Rotor deployment mechanism for electric vertical take-off and landing aircraft

Patent metadata

Field	Value
Publication number	US-11560221-B2
Application number	US-202117389020-A
Country	US
Kind code	B2
Filing date	Jul 29, 2021
Priority date	Mar 18, 2014
Publication date	Jan 24, 2023
Grant date	Jan 24, 2023

Abstract

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements for takeoff and landing. An aerial vehicle which is adapted to vertical takeoff with the rotors in a rotated, take-off attitude then transitions to a horizontal flight path, with the rotors rotated to a typical horizontal configuration. The aerial vehicle uses different configurations of its wing mounted rotors and propellers to reduce drag in all flight modes. The aerial vehicle uses deployment mechanisms to deploy rotor assemblies up and away from their stowed configuration locations.

First claim

What is claimed is:

1. A propeller deployment mechanism for an electric vertical take-off and landing aircraft, said propeller deployment mechanism comprising:
an extendable linkage assembly, said extendable linkage assembly comprising a plurality of pivoting mounting points on a first end, said pivoting mounting points adapted to mount to fixed mounting points on an electric vertical take-off and landing aircraft; and
an outboard bracket, said outboard bracket comprising a central axis, said outboard bracket coupled to a second end of said extendable linkage,

wherein said extendable linkage is adapted to deploy said outboard bracket from a first position where said central axis of said outboard bracket is horizontal to a second position wherein said central axis of said outboard bracket is vertical, and wherein all of said outboard bracket is further forward from said plurality of main pivoting mounting points in said second position than in said first position, and wherein all of said outboard bracket is higher in said second position than in said first position.

2. The propeller deployment mechanism of claim 1 further comprising:
an electric motor, said electric motor comprising:
a rotor; and
a stator, wherein said stator is structurally coupled to said outboard bracket, and

wherein said stator is rotationally coupled to said rotor; and
a propeller main hub, said propeller hub is structurally coupled to said rotor of said motor,
wherein said electric motor and said propeller hub deploy with said outboard bracket.

3. The propeller deployment mechanism of claim 2 further comprising a plurality of blades structurally coupled to said propeller main hub.

4. The propeller deployment mechanism of claim 2 wherein said extendable linkage assembly further comprises one or more multi-arm linkages.

5. The propeller deployment mechanism of claim 4 wherein said extendable linkage assembly further comprises;
a first multi-arm linkage comprising a first end and a second end, said first multi-arm linkage comprising first pivoting mounting point at its first end, said second end of said first multi-arm linkage pivotally coupled to said outboard bracket;
a second multi-arm linkage comprising a first end and a second end, said second multi-arm linkage comprising second pivoting mounting point at its first end, said second end of said second multi-arm linkage pivotally coupled to said outboard bracket;
wherein said an arm of said first multi-arm linkage is pivotally coupled to an arm of said second multi-arm linkage.

6. The propeller deployment mechanism of claim 5 wherein said first multi-arm linkage is pivotally coupled to a first end of said outboard bracket, and wherein said second multi-arm linkage is pivotally coupled to a second end of said outboard bracket.

7. The propeller deployment mechanism of claim 1 further comprising a plurality of blades structurally coupled to said propeller main hub.

8. A propeller deployment system, the propeller deployment system comprising:
an outboard bracket,
wherein the outboard bracket is rotationally coupled to a main hub,
wherein the main hub comprises a first main hub rotation axis,
wherein a first plane is positioned on an upper surface of the outboard bracket,
wherein an intersection of the first plane and the first main hub rotation axis defines a first reference point;

a propeller deployment mechanism,
wherein the propeller deployment mechanism comprises a linkage assembly,
wherein the linkage assembly is configured to pivotally couple to a vehicle body at least at a first vehicle mounting point, wherein the first vehicle mounting point comprises a first vehicle mounting axis,
wherein the linkage assembly is configured to couple to the outboard bracket at least at a first bracket mounting point, wherein the first bracket mounting point comprises a first bracket mounting axis,
wherein the propeller deployment mechanism is configured to deploy the outboard bracket between a vertical flight configuration and a forward flight configuration,
wherein the first reference point travels a first path when the propeller deployment mechanism deploys the outboard bracket,
wherein a radius of curvature defined by the first path is non-zero, non-constant, and no greater than a maximum distance between the first vehicle mounting axis and the first bracket mounting axis.

9. The propeller deployment mechanism of claim 8 further comprising:
an electric motor, said electric motor comprising:
a rotor,
a stator, wherein said stator is structurally coupled to said outboard bracket,
wherein said stator is rotationally coupled to said rotor,

wherein said propeller main hub is structurally coupled to said rotor of said motor, and
wherein said electric motor and said propeller hub deploy with said outboard bracket.

10. The propeller deployment mechanism of claim 9 further comprising a plurality of blades structurally coupled to the main hub.

11. The propeller deployment mechanism of claim 9 wherein the extendable linkage assembly further comprises one or more multi-arm linkages.

12. The propeller deployment mechanism of claim 11 wherein said extendable linkage assembly further comprises;
a first multi-arm linkage comprising a first end and a second end, said first multi-arm linkage comprising first pivoting mounting point at its first end, said second end of said first multi-arm linkage pivotally coupled to said outboard bracket;
a second multi-arm linkage comprising a first end and a second end, said second multi-arm linkage comprising second pivoting mounting point at its first end, said second end of said second multi-arm linkage pivotally coupled to said outboard bracket;
wherein said an arm of said first multi-arm linkage is pivotally coupled to an arm of said second multi-arm linkage.

13. The propeller deployment mechanism of claim 12 wherein said first multi-arm linkage is pivotally coupled to a first end of said outboard bracket, and wherein said second multi-arm linkage is pivotally coupled to a second end of said outboard bracket.

14. The propeller deployment mechanism of claim 8 further comprising a plurality of blades structurally coupled to said main hub.

15. A wing mounted propeller deployment mechanism for an electric vertical take-off and landing aircraft, said propeller deployment mechanism comprising:
a wing;
a nacelle extending forward from said wing;
a plurality of fixed mounting points within said nacelle, said fixed mounting points structurally coupled to said wing;
an extendable linkage assembly, said extendable linkage assembly comprising a plurality of pivoting mounting points on a first end, each of said pivoting mounting points coupled to one of said fixed mounting point; and
an outboard bracket, said outboard bracket comprising a central axis, said outboard bracket coupled to a second end of said extendable linkage,

wherein said extendable linkage is adapted to deploy said outboard bracket from a first position where said central axis of said outboard bracket is horizontal to a second position wherein said central axis of said outboard bracket is vertical, and wherein all of said outboard bracket is further forward from said plurality of main pivoting mounting points in said second position than in said first position, and wherein all of said outboard bracket is higher in said second position than in said first position.

16. The propeller deployment mechanism of claim 15 further comprising:
an electric motor, said electric motor comprising:
a rotor; and
a stator, wherein said stat

Assignees

• Joby Aero Inc

Inventors

• Bevirt Joeben
• Stoll Alex

Classifications

• B64C27/30 Primary

  with provision for reducing drag of inoperative rotor · CPC title

• B64D27/24

  using steam or spring force (jet aircraft B64D27/16) · CPC title

• B64C29/0008

  having its flight directional axis horizontal when grounded · CPC title

• B64C11/10 Primary

  rigid · CPC title

• B64C29/0033

  the propellers being tiltable relative to the fuselage · CPC title