Providing a load from a motor to inhibit further rotation of a propeller of an aerial vehicle while in flight

Patent metadata

Field	Value
Publication number	US-11560238-B2
Application number	US-202016874038-A
Country	US
Kind code	B2
Filing date	May 14, 2020
Priority date	Jan 24, 2020
Publication date	Jan 24, 2023
Grant date	Jan 24, 2023

Abstract

A technique for operating an aerial vehicle involves enabling a vertical takeoff and landing (VTOL) propeller of the aerial vehicle to rotate freely. The VTOL propeller is coupled with a VTOL motor (e.g., a 3-phase brushless DC motor). The technique further involves detecting when the VTOL propeller rotates to a predefined position relative to a direction of flight for the aerial vehicle (e.g., when blades of the VTOL propeller extend along an axis that is parallel to the direction of flight). The technique further involves, in response to detecting that the VTOL propeller has rotated to the predefined position, providing a load from the VTOL motor that inhibits further rotation of the VTOL propeller. Accordingly, while the aerial vehicle is in fixed wing horizontal flight, the controller is able to align the VTOL propeller in the direction of horizontal flight to minimize drag from the VTOL propeller.

First claim

What is claimed is:

1. An aerial vehicle with vertical takeoff and landing (VTOL) capabilities, the aerial vehicle comprising: a frame; a VTOL motor supported by the frame; a VTOL propeller coupled with the VTOL motor; and a controller supported by the frame, the controller being constructed and arranged to perform a method of: enabling the VTOL propeller coupled with the VTOL motor to rotate freely, detecting when the VTOL propeller coupled with the VTOL motor rotates to a predefined position relative to a direction of flight for the aerial vehicle, and in response to detecting that the VTOL propeller coupled with the VTOL motor has rotated to the predefined position, providing a load from the VTOL motor that inhibits further rotation of the VTOL propeller coupled with the VTOL motor; wherein the VTOL motor is a multi-phase electric motor having terminals to receive motor signals having different phases; wherein the terminals of the multi-phase electric motor are not connected to each other while enabling the VTOL propeller to rotate freely; and wherein the providing the load from the VTOL motor includes: connecting the terminals of the multi-phase electric motor together to provide the load from the VTOL motor that inhibits further rotation of the VTOL propeller.

2. An aerial vehicle as in claim 1 wherein the VTOL motor is among a plurality of VTOL motors which includes a first 3-phase brushless direct current (DC) motor that couples with a first VTOL propeller and a second 3-phase brushless DC motor that couples with a second VTOL propeller; and
wherein the controller is constructed and arranged to:
electrically connect the terminals of the first 3-phase brushless DC motor to each other in response to the first VTOL propeller aligning with the direction of flight for the aerial vehicle, and
electrically connect terminals of the second 3-phase brushless DC motor to each other in response to the second VTOL propeller aligning with the direction of flight for the aerial vehicle.

3. An aerial vehicle as in claim 2 wherein the VTOL motors includes a third 3-phase brushless DC motor that couples with a third VTOL propeller and a fourth 3-phase brushless DC motor that couples with a fourth VTOL propeller;
wherein the controller is constructed and arranged to:
electrically connect terminals of the third 3-phase brushless DC motor to each other in response to the third VTOL propeller aligning with the direction of flight for the aerial vehicle, and
electrically connect terminals of the fourth 3-phase brushless DC motor to each other in response to the fourth VTOL propeller aligning with the direction of flight for the aerial vehicle; and

wherein (i) the first and second 3-phase brushless DC motors are constructed and arranged to provide vertical lift to a left side of the aerial vehicle and (ii) the third and fourth 3-phase brushless DC motors are constructed and arranged to provide vertical lift to a right side of the aerial vehicle in a quadcopter configuration.

4. An aerial vehicle as in claim 1 wherein the control circuitry, when enabling a VTOL propeller coupled with a VTOL motor to rotate freely, is constructed and arranged to:
terminate delivery of electric power to the VTOL motor to allow the VTOL propeller to rotate freely.

