SELECTING PROPELLERS FOR PERFORMANCE AND NOISE SHAPING

• US 20170174317A1
• Filed: 12/18/2015
• Published: 06/22/2017
• Est. Priority Date: 12/18/2015
• Status: Active Grant

• Current Assignee: Amazon Technologies, Inc. (Amazon.com, Inc.)
• Original Assignee: Amazon Technologies, Inc. (Amazon.com, Inc.)
• Inventors: Beckman, Brian C., Ko, Allan
• Granted Patent: US 9,745,050 B2
• Time in Patent Office: Days
• CPC Class Codes: B64C 11/00 Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
• CPC Class Codes: B64C 11/20 Constructional features
• CPC Class Codes: B64C 2230/14 achieving noise reductions
• CPC Class Codes: B64C 27/32 Rotors
• CPC Class Codes: B64C 27/473 Constructional features
• CPC Class Codes: B64U 10/14 with four distinct rotor axes, e.g. quadcopters
• CPC Class Codes: B64U 20/20 for noise reduction
• CPC Class Codes: B64U 2101/64 for parcel delivery or retrieval
• CPC Class Codes: B64U 2201/10 autonomous, i.e. by navigating independently from ground or air stations, e.g. by using inertial navigation systems [INS]
• CPC Class Codes: B64U 30/20 Rotors; Rotor supports
• CPC Class Codes: G05D 1/101 specially adapted for aircraft
• CPC Class Codes: G05D 13/00 Control of linear speed; Control of angular speed; Control of acceleration or deceleration, e.g. of a prime mover
• CPC Class Codes: Y02T 50/10 Drag reduction

Abstract

Aerial vehicles may be operated with discrete sets of propellers, which may be selected for a specific purpose or on a specific basis. The discrete sets of propellers may be operated separately or in tandem with one another, and at varying power levels. For example, a set of propellers may be selected to optimize the thrust, lift, maneuverability or efficiency of an aerial vehicle based on a position or other operational characteristic of the aerial vehicle, or an environmental condition encountered by the aerial vehicle. At least one of the propellers may be statically or dynamically imbalanced, such that the propeller emits a predetermined sound during operation. A balanced propeller may be specifically modified to cause the aerial vehicle to emit the predetermined sound by changing one or more parameters of the balanced propeller and causing the balanced propeller to be statically or dynamically imbalanced.

Claims

1. An unmanned aerial vehicle comprising:

a frame;

a first motor mounted to the frame;

a second motor mounted to the frame;

a first propeller coupled to the first motor, wherein the first propeller is substantially statically balanced and substantially dynamically balanced;

a second propeller coupled to the second motor, wherein the second propeller is at least one of statically imbalanced or dynamically imbalanced, and wherein the second propeller is configured to emit a first sound having a first sound pressure level and within a first frequency spectrum when rotated at a critical speed; and

a computing device having a memory and one or more computer processors,

wherein the computing device is configured to at least;

initiate a first operation of the first motor at a first time; and

initiate a second operation of the second motor at a second time.

2. The unmanned aerial vehicle of claim 1, further comprising at least one sound sensor, and wherein the computing device is further configured to at least:

determine information regarding at least a second sound emitted by the unmanned aerial vehicle at a third time using the at least one sound sensor, wherein the information regarding at least the second sound comprises at least a second sound pressure level and at least a second frequency spectrum, and wherein the third time follows the first time and precedes the second time; and

initiate the second operation of the second motor at the second time based at least in part on the information regarding at least the second sound emitted by the unmanned aerial vehicle at the third time.

3. The unmanned aerial vehicle of claim 1, further comprising at least one position sensor, and

wherein the computing device is further configured to at least:

determine a position of the aerial vehicle at a third time using the at least one position sensor, wherein the third time follows the first time and precedes the second time;

initiate the second operation of the second motor at the second time based at least in part on the position of the aerial vehicle at the third time.

4. A method to operate an aerial vehicle having a first set of propellers and a second set of propellers, the method comprising:

initiating a first operation of each of a first set of motors at a first time, wherein each of the first set of motors is coupled to one of the first set of propellers; and

initiating a second operation of each of a second set of motors at a second time, wherein each of the second set of motors is coupled to one of the second set of propellers,

wherein at least one of the first set of propellers is not statically balanced or is not dynamically balanced.

5. The method of claim 4, further comprising:

identifying a preferred sound to be emitted by the aerial vehicle in flight;

determining at least one of a sound pressure level or a frequency spectrum of the preferred sound using at least one computer processor;

selecting a propeller based at least in part on the sound pressure level or the frequency spectrum of the preferred sound; and

outfitting one of the first set of motors with the selected propeller prior to the first time,

wherein the selected propeller is the at least one of the first set of propellers.

6. The method of claim 4, wherein the at least one of the first set of propellers comprises a first blade and a second blade, and

wherein a mass of the first blade is not equal to a mass of the second blade.

7. The method of claim 4, wherein a center of mass of the at least one of the first set of propellers is not aligned with an axis of rotation of the at least one of the first set of propellers.

8. The method of claim 4, further comprising:

initiating a third operation of each of the first set of motors at a third time, wherein the third time is prior to the first time;

identifying a sound emitted by a first propeller coupled to one of the first set of motors during the third operation using at least one computer processor;

determining at least one of a sound pressure level or a frequency spectrum of the sound emitted by the first propeller using the at least one computer processor;

determining at least one of a sound pressure level or a frequency spectrum of a preferred sound to be emitted by the first propeller in flight using the at least one computer processor;

identifying at least one of a first difference between the sound pressure level of the sound emitted by the first propeller during the third operation and the sound pressure level of the preferred sound to be emitted by the first propeller in flight or a second difference between the frequency spectrum of the sound emitted by the first propeller during the third operation and the frequency spectrum of the preferred sound to be emitted by the first propeller in flight using the at least one computer processor;

determining a modification to at least one parameter of the first propeller based at least in part on at least one of the first difference or the second difference using the at least one computer processor; and

causing the modification to the at least one parameter of the first propeller prior to the first time,

wherein the modified first propeller is the at least one of the first set of propellers.

