Controlling mechanical vibrations

Patent metadata

Field	Value
Publication number	US-9964966-B1
Application number	US-201514867347-A
Country	US
Kind code	B1
Filing date	Sep 28, 2015
Priority date	Sep 28, 2015
Publication date	May 8, 2018
Grant date	May 8, 2018

Abstract

Mechanical vibrations are generated on a frame of an aerial vehicle as a response to operation of the aerial vehicle, such as rotation of motors and/or propellers. Likewise, environmental conditions, such as wind, humidity, etc., may also cause vibrations on the frame of aerial vehicles. These vibrations may be destructive to the aerial vehicle, impact stability of the aerial vehicle, and/or result in audible sounds. Disclosed are systems and methods for measuring and/or predicting the vibrations on the frame of the aerial vehicle, generating anti-vibrations, and outputting those anti-vibrations such that the anti-vibrations modify vibrations on the frame of the aerial vehicle.

First claim

What is claimed is:

1. An unmanned aerial vehicle (UAV) comprising:
a frame, including:
a first motor arm coupled to the frame and forming a first joint; and
a second motor arm coupled to the frame and forming a second joint;

a first motor coupled to the first motor arm and forming a third joint;
a second motor coupled to the second motor arm and forming a fourth joint;
a first mechanical vibration control system, including:
a first sensor positioned at the first joint to measure a first mechanical vibration occurring at the first joint;
a first processor in communication with the first sensor to receive the measured first mechanical vibration and generate a first anti-vibration; and
a first actuator positioned at the first joint and in communication with the first processor, the first actuator to output the first anti-vibration such that the first anti-vibration reduces the first mechanical vibration at the first joint; and
wherein the first actuator is configured to operate in a first mode as the first sensor to measure the first mechanical vibration, and the first actuator is configured to operate in a second mode to output the first anti-vibration; and

a second mechanical vibration control system, including:
a second sensor positioned at the second joint to measure a second mechanical vibration occurring at the second joint;
a second processor in communication with the second sensor to receive the measured second mechanical vibration and generate a second anti-vibration; and
a second actuator positioned at the second joint and in communication with the second processor, the second actuator to output the second anti-vibration such that the second anti-vibration reduces the second mechanical vibration at the second joint; and
wherein the second actuator is configured to operate in a third mode as the second sensor to measure the second mechanical vibration, and the second actuator is configured to operate in a fourth mode to output the second anti-vibration.

2. The UAV of claim 1 , further comprising:
a third mechanical vibration control system, including:
a third sensor positioned at the third joint to measure a third mechanical vibration occurring at the third joint; and
a third actuator positioned at the third joint, the third actuator to output a third anti-vibration such that the third anti-vibration reduces the third mechanical vibration at the third joint.

3. The UAV of claim 2 , wherein:
the third sensor communicates with the first processor to provide the measured third mechanical vibration to the first processor; and
the first processor generates the third anti-vibration and sends the third anti-vibration to the third actuator.

4. The UAV of claim 1 , wherein the first actuator is configured in a feedback control mode in which the first actuator is configured to operate in the first mode to measure a result of the first mechanical vibration when combined with the first anti-vibration, and the first actuator is configured to operate in the second mode based at least in part on the result.

5. A method to operate an aerial vehicle, the method comprising:
determining a first mechanical vibration at a first location on the aerial vehicle;
generating a first anti-vibration based at least in part on the first mechanical vibration; and
outputting by a first actuator positioned proximate to the first location, the first anti-vibration such that the first anti-vibration modifies the first mechanical vibration;

wherein determining the first mechanical vibration includes operating the first actuator in a first mode in which the first actuator measures the first mechanical vibration; and
wherein outputting the first anti-vibration includes operating the first actuator in a second mode in which the first actuator outputs the first anti-vibration.

6. The method of claim 5 , wherein generating the first anti-vibration includes:
providing information regarding the first mechanical vibration to at least one processor, the information including at least one of a first acceleration of the first mechanical vibration, a first velocity of the first mechanical vibration, a first displacement of the first mechanical vibration, or a first frequency of the first mechanical vibration; and
receiving, from the at least one processor, information regarding the first anti-vibration, wherein the information regarding the first anti-vibration includes at least one of a second acceleration of the first anti-vibration, a second velocity of the first anti-vibration, a second displacement of the first anti-vibration, or a second frequency of the first anti-vibration; and
wherein the second frequency is equal in magnitude and of reverse polarity with respect to the first frequency.

7. The method of claim 5 , wherein determining the first mechanical vibration includes measuring the first mechanical vibration using the first actuator in the first mode as a first sensor positioned at the first location on the aerial vehicle.

8. The method of claim 5 ,
wherein the first anti-vibration is generated without regard to the output from the first actuator.

9. The method of claim 5 ,
wherein the first anti-vibration is generated based at least in part on a net effect of a combination of the first mechanical vibration and the first anti-vibration.

10. The method of claim 5 , further comprising:
determining information regarding a transit plan for the aerial vehicle, wherein the transit plan comprises information regarding at least one of a plurality of positions of the aerial vehicle, environmental conditions anticipated for the aerial vehicle, or operational conditions anticipated for the aerial vehicle; and
wherein determining the first mechanical vibration is based on the transit plan.

11. The method of claim 10 , further comprising:
determining a second mechanical vibration at a second location on the aerial vehicle, wherein the second mechanical vibration is determined based at least in part on the transit plan;
generating a second anti-vibration based at least in part on the second mechanical vibration; and
outputting by a second actuator positioned at the second location, the second anti-vibration such that the second anti-vibration modifies the second mechanical vibration.

12. The method of claim 5 , further comprising:
determining a second mechanical vibration at a second location on the aerial vehicle, wherein the second mechanical vibration is measured by a sensor positioned at the second location;
generating a second anti-vibration based at least in part on the second mechanical vibration; and
outputting by a second actuator positioned proximate to the second location, the second anti-vibration such that the second anti-vibration modifies the second mechanical vibration.

13. The method of claim 5 , further comprising:
measuring an environmental condition during an operation of the aerial vehicle;
measuring an operational condition during the operation of the aerial vehicle; and
correlating the first mechanical vibration with at least one of the environmental condition or the operational condition.

14. The method of claim 13 , wherein the environmental condition is at least one of a temperature, a barometric pressure, a wind speed, a humidity, a level of cloud coverage, a level of sunshine, a surface condition, a time of day, a time of year, a phase of a moon, a tide of the ocean, a direction of a earth's magnetic field, a pollution level, or a particulates count.

15. The method of claim 13 , wherein the operational characteristic is at least one of a rotating speed of a m

Assignees

• Amazon Tech Inc

Inventors

• Beckman Brian C
• Green Scott A

Classifications

• B64C2027/002

  mounted between the rotor drive and the fuselage · CPC title

• B64C27/08

  with two or more rotors · CPC title

• G05D19/00 Primary

  Control of mechanical oscillations, e.g. of amplitude, of frequency, of phase · CPC title

• B64C2027/004

  using actuators, e.g. active systems · CPC title

• B64C27/001 Primary

  Vibration damping devices · CPC title