5. An aerial vehicle as in claim 4 wherein the control circuitry, when detecting when a VTOL propeller coupled with a VTOL motor rotates to a predefined position relative to a direction of flight for the aerial vehicle, is constructed and arranged to:
sense when the VTOL propeller aligns with the direction of flight for the aerial vehicle.

6. An aerial vehicle as in claim 5 wherein each VTOL propeller includes a center axis, a first blade that extends outwardly from the center axis, and a second blade that extends outwardly from the center axis in a direction that is opposite that of the first blade; and
wherein the control circuitry, when sensing when a VTOL propeller aligns with the direction of flight for the aerial vehicle, is constructed and arranged to:
identify when the first and second blades of the VTOL propeller extend along an axis that is parallel to the direction of flight for the aerial vehicle.

7. An aerial vehicle as in claim 1 wherein the frame includes a fixed wing; and
wherein the aerial vehicle further comprises:
a set of horizontal propulsion devices supported by the frame, the set of horizontal propulsion devices being constructed and arranged to provide horizontal propulsion to the aerial vehicle enabling the fixed wing to generate lift for fixed wing flight.

8. An aerial vehicle as in claim 7 wherein the frame further includes:
a left beam that fastens to a left side of the fixed wing, the left beam supporting a first set of the VTOL motors, and
a right beam that fastens to a right side of the fixed wing, the right beam supporting a second set of the VTOL motors.

9. An aerial vehicle as in claim 7 wherein the set of horizontal propulsion devices includes:
a horizontal electric motor that is different from the VTOL motors, and
a horizontal flight propeller coupled with the horizontal electric motor, the horizontal flight propeller being different from the VTOL propellers.

10. An aerial vehicle as in claim 9 wherein the control circuitry is further constructed and arranged to:
operate the set of VTOL motors to execute vertical takeoff and landing maneuvers.

11. An aerial vehicle as in claim 9 wherein the control circuitry is further constructed and arranged to:
after executing a vertical takeoff maneuver and before executing a vertical landing maneuver, operate the horizontal electric motor to provide fixed wing horizontal flight while simultaneously providing loads from the set of VTOL motors to inhibit further rotation of the set of VTOL propellers.

12. A method of operating an aerial vehicle, comprising: enabling a vertical takeoff and landing (VTOL) propeller of the aerial vehicle to rotate freely, the VTOL propeller being coupled with a VTOL motor; detecting when the VTOL propeller rotates to a predefined position relative to a direction of flight for the aerial vehicle; and in response to detecting that the VTOL propeller has rotated to the predefined position, providing a load from the VTOL motor that inhibits further rotation of the VTOL propeller; wherein the VTOL motor is a multi-phase electric motor having terminals to receive motor signals having different phases; wherein the terminals of the multi-phase electric motor are not connected to each other while enabling the VTOL propeller to rotate freely; and wherein the providing the load from the VTOL motor includes: connecting the terminals of the multi-phase electric motor together to provide the load from the VTOL motor that inhibits further rotation of the VTOL propeller.

13. A method as in claim 12 wherein the multi-phase electric motor is a 3-phase brushless direct current (DC) motor having (i) a first set of windings and a first terminal leading to the first set of windings for a first phase, (ii) a second set of windings and a second terminal leading to the second set of windings for a second phase, and (iii) a third set of windings and a third terminal leading to the third set of windings for a third phase; and
wherein connecting the terminals of the multi-phase electric motor to each other includes:
electrically shorting the first terminal, the second terminal,
and the third terminal together through a node that is external to the 3-phase brushless DC motor.

14. A method as in claim 13 , further comprising:
while electrically shorting the first terminal, the second terminal, and the

Assignees

• Textron Systems Corp

Inventors

• Eppink James
• Vyas Surendra

Classifications

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64C11/00

  Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft · CPC title

• B64C2201/02

  Operations & Transport · mapped topic

• B64C39/024

  of the remote controlled vehicle type, i.e. RPV · CPC title

• B64D31/06

  actuated automatically · CPC title