Vertical takeoff and landing aircraft

Patent metadata

Field	Value
Publication number	US-11124308-B2
Application number	US-201816042522-A
Country	US
Kind code	B2
Filing date	Jul 23, 2018
Priority date	Jul 21, 2017
Publication date	Sep 21, 2021
Grant date	Sep 21, 2021

Abstract

An aircraft includes a fuselage; a propulsion system including a power source and a vertical thrust propulsor driven by the power source; and a wing extending from the fuselage, the vertical thrust propulsor positioned on or at least partially within the wing, the wing including a diffusion assembly, the diffusion assembly including at least one diffusion member fixed in position and located downstream of the vertical thrust propulsor for diffusing an airflow from the vertical thrust propulsor.

First claim

What is claimed is:

1. An aircraft defining a vertical direction, the aircraft comprising:
a fuselage;
a propulsion system comprising a power source and a first vertical thrust propulsor driven by the power source; and
a wing extending from the fuselage, the first vertical thrust propulsor positioned on or at least partially within the wing, the wing comprising a diffusion assembly, the diffusion assembly comprising a first diffusion member having a first cross-sectional geometry in a longitudinal direction and a second diffusion member having a second cross-sectional geometry in the longitudinal direction, the first cross-sectional geometry being different from the second cross-sectional geometry, wherein the first diffusion member and the second diffusion member each fixed in position and located downstream of the first vertical thrust propulsor for diffusing an airflow from the first vertical thrust propulsor.

2. The aircraft of claim 1 , wherein the first diffusion member is configured as a forward diffusion member extending generally along a length of the wing at a forward edge of the first vertical thrust propulsor.

3. The aircraft of claim 2 , wherein the second diffusion member is configured as a central diffusion member extending approximately through an axis of the first vertical thrust propulsor.

4. The aircraft of claim 3 , wherein the propulsion system further comprises a second vertical thrust propulsor, wherein the forward diffusion member extends generally along the length of the wing at a forward edge of each of the first vertical thrust propulsor and the second vertical thrust propulsor, and wherein the second diffusion member extends generally along the length of the wing at a central axis of each of the first vertical thrust propulsor and the second vertical thrust propulsor.

5. The aircraft of claim 3 , wherein the propulsion system further comprises a second vertical thrust propulsor each configured as vertical thrust electric fans, wherein the wing defines a lengthwise direction and a widthwise direction perpendicular to the lengthwise direction, wherein the first vertical thrust propulsor and the second vertical thrust propulsor further comprises a separation diffusion member extending generally along the widthwise direction between the first and second vertical thrust electric fans.

6. The aircraft of claim 1 , wherein the wing defines a lengthwise direction and a widthwise direction perpendicular to the lengthwise direction, wherein the diffusion assembly further comprises a third diffusion member, the first diffusion member configured as a forward diffusion member, the second first diffusion member configured as a central diffusion member, and the third first diffusion member configured as an aft diffusion member along the widthwise direction.

7. The aircraft of claim 1 , wherein the first vertical thrust propulsor defines a fan diameter, wherein the first diffusion member defines a maximum height along the vertical direction, and wherein the maximum height of the first diffusion member is less than about 30 percent of the fan diameter.

8. The aircraft of claim 1 , wherein the diffusion assembly defines a diffusion area ratio greater than 1:1 and less than about 2:1.

9. The aircraft of claim 1 , wherein the diffusion assembly defines an inlet immediately downstream of the first vertical thrust propulsor having a substantially circular cross-sectional shape, and wherein the diffusion assembly further defines an outlet positioned downstream of the inlet and defining a substantially polygonal cross-sectional shape.

10. The aircraft of claim 1 , wherein the wing further comprises a variable geometry assembly extending along a length of the wing and moveable between a forward thrust position and a vertical thrust position, the variable geometry assembly at least partially covering the first vertical thrust propulsor and the first diffusion member when in the forward thrust position and at least partially exposing the first vertical thrust propulsor and the first diffusion member when in the vertical thrust position.

11. The aircraft of claim 10 , wherein the wing substantially completely encloses the first vertical thrust propulsor and the first diffusion member when the variable geometry assembly is in the forward thrust position and substantially completely exposes the first vertical thrust propulsor and the first diffusion member when the variable geometry assembly is in the vertical thrust position.

12. The aircraft of claim 1 , wherein the first vertical thrust propulsor is fixed in orientation for providing thrust generally along the vertical direction.

13. The aircraft of claim 1 , wherein the propulsion system further comprises a second vertical thrust propulsor, and wherein the first and second thrust propulsors are integrated into the wing and arranged substantially linearly along a length of the wing.

14. The aircraft of claim 1 , wherein the diffusion assembly defines an outlet positioned downstream of an inlet and defining a non-axisymmetric shape.

15. An aircraft defining a vertical direction, the aircraft comprising:
a fuselage;
a propulsion system comprising a power source and a plurality of vertical thrust propulsors driven by the power source, each of the plurality of vertical thrust propulsors including a respective fan; and
a wing extending from the fuselage, the plurality of vertical thrust propulsors arranged along a length of the wing, the wing comprising a diffusion assembly, the diffusion assembly comprising a plurality of diffusion members fixed in position and located downstream of at least one vertical thrust propulsor of the plurality of vertical thrust propulsors for diffusing an airflow from the at least one vertical thrust propulsor, wherein the plurality of diffusion members includes a first diffusion member having a first cross-sectional geometry in a longitudinal direction and a second diffusion member having a second cross-sectional geometry in the longitudinal direction, the first cross-sectional geometry being different from the second cross-sectional geometry.

16. The aircraft of claim 15 , wherein the first diffusion is configured as a forward diffusion member extending generally along the length of the wing at a forward edge of the at least one vertical thrust propulsor.

17. The aircraft of claim 15 , wherein the second diffusion is configured as an aft diffusion member extending generally along the length of the wing at an aft edge of the at least one vertical thrust propulsor.

18. The aircraft of claim 17 , wherein the first diffusion member extends generally along the length of the wing at a forward edge of each of the plurality of vertical thrust propulsors, and wherein the second diffusion member extends generally along the length of the wing at an aft edge of each of the plurality of vertical thrust propulsors.

19. The aircraft of claim 17 , wherein the wing defines a lengthwise direction and a widthwise direction perpendicular to the lengthwise direction, wherein the plurality of diffusion members further comprises a separation diffusion member extending generally along the widthwise direction between two adjacent vertical thrust propulsors of the plurality of vertical thrust propulsors.

20. A wing for an aircraft including a fuselage and a propulsion system and defining a vertical direction, the wing comprising:
a plurality of vertical thrust electric fans positioned at least partially within the wing and arranged along a length of the wing;
a variable geomet

Assignees

• Gen Electric

Inventors

• Murrow Kurt David
• Breeze-Stringfellow Andrew

Classifications

• B64D27/31

  within, or attached to, wings · CPC title

• B64D35/023

  of series-parallel type · CPC title

• B64D27/357

  using batteries · CPC title

• B64D27/33

  Hybrid electric aircraft · CPC title

• B64D27/406

  Suspension arrangements specially adapted for supporting thrust loads, e.g. thrust links · CPC title