9. The method of claim 8, wherein the at least one parameter of the first propeller is at least one of:

a mass of at least a first blade of the first propeller;

a shape of at least the first blade of the first propeller;

a lift profile of the first propeller;

or

a drag profile of the first propeller.

10. The method of claim 9, wherein causing the modification to the at least one parameter of the first propeller prior to the first time comprises at least one of:

forming a hole in the first blade;

reducing a width of the first blade;

reducing a length of the first blade;

removing a core from the first blade;

inserting a slug into the first blade;

exposing an opening in the first blade;

changing a blade angle of the first blade;

changing a rake angle of the first blade;

or

changing a thickness of the first blade.

11. The method of claim 4, further comprising:

determining a position of the aerial vehicle at a third time using at least one sensor, wherein the third time is not later than the first time; and

in response to determining the position of the aerial vehicle at the third time,

initiating the first operation of each of the first set of motors at the first time based at least in part on the position of the aerial vehicle at the third time.

12. The method of claim 4, further comprising:

determining an environmental condition in a vicinity of the aerial vehicle at a third time using at least one sensor, wherein the third time is not later than the first time; and

in response to determining the environmental condition in the vicinity of the aerial vehicle at the third time,

initiating the first operation of each of the first set of motors at the first time based at least in part on the environmental condition in the vicinity of the aerial vehicle at the third time,

wherein the environmental condition in the vicinity of the aerial vehicle at the third time comprises at least one of;

a temperature;

a pressure;

a humidity;

a wind speed;

a wind direction;

a weather event;

a level of cloud coverage;

a level of sunshine;

or

a surface condition.

13. The method of claim 4, further comprising:

determining an operational characteristic of the aerial vehicle at a third time using at least one sensor, wherein the third time is not later than the first time; and

in response to determining the operational characteristic of the aerial vehicle at the third time,

initiating the first operation of each of the first set of motors at the first time based at least in part on the operational characteristic of the aerial vehicle at the third time,

wherein the operational characteristic of the aerial vehicle at the third time comprises at least one of;

an altitude;

a course;

a speed;

a climb rate;

a descent rate;

a turn rate;

or

an acceleration.

14. The method of claim 4, further comprising:

determining information regarding at least one sound emitted by the aerial vehicle at a third time using at least one sensor, wherein the information regarding the at least one sound comprises at least one of a sound pressure level of the at least one sound or a frequency spectrum of the at least one sound, and wherein the third time is not later than the first time; and

in response to determining information regarding the at least one sound emitted by the aerial vehicle at the third time,

initiating the second operation of each of the first set of motors at the first time.

15. The method of claim 4,

identifying a mission for the aerial vehicle;

determining a first attribute of the mission for the aerial vehicle;

selecting the at least one of the first set of propellers based at least in part on the first attribute of the mission for the aerial vehicle; and

causing the aerial vehicle to be outfitted with the first set of propellers prior to the first time.

16. The method of claim 15,

wherein the first attribute of the mission for the aerial vehicle is at least one of:

a location of an origin for the mission;

a location of a destination for the mission;

a dimension or a mass of a payload for the mission;

a course for the aerial vehicle during the mission;

a speed for the aerial vehicle during the mission;

an anticipated environmental condition to be encountered by the aerial vehicle during the mission;

an anticipated operational characteristic of the aerial vehicle during the mission;

or

an anticipated sound to be emitted by the aerial vehicle during the mission.

17. A method comprising:

causing a first propeller to rotate to at least a critical speed, wherein the first propeller has a plurality of blades;

determining characteristics of a sound radiating from the first propeller at at least the critical speed, wherein the characteristics of the sound comprise at least one of a first sound pressure level or a first frequency spectrum;

identify characteristics of a preferred sound, wherein the characteristics of the preferred sound comprise at least one of a second sound pressure level or a second frequency spectrum;

determining a difference between at least one of the characteristics of the sound radiating from the first propeller at at least the critical speed and at least one of the characteristics of the preferred sound using at least one computer processor;

modifying the first propeller based at least in part on the difference;

coupling the first propeller to a first motor mounted to an aerial vehicle at a first time; and

initiating a first operation of the first motor after the first time.

18. The method of claim 17, wherein modifying the first propeller comprises at least one of:

forming a hole in at least one of the plurality of blades;

reducing a width of the at least one of the plurality of blades;

reducing a length of the at least one of the plurality of blades;

removing a core from the at least one of the plurality of blades;

inserting a slug into the at least one of the plurality of blades;

exposing an opening in the at least one of the plurality of blades;

changing a blade angle of the at least one of the plurality of blades;

changing a rake angle of the at least one of the plurality of blades;

or

changing a thickness of the at least one of the plurality of blades.

19. The method of claim 17, wherein causing the first propeller to rotate to at least the critical speed further comprises;

coupling the first propeller to the first motor mounted to the aerial vehicle at a second time, wherein the second time precedes the first time; and

initiating a second operation of the first motor after the second time and prior to the first time,

wherein the characteristics of the sound radiating from the first propeller at least the critical speed are determined prior to the first time.

20. The method of claim 19, wherein causing the first propeller to rotate to at east the critical speed further comprises;

coupling the first propeller to a second motor provided in a testing facility at a second time, wherein the second time precedes the first time; and

initiating a second operation of the second motor after the second time and prior to the first time.