Redundant aircraft propulsion system using multiple motors per drive shaft

Patent metadata

Field	Value
Publication number	US-10086933-B2
Application number	US-201514973618-A
Country	US
Kind code	B2
Filing date	Dec 17, 2015
Priority date	Dec 17, 2015
Publication date	Oct 2, 2018
Grant date	Oct 2, 2018

Abstract

Multiple motors may drive (rotate) a single shaft coupled to a propeller. The motors may be selected such that a first motor is capable of rotating the drive shaft in an event of a failure of a second motor coupled to the drive shaft. A one-way clutch bearing, or similar device, may interface between a motor and the drive shaft to enable free rotation of the drive shaft in an event of the motor becoming inoperable, such as the motor freezing or locking in a position due to failure caused by overheating or caused by other conditions or events. Use of the second motor may secure a position of the drive shaft which may support the propeller in radial eccentric loading.

First claim

What is claimed is:

1. A redundant propeller drive system comprising:
a frame;
a propeller;
a drive shaft coupled to the propeller, the drive shaft having a first portion located proximate to a first side of the propeller and a second portion located proximate to a second side of the propeller;
a first motor axially aligned with the drive shaft and coupled to the frame;
a first one-way clutch bearing that includes a first cylinder coupled to the first portion of the drive shaft and second cylinder coupled to the first motor, the first one-way clutch bearing configured to prevent rotation of the first cylinder in a first direction with respect to the second cylinder to transfer a rotational force from the first motor onto the drive shaft, the first one-way clutch bearing configured to allow rotation of the first cylinder in a second direction with respect to the second cylinder;
a second motor axially aligned with the drive shaft and coupled to the frame; and
a second one-way clutch bearing that includes a third cylinder coupled to the second portion of the drive shaft and fourth cylinder coupled to the second motor, the second one-way clutch bearing configured to prevent rotation of the third cylinder in the first direction with respect to the fourth cylinder to transfer a rotational force from the second motor onto the drive shaft, the second one-way clutch bearing configured to allow rotation of the third cylinder in the second direction with respect to the fourth cylinder,
wherein, in an event of failure of the first motor, the second motor drives the drive shaft while the first one-way clutch bearing allows rotation of the first cylinder in the second direction with respect to the second cylinder, and
wherein, in an event of failure of the second motor, the first motor drives the drive shaft while the second one-way clutch bearing allows rotation of the third cylinder in the second direction with respect to the fourth cylinder.

2. The redundant propeller drive system as recited in claim 1 , wherein the first cylinder is coupled to the first portion proximate to a first end of the drive shaft and the third cylinder is coupled to the second portion proximate to a second end of the drive shaft, and wherein the first cylinder and the third cylinder secure the drive shaft with respect to the frame.

3. The redundant propeller drive system as recited in claim 1 , wherein the propeller is a first propeller, and further comprising:
a second propeller coupled to the drive shaft;
a first tip connector to couple a first tip of the first propeller to a first tip of the second propeller; and
a second tip connector to couple a second tip of the first propeller to a second tip of the second propeller.

4. The redundant propeller drive system as recited in claim 1 , wherein:
the first motor is configured to operate up to a threshold number of revolutions per minute to support continuous flight of an aircraft and operate at a first maximum threshold torque that is less than a threshold torque required to support the continuous flight of the aircraft,
the second motor is configured to operate up to the threshold number of revolutions per minute to support the continuous flight of the aircraft and operate at a second maximum threshold torque that is less than the threshold torque required to support the continuous flight of the aircraft, and
the first motor and the second motor, during simultaneous operation, generate a third maximum torque that is greater than the threshold torque required to support the continuous flight of the aircraft.

5. The redundant propeller drive system as recited in claim 1 , wherein the propeller is a first propeller, and further comprising:
a second propeller coupled to the drive shaft, and
wherein the first motor, the second motor, or both are located between the first propeller and the second propeller.

6. An apparatus comprising:
a propeller;
a drive shaft coupled to the propeller;
a first one-way clutch bearing to cause rotation of the drive shaft while rotating in a first direction;
a first motor coupled to the drive shaft and to the first one-way clutch bearing; and
a second one-way clutch bearing to cause rotation of the drive shaft while rotating in the first direction;
a second motor coupled to the drive shaft and to the second one-way clutch bearing,
wherein power output from the first motor, the second motor, or both cause rotation of the drive shaft and the propeller, and
wherein the first one-way clutch bearing allows the rotation of the drive shaft in an event of failure of the first motor while the second motor is in operation, and the second one-way clutch bearing allows the rotation of the drive shaft in an event of failure of the second motor while the first motor is in operation.

7. The apparatus as recited in claim 6 , wherein the drive shaft includes a first portion that extends outward from a first side of the propeller and a second portion that extends outward from a second side of the propeller, and wherein the first motor is coupled to the first portion of the drive shaft and the second motor is coupled to the second portion of the drive shaft.

8. The apparatus as recited in claim 7 , wherein the drive shaft rotates about an axis, the first motor is coupled to the first portion proximate to a first end of the drive shaft and the second motor is coupled to the second portion proximate to a second end of the drive shaft, and the first motor and the second securing the drive shaft along the axis.

9. The apparatus as recited in claim 6 , wherein the drive shaft includes a first portion that extends outward from a first side of the propeller, and wherein the first motor and the second motor are coupled to the first portion of the drive shaft.

10. The apparatus as recited in claim 6 , wherein:
the drive shaft includes a first portion that extends outward from a first side of the propeller and a second portion that extends outward from a second side of the propeller,
the first one-way clutch bearing is coupled to the first portion proximate to a first end of the drive shaft and the second one-way clutch bearing is coupled to the second portion proximate to a second end of the drive shaft, and
the first one-way clutch bearing and the second one-way clutch bearing securing a location of the drive shaft.

11. The apparatus as recited in claim 6 , further comprising:
a first cogwheel coupled to the first motor;
a second cogwheel coupled to the second motor; and
a third cogwheel coupled to the drive shaft,
wherein the first cogwheel and second cogwheel engage the third cogwheel to enable the first motor, the second motor, or both to drive rotation of the drive shaft.

12. The apparatus as recited in claim 11 , wherein at least one of the first cogwheel or the second cogwheel has a different number of cogs than the third cogwheel.

13. The apparatus as recited in claim 6 , wherein the propeller is a first propeller, and further comprising:
a second propeller coupled to the drive shaft;
a first tip connector to couple a first tip of the first propeller to a first tip of the second propeller; and
a second tip connector to couple a second tip of the first propeller to a second tip of the second propeller.

14. The apparatus as recited in claim 13 , wherein the first motor, the second motor, or both are located between the first propeller and the second propeller.

15. An unmanned aerial vehicle (UAV) comprising:
a frame;
a power source coupled to the frame; and
a plurality of propulsion units coupled to the frame and connected to the power source, whe

Assignees

• Amazon Tech Inc

Inventors

• Roberts Nicholas Hampel
• Shiosaki Dominic Timothy
• Welsh Ricky Dean

Classifications

• B64C11/18

  Aerodynamic features · CPC title

• B64C27/46

  Blades · CPC title

• B64C39/024

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

• B64C2201/165

  Operations & Transport · mapped topic

• B64C2201/042

  Operations & Transport · mapped topic