Active sail blade

Patent metadata

Field	Value
Publication number	US-11718396-B2
Application number	US-201916439487-A
Country	US
Kind code	B2
Filing date	Jun 12, 2019
Priority date	Jun 12, 2019
Publication date	Aug 8, 2023
Grant date	Aug 8, 2023

Abstract

Embodiments are directed to systems and methods for deploying an outboard rotor blade of proprotor pylon to act as an extended lifting surface. Blade control actuators may provide primary rotor flight control as well as providing fold linkage actuation when fold locks are disengaged. During cruise flight, the blade control actuator may provide feathering inputs to the extended rotor blade, wherein the amplitude and frequency of feathering inputs are tuned to mitigate undesirable wing and fuselage dynamic modes thereby enhancing aircraft stability. The deployed rotor blades also improve the total lifting area of the aircraft, which may increase aircraft range and efficiency.

First claim

What is claimed is:

1. An aircraft, comprising:
a fuselage;
a wing attached to the fuselage;
a proprotor assembly having a plurality of rotor blades and mounted on a first end of the wing;
a controller configured to, when the proprotor assembly is not rotating and the aircraft is in flight:
maintain, using a blade actuator, a first of the plurality of rotor blades in an extended position perpendicular to a direction of the flight;
adjust, using the blade actuator, a pitch of the first rotor blade to provide a flight control surface for controlling the direction of the flight of the aircraft, wherein the pitch is adjusted to the exclusion of the other rotor blades;
rotate, using one or more other actuators, the other rotor blades to a folded position parallel to the direction of the flight; and
decouple the other rotor blades from the other actuators so that the other rotor blades do not move while in the folded position.

2. The aircraft of claim 1 , wherein the blade actuator is configured to move the first rotor blade when the other rotor blades are in the folded position.

3. The aircraft of claim 2 , wherein the blade actuator operates to move the first rotor blade to dampen an undesired force acting on the aircraft.

4. The aircraft of claim 3 , wherein the undesired force comprises an aircraft vibration or wing flutter.

5. The aircraft of claim 1 , wherein the blade actuator is configured to move the first rotor blade in response to a flight control input from the controller.

6. The aircraft of claim 1 , wherein the first rotor blade is configured to operate as at least one of a primary flight control, a secondary flight control, or an augmented flight control when the other rotor blades are in the folded position.

7. The aircraft of claim 1 , wherein the first rotor blade is configured to generate a lifting force for the aircraft.

8. The aircraft of claim 1 , wherein the proprotor assembly is configured to move between a horizontal position and a vertical position during operation.

9. A tiltrotor aircraft, comprising:
a fuselage;
a wing attached to the fuselage;
a rotor system coupled to a first end of the wing and configured to move between a horizontal position and a vertical position during operation, the rotor system comprising a first rotor blade and one or more additional rotor blades, the rotor system operable to generate thrust when rotating; and
a controller configured to:
when the tiltrotor aircraft is in flight, maintain the first rotor blade in an extended position perpendicular to a direction of the flight;
rotate the additional rotor blades to a folded position parallel to the direction of the flight;
adjust, using an actuator, a pitch of the first rotor blade to provide a flight control surface for controlling the direction of the flight of the aircraft, wherein the pitch is adjusted to the exclusion of the other rotor blades; and
decouple the additional rotor blades from the actuator so that the additional rotor blades do not move while in the folded position.

10. The tiltrotor aircraft of claim 9 , wherein the first rotor blade is operable to provide a lift force on the aircraft while in the extended position.

11. The tiltrotor aircraft of claim 9 , wherein the controller is configured to move the first rotor blade to counter an undesired force acting on the aircraft.

12. The tiltrotor aircraft of claim 11 , wherein the undesired force comprises a vibration or flutter.

13. The tiltrotor aircraft of claim 9 , wherein the actuator is configured to move the first rotor blade in response to a flight control input from the controller.

14. The tiltrotor aircraft of claim 9 , further comprising:
a feedback loop computing unit in communication with a blade actuator, the feedback loop computing unit operable to control movement of the first rotor blade by the actuator.

15. The tiltrotor aircraft of claim 14 , further comprising:
at least one sensor coupled to the aircraft and in data communication with the feedback loop computing unit, the at least one sensor operable to detect at least one stability parameter of the aircraft.

16. The tiltrotor aircraft of claim 15 , wherein the feedback loop computing unit is operable to determine a frequency and a phase angle of a mode of the aircraft based on the at least one stability parameter.

17. The tiltrotor aircraft of claim 16 , wherein the feedback loop computing unit is operable to send a command to oscillate the first rotor blade at a dampening frequency having substantially the same frequency of the mode of the aircraft and having a different phase angle of the mode of the aircraft.

18. The tiltrotor aircraft of claim 9 , further comprising:
a second rotor system coupled to a second end of the wing and configured to move between a horizontal position and a vertical position during operation, the second rotor system comprising a first rotor blade and one or more additional rotor blades and operable to generate thrust when rotating; and
the first rotor blade on the second rotor system configured to remain in an extended position outboard of the wing when the additional rotor blades on the second rotor system rotated to a folded position during the flight.

19. The tiltrotor aircraft of claim 18 , further comprising:
a second wing attached to the fuselage;
a third and a fourth rotor system coupled to first and second ends of the second wing, the third and fourth rotor systems configured to move between a horizontal position and a vertical position during operation, the third and fourth rotor systems each comprising a plurality of rotor blades operable to generate thrust when rotating.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Foskey Christopher Edward
• Bosworth Jeffrey Mark

Classifications

• B64C29/0033 Primary

  the propellers being tiltable relative to the fuselage · CPC title

• B64C3/38

  Adjustment of complete wings or parts thereof · CPC title

• B64C11/18

  Aerodynamic features · CPC title

• B64C11/28

  Collapsible or foldable blades · CPC title

• B64C27/51

  Damping of blade movements · CPC title