Wing for an aircraft, and an aircraft comprising such a wing
US-9988142-B2 · Jun 5, 2018 · US
Split winglet
US10625847B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-10625847-B2 |
| Application number | US-201715494071-A |
| Country | US |
| Kind code | B2 |
| Filing date | Apr 21, 2017 |
| Priority date | Apr 21, 2017 |
| Publication date | Apr 21, 2020 |
| Grant date | Apr 21, 2020 |
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- Title
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- Abstract
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- First independent claim
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Abstract
Official abstract text for this publication.
A split winglet has a leading airfoil (LA) comprising a LA leading edge, a LA trailing edge, a LA upper surface, and a LA lower surface. The split winglet also has a trailing airfoil (TA) comprising a TA leading edge, a TA trailing edge, a TA upper surface, and a TA lower surface. The split winglet further has a base connected to each of the LA and the TA, the base being configured for connection to a tip of a main airfoil.
First claim
Opening claim text (preview).
What is claimed is: 1. A split winglet, comprising: a leading airfoil (LA) comprising a LA leading edge, a LA trailing edge, a LA upper surface, a LA lower surface, and a LA tip; a trailing airfoil (TA) comprising a TA leading edge, a TA trailing edge, a TA upper surface, a TA lower surface, and a TA tip; and a base connected to each of the LA and the TA, the base being configured for connection to a tip of a main airfoil; wherein the LA tip and the TA tip extend to substantially a same vertical height. 2. The split winglet of claim 1 , wherein the LA trailing edge is located upstream relative to the TA leading edge. 3. The split winglet of claim 1 , wherein a gap exists between the LA and the TA when the split winglet is viewed from above or below. 4. The split winglet of claim 1 , wherein a gap exists between the LA lower surface and the TA upper surface when the split winglet is viewed from the front or back. 5. The split winglet of claim 1 , wherein the LA comprises a substantially straight LA section and the TA comprises a substantially straight TA section. 6. The split winglet of claim 5 , wherein the straight LA section is located inboard relative to the straight TA section. 7. The split winglet of claim 5 , wherein the straight LA section is joined to the base by a curved LA section. 8. The split winglet of claim 7 , wherein the straight TA section is joined to the base by a curved TA section. 9. The split winglet of claim 1 , wherein the main airfoil comprises a main rotor blade of a helicopter. 10. The split winglet of claim 1 , wherein the main airfoil comprises a wing of a fixed wing aircraft. 11. A helicopter, comprising: a main rotor system comprising a main rotor blade comprising and outboard end; and a split winglet attached to the outboard end, the split winglet comprising: a leading airfoil (LA) comprising a LA leading edge, a LA trailing edge, a LA upper surface, a LA lower surface, and a LA tip; a trailing airfoil (TA) comprising a TA leading edge, a TA trailing edge, a TA upper surface, a TA lower surface, and a TA tip; and a base connected to each of the LA and the TA, the base being configured for connection to a tip of a main airfoil; wherein the LA tip and the TA tip extend to substantially a same vertical height. 12. The helicopter of claim 11 , wherein the LA trailing edge is located upstream relative to the TA leading edge. 13. The helicopter of claim 11 , wherein a gap exists between the LA and the TA when the split winglet is viewed from above or below. 14. The helicopter of claim 11 , wherein a gap exists between the LA lower surface and the TA upper surface when the split winglet is viewed from the front or back. 15. The helicopter of claim 11 , wherein the LA comprises a substantially straight LA section and the TA comprises a substantially straight TA section. 16. The helicopter of claim 15 , wherein the straight LA section is located inboard relative to the straight TA section. 17. The helicopter of claim 15 , wherein the straight LA section is joined to the base by a curved LA section. 18. The helicopter of claim 17 , wherein the straight TA section is joined to the base by a curved TA section.
Assignees
Inventors
Classifications
- B64C23/069Primary
using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips · CPC title
at the wing tips · CPC title
Blade tips · CPC title
Aerodynamic features · CPC title
Drag reduction · CPC title
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Frequently asked questions
Answers are generated from the same data shown on this page.
- What does patent US10625847B2 cover?
- A split winglet has a leading airfoil (LA) comprising a LA leading edge, a LA trailing edge, a LA upper surface, and a LA lower surface. The split winglet also has a trailing airfoil (TA) comprising a TA leading edge, a TA trailing edge, a TA upper surface, and a TA lower surface. The split winglet further has a base connected to each of the LA and the TA, the base being configured for connecti…
- Who is the assignee on this patent?
- Bell Helicopter Textron Inc, Textron Innovations Inc
- What technology area does this patent fall under?
- Primary CPC classification B64C23/069. Mapped technology areas include Operations & Transport.
- When was this patent published?
- Publication date Tue Apr 21 2020 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 3 related publications on this page (citations in our corpus or others sharing the same primary CPC).