Aerial vehicle with rotor blade assembly having rotor blade including vortex generator

Patent metadata

Field	Value
Publication number	US-11827340-B2
Application number	US-202016823707-A
Country	US
Kind code	B2
Filing date	Mar 19, 2020
Priority date	Jun 21, 2019
Publication date	Nov 28, 2023
Grant date	Nov 28, 2023

Abstract

An unmanned aerial vehicle includes a fuselage body and a lift mechanism. The lift mechanism includes a rotor blade assembly and a rotary driving member and defines an axis of rotation. The lift being mechanism is coupled to the fuselage body. The rotary driving member is configured to controllably rotate the rotor blade assembly about the axis of rotation. The rotor blade assembly includes at least one rotor blade. The at least one rotor blade including a vortex generator defined along an upper surface of the rotor blade.

First claim

What is claimed is:

1. An unmanned aerial vehicle, comprising:
a fuselage body; and
a lift mechanism including a rotor blade assembly and a rotary driving member and defining an axis of rotation, the lift mechanism being coupled to the fuselage body, the rotary driving member being configured to controllably rotate the rotor blade assembly about the axis of rotation, the rotor blade assembly including a pair of opposing rotor blades, each rotor blade having an upper surface and including an associated vortex generator defined along the upper surface wherein the rotor blade assembly includes a rotor blade attachment mechanism and each rotor blade includes an associated longitudinal spanwise axis that extends between a root portion and an opposing tip portion and a chordwise axis that extends between a leading edge and a trailing edge, each rotor blade being mounted to the rotor blade attachment mechanism at the root portion, wherein each vortex generator extends along the longitudinal spanwise axis, each vortex generator having a length along the longitudinal spanwise axis being over half a distance between the root portion and the opposing tip portion, wherein each rotor blade has a chord length defined by a distance along the chordwise axis between the leading edge and the trailing edge, the height or depth of each vortex generator, relative to the upper surface of the associated rotor blade, being between 0.2% and 5% of the chord length, wherein the associated vortex generator of each rotor blade includes a first row including a first plurality of generator portions and a second row including a second plurality of generator portions, wherein at least some of the generator portions in the first row have a first shape identical to an adjacent generator portion and at least some of the generator portions in the second row having a second shape, the second shape being a portion of the first shape, wherein the associated vortex generator is created by roughening the upper surface of each rotor blade.

2. An unmanned aerial vehicle, as set forth in claim 1 , wherein each rotor blade and the associated vortex generator being unitarily formed.

3. An unmanned aerial vehicle, as set forth in claim 1 , wherein each rotor blade is formed using an injection molding process.

4. A rotor blade assembly for use in an aerial vehicle, the aerial vehicle including a fuselage body and a lift mechanism, the lift mechanism including a rotary driving member and defining an axis of rotation, the lift mechanism being coupled to the fuselage body, the rotary driving member being configured to controllably rotate the rotor blade assembly about the axis of rotation, comprising:
a pair of opposing rotor blades, each rotor blade having an upper surface, and
an associated vortex generator defined along the upper surface of each rotor blade, the rotor blade assembly includes a rotor blade attachment mechanism and each rotor blade having an associated longitudinal spanwise axis extending between a root portion and an opposing tip portion and an associated chordwise axis extending between a leading edge and a trailing edge along a chord wise axis, each rotor blade being mounted to the rotor blade attachment mechanism at the root portion, wherein each rotor blade has a chord length defined by a distance along the chordwise axis between the leading edge and the trailing edge, the height or depth of each vortex generator, relative to the upper surface of the associated rotor blade, being between 0.2% and 5% of the chord length, each vortex generator having a length along the longitudinal spanwise axis being over half a distance between the root portion and the opposing tip portion, wherein the associated vortex generator of each rotor blade includes a first row including a first plurality of generator portions and a second row including a second plurality of generator portions, wherein at least some of the generator portions in the first row have a first shape identical to an adjacent generator portion and at least some of the generator portions in the second row having a second shape, the second shape being a portion of the first shape, wherein the associated vortex generator is created by roughening the upper surface of each rotor blade.

5. A rotor blade assembly, as set forth in claim 4 , wherein each rotor blade and the associated vortex generator being unitarily formed.

6. A rotor blade assembly, as set forth in claim 4 , wherein each rotor blade is formed using an injection molding process.

Assignees

• Hangzhou Zero Zero Tech Co Ltd

Inventors

• Guo Liqiang

Classifications

• B64U2101/30

  for imaging, photography or videography · CPC title

• B64U2201/20

  Remote controls · CPC title

• B64U10/14

  with four distinct rotor axes, e.g. quadcopters · CPC title

• B64U30/24

  Coaxial rotors · CPC title

• B64U30/29

  Constructional aspects of rotors or rotor supports; Arrangements thereof · CPC title