Rotor units having asymmetric rotor blades

Patent metadata

Field	Value
Publication number	US-10604245-B2
Application number	US-201615396399-A
Country	US
Kind code	B2
Filing date	Dec 30, 2016
Priority date	Dec 30, 2016
Publication date	Mar 31, 2020
Grant date	Mar 31, 2020

Abstract

An aerial vehicle is provided including rotor units connected to the aerial vehicle, and a control system configured to operate at least one of the rotor units. The rotor unit includes rotor blades, wherein each rotor blade includes a surface area, and wherein an asymmetric parameter is defined, at least in part, by the relationship between the surface areas of the rotor blades. The value of the asymmetric parameter is selected such that the operation of the rotor unit: (i) moves the rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices cause the rotor unit to produce a sound output having an energy distribution defined, at least in part, by a set of frequencies, wherein the set of frequencies includes a fundamental frequency, one or more harmonic frequencies, and one or more non-harmonic frequencies having a respective strength greater than a threshold strength.

First claim

We claim:

1. An aerial vehicle comprising:
a plurality of rotor units connected to the aerial vehicle, wherein at least one rotor unit of the plurality of rotor units comprises:
two or more rotor blades, wherein each rotor blade of the two or more rotor blades comprises a surface area, and wherein an asymmetric parameter is defined, at least in part, by the relationship between the surface areas of the two or more rotor blades; and

a control system configured to operate the at least one rotor unit, wherein the value of the asymmetric parameter is selected such that the operation of the at least one rotor unit: (i) moves the two or more rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices produced by the two or more rotor blades cause the rotor unit to produce a sound output having an energy distribution defined, at least in part, by a set of frequencies, wherein the set of frequencies comprises a fundamental frequency, one or more harmonic frequencies of the fundamental frequency, and one or more non-harmonic frequencies of the fundamental frequency having a respective strength greater than a threshold strength.

2. The aerial vehicle of claim 1 , wherein the value of the asymmetric parameter is selected such that the operation of the at least one rotor unit: (i) moves the two or more rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices produced by the two or more rotor blades cause the rotor unit to produce the sound output having the energy distribution defined, at least in part, by the set of frequencies, wherein the set of frequencies comprises a predetermined number of frequencies.

3. The aerial vehicle of claim 1 , wherein the value of the asymmetric parameter is selected such that the operation of the at least one rotor unit: (i) moves the two or more rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices produced by the two or more rotor blades cause the rotor unit to produce the sound output having the energy distribution, defined at least in part, by the set of frequencies, wherein the set of frequencies comprises at least one frequency having a predetermined strength.

4. The aerial vehicle of claim 1 , wherein the two or more rotor blades comprise: a first rotor blade comprising a first length, and
a second rotor blade comprising a second length, and wherein the asymmetric parameter is defined, at least in part, by a difference between the first length and the second length.

5. The aerial vehicle of claim 1 , wherein the two or more rotor blades comprise:
a first rotor blade comprising a first width, and
a second rotor blade comprising a second width, and wherein the asymmetric parameter is defined, at least in part, by a difference between the first width and the second width.

6. The aerial vehicle of claim 1 , wherein the two or more rotor blades comprise a first rotor blade and a second rotor blade, and wherein the value of the asymmetric parameter is selected such that the operation of the at least one rotor unit: (i) moves the first rotor blade such that the first rotor blade produces a first vortex, (ii) moves the second rotor blade such that the second rotor blade produces a second vortex, and (iii) the first vortex produced by the first rotor blade and the second vortex produced by the second rotor blade cause the rotor unit to produce the sound output having the energy distribution defined, at least in part, by the set of frequencies.

7. The aerial vehicle of claim 6 , wherein the first vortex has a first strength, and wherein the second vortex has a second strength that is different than the first strength.

8. The aerial vehicle of claim 6 , wherein the first vortex and the second vortex couple to form a third vortex, and wherein the third vortex causes the rotor unit to produce the sound output having the energy distribution defined, at least in part, by the set of frequencies.

9. The aerial vehicle of claim 8 , wherein the first vortex has a first period, wherein the second vortex has a second period that is substantially the same as the first period, and wherein the third vortex has a third period that is different than the first and second periods.

10. The aerial vehicle of claim 1 , wherein the plurality of rotor units comprise a first rotor unit and a second rotor unit, wherein the first rotor unit comprises:
a first rotor blade and a second rotor blade coupled to a first motor, wherein the first rotor blade comprises a first length, wherein the second rotor blade comprises a second length, and wherein a first asymmetric parameter is defined, at least in part, by the relationship between the first length and the second length, wherein the value of the first asymmetric parameter is selected such that the operation of the first rotor unit: (i) moves the first rotor blade such that the first rotor blade produces a first trailing tip vortex, (ii) moves the second rotor blade such that the second rotor blade produces a second trailing tip vortex, and (iii) the first trailing tip vortex produced by the first rotor blade and the second trailing tip vortex produced by the second rotor blade cause the first rotor unit to produce a first sound output having a first energy distribution defined, at least in part, by a first set frequencies, wherein the first set of frequencies comprises a first fundamental frequency, one or more first harmonic frequencies of the first fundamental frequency, and one or more first non-harmonic frequencies of the first fundamental frequency having a respective strength greater than the threshold strength, wherein the second rotor unit comprises:
a third rotor blade and a fourth rotor blade coupled to a second motor, wherein the third rotor blade comprises a third length, wherein the fourth rotor blade comprises a fourth length, and wherein a second asymmetric parameter is defined, at least in part, by the relationship between the third length and the fourth length, wherein the value of the second asymmetric parameter is selected such that the operation of the second rotor unit: (i) moves the third rotor blade such that the third rotor blade produces a third trailing tip vortex, (ii) moves the fourth rotor blade such that the fourth rotor blade produces a fourth trailing tip vortex, and (iii) the third trailing tip vortex produced by the third rotor blade and the fourth trailing tip vortex produced by the fourth rotor blade cause the second rotor unit to produce a second sound output having a second energy distribution defined, at least in part, by a second set frequencies, and wherein the second set of frequencies comprises a second fundamental frequency, one or more second harmonic frequencies of the second fundamental frequency, and one or more second non-harmonic frequencies of the second fundamental frequency having a respective strength greater than the threshold strength.

11. The aerial vehicle of claim 10 , wherein the first asymmetric parameter is substantially the same as the second asymmetric parameter.

12. The aerial vehicle of claim 10 , wherein the first asymmetric parameter is different than the second asymmetric parameter.

13. The aerial vehicle of claim 10 , wherein the first set of frequencies is substantially the same as the second set of frequencies.

14. The aerial vehicle of claim 10 , wherein the first set of frequencies is different than the second set of frequencies.

15. A rotor unit comprising:
a motor;
a hub coupled to the motor; and
two or more rotor blades coupled to the hub, wherein each rotor blade of the t

Assignees

• Wing Aviation Llc

Inventors

• Pantalone Giulia
• Woodworth Adam

Classifications

• B64C27/32 Primary

  Rotors · CPC title

• B64C2230/14

  achieving noise reductions · CPC title

• B64C27/463 Primary

  Blade tips · CPC title

• B64C2230/28

  at propeller or rotor blades · CPC title

• B64C27/467 Primary

  Aerodynamic features · CPC title