Aerodynamically Efficient Lightweight Vertical Take-Off And Landing Aircraft With Pivoting Rotors And Box Wing Design

Patent metadata

Field	Value
Publication number	US-2020317353-A1
Application number	US-202016815006-A
Country	US
Kind code	A1
Filing date	Mar 11, 2020
Priority date	Mar 18, 2014
Publication date	Oct 8, 2020
Grant date	—

Abstract

An aerial vehicle adapted for vertical takeoff and landing using a set of wing mounted thrust producing elements and a set of tail mounted rotors 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.

First claim

What is claimed is:

1 . An aerial vehicle adapted for vertical take-off and horizontal flight, said aerial vehicle comprising:
a main vehicle body; a box wing structure, said box wing structure comprising:
a right side box wing structure portion, said right side box wing structure comprising:
a right side forward wing section coupled to said main vehicle body at a first joining position; and
a right side rear wing section coupled to said main vehicle body rearward at a second joining position rearward of said first joining position, wherein said right side forward wing section is coupled to said right side rear wing section outboard of said main vehicle body; and

a left side box wing structure portion, said left side box wing structure comprising:
a left side forward wing section coupled to said main vehicle body at a first joining position; and
a left side rear wing section coupled to said main vehicle body rearward at a second joining position rearward of said first joining position, wherein said forward wing section is coupled to said rear wing section outboard of said main vehicle body;

one or more right side forward wing rotor assemblies, said one or more right side forward wing rotor assemblies comprising a propeller and a motor, wherein one or more right side forward wing rotor assemblies are attached to said right side forward wing, and wherein said one or more right side forward wing rotor assemblies protrude forward of the leading edge of said right side wing along a middle section of the right side forward wing span; one or more left side forward wing rotor assemblies, said one or more left side forward wing rotor assemblies comprising a propeller and a motor, wherein one or more left side forward wing rotor assemblies are attached to said left side forward wing, and wherein said one or more left side forward wing rotor assemblies protrude forward of the leading edge of said left side wing along a middle section of the left side forward wing span; one or more right side rear wing rotor assemblies, said one or more right side rear wing rotor assemblies comprising a propeller and a motor, wherein one or more right side rear wing rotor assemblies are attached to said right side rear wing along a middle section of the right side rear wing span; and one or more left side rear wing rotor assemblies, said one or more left side rear wing rotor assemblies comprising a propeller and a motor, wherein one or more left side rear wing rotor assemblies are attached to said left side rear wing along a middle section of the left side rear wing span.

2 . The aerial vehicle of claim 1 wherein said one or more right side forward wing rotor assemblies are attached to said right forward wing by a deployment mechanism adapted to deploy said one or more right side forward wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration, and wherein said one or more left side forward wing rotor assemblies are attached to said left side forward wing by a deployment mechanism adapted to deploy said one or more left side forward wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration, and wherein said one or more right side rear wing rotor assemblies are attached to said right side rear wing by a deployment mechanism adapted to deploy said one or more right side rear wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration, and wherein said one or more left side rear wing rotor assemblies are attached to said left side rear wing by a deployment mechanism adapted to deploy said one or more left side rear wing rotor assemblies from a forward facing horizontal flight configuration to a vertical take-off configuration.

3 . The aerial vehicle of claim 1 wherein said motor of each of said one or more right side forward wing rotor assemblies is an electric motor, and wherein said motor each of said one or more right side rear wing rotor assemblies is an electric motor, and wherein said motor of each of said one or more left side front wing rotor assemblies is an electric motor, and wherein said motor of each of said left side rear wing rotor assemblies is an electric motor.

4 . The aerial vehicle of claim 3 wherein the spin axis of said one or more right side forward wing rotor assemblies are forward of the leading edge of said right side forward wing in the vertical take-off position, and wherein the spin axis of said one or more left side forward wing rotor assemblies are forward of the leading edge of said left side forward wing in the vertical take-off position.

5 . The aerial vehicle of claim 1 wherein said right side rear wing section is higher than said right side forward wing section when said aerial vehicle is in a forward flight configuration, and wherein said left side rear wing section is higher than said left side forward wing section when said aerial vehicle is in a forward flight configuration.

6 . The aerial vehicle of claim 2 wherein said right side rear wing section is higher than said right side forward wing section when said aerial vehicle is in a forward flight configuration, and wherein said left side rear wing section is higher than said left side forward wing section when said aerial vehicle is in a forward flight configuration.

7 . The aerial vehicle of claim 3 wherein said right side rear wing section is higher than said right side forward wing section when said aerial vehicle is in a forward flight configuration, and wherein said left side rear wing section is higher than said left side forward wing section when said aerial vehicle is in a forward flight configuration.

8 . The aerial vehicle of claim 4 wherein the spin axis of said one or more right side rear wing rotor assemblies are forward of the leading edge of said right side rear wing in the vertical take-off position, and wherein the spin axis of said one or more left side rear wing rotor assemblies are forward of the leading edge of said left side rear wing in the vertical take-off position.

9 . The aerial vehicle of claim 6 wherein the spin axis of said one or more right side forward wing rotor assemblies are forward of the leading edge of said right side forward wing in the vertical take-off position, and wherein the spin axis of said one or more left side forward wing rotor assemblies are forward of the leading edge of said left side forward wing in the vertical take-off position.

10 . The aerial vehicle of claim 9 wherein the spin axis of said one or more right side rear wing rotor assemblies are forward of the leading edge of said right side rear wing in the vertical take-off position, and wherein the spin axis of said one or more left side rear wing rotor assemblies are forward of the leading edge of said left side rear wing in the vertical take-off position.

Assignees

• Joby Aero Inc

Inventors

• Bevirt Joeben
• Stoll Alex

Classifications

• B64D27/34

  All-electric aircraft · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/357

  using batteries · CPC title

• B64C11/28 Primary

  Collapsible or foldable blades · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title