Unmanned aerial vehicle drag augmentation by reverse propeller rotation

Patent metadata

Field	Value
Publication number	US-10955859-B2
Application number	US-201916728366-A
Country	US
Kind code	B2
Filing date	Dec 27, 2019
Priority date	Jan 14, 2011
Publication date	Mar 23, 2021
Grant date	Mar 23, 2021

Abstract

An air vehicle configured to augment effective drag to change the rate of descent of the air vehicle in flight via propeller shaft rotation direction reversal, i.e., thrust reversal.

First claim

What is claimed is:

1. A system comprising:
an autopilot configured to:
generate an input to effect a change in a descent angle of an air vehicle via direction of rotation reversal of at least one propeller having a constant pitch angle, wherein the generated descent angle input rotates the at least one propeller in a direction of rotation for generating forward air vehicle thrust; and
generate an input to effect a change in the trim of the air vehicle, wherein the generated trim input reduces an angle-of-attack of the air vehicle below an angle sufficient to maintain level flight such that a constant forward airspeed is maintained in descent and a stall condition is avoided.

2. The system of claim 1 , wherein the autopilot is further configured to regulate an airspeed value of the air vehicle by regulating the descent angle, wherein the descent angle comprises control of the at least one motor of the air vehicle and control of the trim of the air vehicle.

3. The system of claim 1 , wherein a motor driving the at least one propeller is an electrical motor configured to drive the at least one propeller in two angular directions.

4. The system of claim 1 , wherein the at least one propeller is at least one of: a forward-mounted tractor propeller and an aft-mounted pusher propeller.

5. The method of claim 1 , wherein the at least one propeller comprises two blades.

6. The method of claim 1 , wherein the at least one blade comprises a counterweight.

7. A system comprising:
an autopilot configured to:
generate an input to reverse a direction of rotation of at least one motor of an in-flight air vehicle, the at least one motor connected to at least one propeller comprising at least one blade having a constant pitch angle;
generate a downward bias to an acceleration command based on a detected airspeed of the in-flight air vehicle; and
generate an input to effect a change in the trim of the air vehicle, wherein the generated trim input reduces an angle-of-attack of the air vehicle below an angle sufficient to maintain level flight such that a constant forward airspeed is maintained in descent and a stall condition is avoided.

8. The system of claim 7 , wherein the autopilot is further configured to:
generate an input to set a rotation rate of the reversed propeller of the in-flight air vehicle to pin-wheel the at least one propeller.

9. The system of claim 7 , wherein the autopilot is further configured to:
generate an input to set a rotation rate of the reversed propeller of the in-flight air vehicle to free wheel the at least one propeller.

10. The system of claim 7 , wherein the generated input to reverse the direction of rotation of the at least one motor comprises a generated voltage of opposite polarity of an original voltage, wherein the at least one motor of the in-flight air vehicle is a brushless direct current (DC) motor.

11. The system of claim 7 , wherein the generated input to reverse the direction of rotation of the at least one motor comprises a generated reverse phase of an original phase, wherein the at least one motor of the in-flight air vehicle is an electrically commutated alternating current (AC) motor.

12. The system of claim 7 , wherein the autopilot is further configured to:
maintain one or more maneuver limits of the in-flight air vehicle.

13. The system of claim 7 , wherein the autopilot is further configured to:
maintain a limit below a threshold on at least one of: an acceleration command, a bias, and an error path of the in-flight air vehicle.

14. The system of claim 7 , wherein the autopilot is further configured to:
maintain a flight trim of the in-flight air vehicle proportional to a drag produced by reversing the direction of rotation of the at least one motor.

15. The system of claim 7 , wherein the reversed direction of rotation of the at least one motor increases the drag of the in-flight air vehicle.

16. The system of claim 7 , wherein the at least one propeller is at least one of:
a forward-mounted tractor propeller and an aft-mounted pusher propeller.

17. A method comprising:
reversing, by an autopilot, a propeller direction of rotation of at least one propeller while an air vehicle is in flight, wherein the at least one propeller comprises at least one blade having a constant pitch angle;
maintaining, by an autopilot, an airspeed of an air vehicle above stall conditions using a propeller motor while the air vehicle is in flight; and
generating, by the autopilot, an input to effect a change in the trim of the air vehicle, wherein the generated trim input reduces an angle-of-attack of the air vehicle below an angle sufficient to maintain level flight such that a constant forward airspeed is maintained in descent and a stall condition is avoided.

18. The method of claim 17 further comprising:
driving the propeller via a propeller shaft of the propeller motor, wherein the propeller motor is an electrical motor configured to drive the propeller shaft in either of two angular directions.

19. The method of claim 17 , wherein the at least one propeller is at least one forward-mounted tractor propeller.

20. The method of claim 17 wherein the at least one propeller is at least one aft-mounted pusher propeller.

Assignees

• Aerovironment Inc

Inventors

• Cowley Martyn
• Keennon Matthew Todd

Classifications

• B64U70/60

  Take-off or landing of UAVs from a runway using their own power · CPC title

• B64U2201/10

  autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS] · CPC title

• B64U50/19

  using electrically powered motors · CPC title

• B64U30/10

  Wings · CPC title

• B64U10/25

  Fixed-wing aircraft (VTOL aircraft B64U10/20) · CPC title