoil and the first flow body. A second flow body can be coupled to the airfoil and can be movable between at least a retracted position where the second flow body is positioned to at least approximately aerodynamically seal the at least one gap, and an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.
Claims25
An aerospace vehicle system, comprising:
- an airfoil having a leading edge;
- a first flow body fixedly coupled to the airfoil to form at least one gap between the leading edge of the airfoil and the first flow body;
- and
- a second flow body having a recess, an upper trailing edge, and a lower trailing edge, the second flow body being movably coupled to the airfoil to move between:
- a retracted position wherein the second flow body is positioned to at least approximately aerodynamically seal the at least one gap, and wherein the first flow body is located in the recess, the upper trailing edge is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil, and the lower trailing edge is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil;
- and
- an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.
4 more elements
An aerospace vehicle system, comprising:
- an airfoil having a leading edge;
- a first flow body fixedly coupled to the airfoil to form a first gap between the leading edge of the airfoil and the first flow body;
- a second flow body movably coupled to the airfoil;
- and
- a third flow body fixedly coupled to the leading edge of the airfoil, the third flow body positioned to form a second gap between the first flow body and the third flow body, wherein the second flow body is movable between:
- a retracted position where the second flow body is positioned to at least approximately aerodynamically seal the first gap and the second gap;
- and
- an extended position where the second flow body is positioned to allow fluid flow through at least one of the first gap and the second gap.
5 more elements
A method for making an aerospace vehicle system, comprising:
- fixedly coupling a first flow body to an airfoil to form at least one gap between the first flow body and a leading edge of the airfoil;
- and
- movably coupling a second flow body to the airfoil, the second flow body having a recess, an upper trailing edge, and a lower trailing edge, the second flow body being movable between:
- a retracted position wherein the second flow body at least approximately aerodynamically seals the at least one gap, and wherein the first flow body is located in the recess, the upper trailing edge is positioned proximate to the leading edae of the airfoil to at least approximately aerodynamically seal with the airfoil, and the lower trailing edge is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil;
- and
- an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.
3 more elements
A method for making an aerospace vehicle system, comprising:
- fixedly coupling a first flow body to an airfoil to form a first gap between the first flow body and a leading edge of the airfoil;
- movably coupling a second flow body to the airfoil;
- fixedly coupling a third flow body to the leading edge of the airfoil, the third flow body positioned to form a second gap between the first flow body and the third flow body, wherein the second flow body is movable between:
- a retracted position where the second flow body at least approximately aerodynamically seals the first gap and the second gap;
- and
- an extended position where the second flow body is positioned to allow fluid flow through at least one of the first gap and the second gap.
3 more elements
A method for configuring an aerospace vehicle system, comprising:
- removing at least a portion of a pre-existing leading edge device from an airfoil;
- fixedly coupling a first flow body to the airfoil to form at least one gap between the first flow body and a leading edge of the airfoil;
- and
- coupling a second flow body to the airfoil to be movable between:
- a retracted position where the second flow body at least approximately aerodynamically seals the at least one gap;
- and
- an extended position where the second flow body is positioned to allow fluid flow through the at least one gap.
4 more elements
A method for configuring an aerospace vehicle for various phases of flight comprising:
- positioning a leading edge device in a retracted position wherein:
- a second flow body of the leading edge device at least approximately aerodynamically seals a gap between a portion of a first flow body of the leading edge device and a portion of a leading edge of an airfoil, wherein the first flow body is fixedly coupled to the leading edge of the airfoil;
- and
- the first flow body is located in a recess of the second flow body, an upper trailing edge of the second flow body is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil, and a lower trailing edge of the second flow body is positioned proximate to the leading edge of the airfoil to at least approximately aerodynamically seal with the airfoil;
- and
- positioning the leading edge device in an extended position wherein the second flow body of the leading edge device is positioned to allow fluid flow through the gap.
3 more elements
An aerospace vehicle system, comprising:
- an airfoil having a leading edge and a spanwise section;
- a first flow body movably coupled to the airfoil;
- and
- a second flow body movably coupled to the airfoil, the second flow body having a recess, an upper trailing edge, and a lower trailing edge, the first flow body and the second flow body being movable between:
- a retracted position where the first flow body is located in the recess, the upper trailing edae of the second flow body is proximate to and at least approximately aerodynamically sealed with the leading edge of the airfoil above the first flow body across the spanwise section, and the lower trailing edge of the second flow body is proximate to and at least approximately aerodynamically sealed with the leading edge of the airfoil below the first flow body across the spanwise section;
- and
- an extended position where the first flow body and the second flow body are positioned to interact with a fluid flow.
4 more elements
Dependencies are inferred from the claim text.