Aerodynamically actuated thrust vectoring devices

Patent metadata

Field	Value
Publication number	US-10370100-B2
Application number	US-201615077268-A
Country	US
Kind code	B2
Filing date	Mar 22, 2016
Priority date	Mar 24, 2015
Publication date	Aug 6, 2019
Grant date	Aug 6, 2019

Abstract

A vehicle includes a wing and a control surface pivotably coupled to the wing and configured to pivot about a range of motion. A propulsor is coupled to the control surface and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode. The propulsor is aerodynamically actuated between the first position and the second position due to aerodynamics about the wing. The propulsor may rotate from an initial flight mode, such as a takeoff mode, to a second flight mode, such as a forward flight mode.

First claim

What is claimed is:

1. A vehicle comprising:
a wing;
a control surface pivotably coupled to the wing and configured to pivot about a range of motion; and
a propulsor coupled to the control surface and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode,
wherein the propulsor is aerodynamically actuated between the first position and the second position due to aerodynamics about the wing.

2. The vehicle of claim 1 , further comprising a connecting member connecting the propulsor to the control surface such that movement of the control surface about the range of motion produces rotation of the propulsor.

3. The vehicle of claim 2 , Wherein the connecting member is coupled to the control surface at a first end and coupled to the propulsor at a second end, and wherein the connecting member is coupled to the wing at a pivot point at a location of the connecting member between the first end and the second end.

4. The vehicle of claim 3 , wherein the pivot point is located aft of a center of gravity of the wing and forward of an aerodynamic center of the wing.

5. The vehicle of claim 3 , wherein the pivot point is positioned at a chord length location of the wing based on a weight of the propulsor and a weight the control surface and a length of the connecting member.

6. The vehicle of claim 5 , wherein a portion of the connecting member forward of the pivot point is configured to lie flush with an upper surface of the wing and wherein the wing comprises a notch sized to fit a portion of the connecting member aft of the pivot point.

7. The vehicle of claim 2 , wherein the control surface is a trailing edge flap.

8. A vehicle comprising:
a vehicle body;
a tilting body configured to move through a range of motion relative to the vehicle body; and
a series of propulsors coupled to the vehicle body and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode,
wherein the series of propulsors are configured to aerodynamically actuate through the range of motion along with the tilting body due to aerodynamics about the tilting body to change between the first position and the second position.

9. The vehicle of claim 8 , further comprising:
a tail including a tail control surface configured to tilt through a range of motion relative to the tail and a series of tail propulsors coupled to the tail and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode,
wherein the series of tail propulsors are configured to aerodynamically actuate through the range of motion along with the tail due to aerodynamics about the tail to change between the first position and the second position.

10. The vehicle of claim 8 , wherein the series of propulsors are configured to be positioned in the first position prior to takeoff due to weights of the tilting body and the series of propulsors.

11. The vehicle of claim 8 , wherein the series of propulsors are configured to be positioned in the second position during forward flight due to lifting forces acting on the tilting body.

12. A thrust vectoring device comprising:
a control surface configured to pivot about a range of motion; and
a propulsor coupled to the control surface and configured to rotate between a first position associated with a hover flight mode and a second position associated with a forward flight mode,
wherein the propulsor is aerodynamically actuated between the first position and the second position due to aerodynamic conditions about the control surface.

Assignees

• Nasa

Inventors

• Rothhaar Paul M
• Fredericks William J
• North David D

Classifications

• Y02T50/44

  Cross-Sectional Technologies · mapped topic

• Y02T50/32

  Cross-Sectional Technologies · mapped topic

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C9/04

  with compound dependent movements · CPC title

• Y02T50/40

  Weight reduction · CPC title