Six degree of freedom aerial vehicle having reconfigurable propellers

Patent metadata

Field	Value
Publication number	US-11249477-B2
Application number	US-201816133592-A
Country	US
Kind code	B2
Filing date	Sep 17, 2018
Priority date	Sep 17, 2018
Publication date	Feb 15, 2022
Grant date	Feb 15, 2022

Abstract

Various reconfigurations of propellers, propeller blades, and/or blade sections of propulsion mechanisms of an aerial vehicle are described. For example, responsive to a fault or failure of a propulsion mechanism, propellers, propeller blades, and/or blade sections of the remaining propulsion mechanisms may be modified to maintain control and safety of the aerial vehicle. In example embodiments, angular orientations, positions, and/or lengths of one or more propellers, propeller blades, and/or blade sections of propulsion mechanisms may be modified to maintain control and safety in either a horizontal, wingborn flight orientation, or a vertical, VTOL flight orientation.

First claim

What is claimed is:

1. An aerial vehicle, comprising:
a fuselage;
six motor arms coupled to and extending from the fuselage;
six motors, each motor coupled to a respective motor arm and positioned around the fuselage;
six propellers, each propeller coupled to and rotated by a respective motor;
a ring wing coupled to outer ends of the six motor arms and positioned around the fuselage, the six motors, and the six propellers; and
six actuators, each actuator coupled to a respective propeller and configured to alter at least one of an orientation or a length of at least one blade of the respective propeller.

2. The aerial vehicle of claim 1 , wherein angles of the six propellers are configured to be altered relative to at least one of the fuselage, the six motor arms, or the six motors.

3. The aerial vehicle of claim 1 , wherein angles of at least a portion of the at least one blade of the six propellers are configured to be altered relative to roots of the at least one blade of the six propellers.

4. The aerial vehicle of claim 1 , wherein lengths of the at least one blade of the six propellers are configured to be altered.

5. The aerial vehicle of claim 1 , further comprising:
a controller configured to at least:
detect a failure of a first propeller of the six propellers;
responsive to the detected failure, actuate at least one actuator of the six actuators to alter at least one of the orientation or the length of the at least one blade of the respective propeller;
identify a safe landing location for the aerial vehicle; and
navigate the aerial vehicle to the safe landing location.

6. An aerial vehicle, comprising:
a fuselage;
a plurality of propulsion mechanism arms coupled to and extending from the fuselage;
a plurality of propulsion mechanisms, each propulsion mechanism coupled to a respective propulsion mechanism arm and positioned around the fuselage;
a plurality of propellers, each propeller coupled to and rotated by a respective propulsion mechanism;
a ring wing coupled to outer ends of the plurality of propulsion mechanism arms and positioned around the fuselage and the plurality of propulsion mechanisms; and
a first actuator coupled to a first propeller and configured to alter at least one of an orientation or a length of at least one blade of the first propeller.

7. The aerial vehicle of claim 6 , wherein the first actuator is configured to alter an angle of the first propeller relative to a first propulsion mechanism to which the first propeller is coupled.

8. The aerial vehicle of claim 6 , wherein the first actuator is configured to alter at least one of an angle or a position of at least a portion of the at least one blade of the first propeller.

9. The aerial vehicle of claim 8 , wherein the at least a portion of the at least one blade comprises at least one of a control surface or a trim tab of the at least one blade.

10. The aerial vehicle of claim 8 , wherein the at least a portion of the at least one blade comprises a tip section of the at least one blade.

11. The aerial vehicle of claim 10 , wherein the first actuator is configured to alter the angle of the tip section of the at least one blade at least one of: upward outside a plane of rotation of the first propeller, downward outside the plane of rotation of the first propeller, forward inside the plane of rotation of the first propeller, or rearward inside the plane of rotation of the first propeller.

12. The aerial vehicle of claim 10 , wherein the first actuator is configured to alter the position of the tip section of the at least one blade radially outward or radially inward inside a plane of rotation of the first propeller.

13. The aerial vehicle of claim 10 , wherein the first actuator comprises at least one of a tunable bias element or a magnetic actuator configured to alter a springiness of at least a portion of a coupling between the tip section of the at least one blade and a root of the at least one blade.

14. The aerial vehicle of claim 13 , wherein at least one of a pitch or the orientation of the at least one blade of the first propeller is configured to be altered by the first actuator based at least in part on a thrust generated by the first propulsion mechanism.

15. The aerial vehicle of claim 6 , wherein the first actuator comprises at least one of a clutch, a switch, a bias element, a servo, a solenoid, a motor, a screw actuator, a magnetic actuator, a linear actuator, or a rotary actuator.

16. The aerial vehicle of claim 6 , further comprising:
a controller configured to at least:
detect a failure of a second propulsion mechanism of the plurality of propulsion mechanisms;
responsive to the detected failure, actuate the first actuator to alter at least one of the orientation or the length of the at least one blade of the first propeller;
identify a safe landing location for the aerial vehicle; and
navigate the aerial vehicle to the safe landing location.

17. The aerial vehicle of claim 6 , further comprising:
a plurality of actuators, each actuator coupled to a respective propeller and configured to alter at least one of an orientation or a length of at least one blade of the respective propeller;
wherein the plurality of actuators comprise the first actuator.

Assignees

• Amazon Tech Inc

Inventors

• Legrand Louis
• Rand Omri
• Kimchi Gur
• Fischer Sebastian
• Welsh Ricky

Classifications

• B64U30/297

  Tilting rotors · CPC title

• B64U10/16

  with five or more distinct rotor axes, e.g. octocopters · CPC title

• B64U30/26

  Ducted or shrouded rotors · CPC title

• G05D1/0072 Primary

  to counteract a motor failure · CPC title

• B64C39/08

  having multiple wings · CPC title