Aerodynamically actuated thrust vectoring devices
AssigneeUnited States of America as represented by the Administrator of NASA
InventorsPaul M. Rothhaar, William J. Fredericks, David D. North
Life of this patent
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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.
Claims12
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.
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.
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.
Dependencies are inferred from the claim text.