Aircraft drag reduction system including an internally cooled motor system and aircraft using same

Patent metadata

Field	Value
Publication number	US-11912393-B2
Application number	US-202217586801-A
Country	US
Kind code	B2
Filing date	Jan 28, 2022
Priority date	Mar 16, 2018
Publication date	Feb 27, 2024
Grant date	Feb 27, 2024

Abstract

An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

First claim

What is claimed is:

1. An aerial vehicle with a drag reduction system, said aerial vehicle comprising:
a motor driven rotor assembly, said motor driven rotor assembly comprising:
a rotor;
a stator, said rotor rotationally coupled to said stator;
a propeller hub, said propeller hub mounted directly to a front side of said rotor;
a nacelle, said nacelle defining an outer surface, said rotor forward of a forward edge of the nacelle, the forward edge of said outer surface of said nacelle defining an air inlet gap behind said rotor, said air inlet gap fluidically coupled to an interior of said nacelle; and
a multi-channel diffuser, said diffuser comprising one or more diffuser plates, said diffuser fluidically coupled to said air inlet gap, said diffuser fluidically coupled to said interior of said nacelle.

2. The aerial vehicle of claim 1 wherein said air inlet gap comprises a ring gap behind the outer periphery of said rotor.

3. The aerial vehicle of claim 1 wherein said motor driven rotor assembly further comprises an air fan, said air fan adapted to suck air into said air inlet gap, said air fan structurally coupled to said stator, said air fan downstream from said diffuser.

4. The aerial vehicle of claim 2 wherein said motor driven rotor assembly further comprises an air fan, said air fan adapted to suck air into said air inlet gap, said air fan structurally coupled to said stator, said air fan downstream from said diffuser.

5. The aerial vehicle of claim 4 wherein said nacelle comprises an airflow exit, said airflow exit fluidically coupled to an interior of said nacelle.

6. The aerial vehicle of claim 5 wherein said motor driven rotor assembly is adapted to ingest air during flight into said air inlet gap at a flow volume fraction of greater than 0.2.

7. The aerial vehicle of claim 6 wherein said motor driven rotor assembly is adapted to ingest air during flight into said air inlet gap at a flow volume fraction of greater than 0.5.

8. The aerial vehicle of claim 1 wherein said motor driven rotor assembly further comprises
a segmented fan, said segmented fan adapted to transfer momentum of a first portion of the airflow through said fan to a second portion of the airflow through said fan; and
air flow channel structures adapted to channelize the airflow through said diffuser into different intake areas of said segmented fan.

9. An aerial vehicle with a drag reduction system, said aerial vehicle comprising:
a motor driven rotor assembly, said motor driven rotor assembly comprising:
a rotor;
a stator, said rotor rotationally coupled to said stator;
a nacelle, said nacelle defining an outer surface, wherein all of said rotor is forward of a forward edge of the nacelle, the forward edge of said outer surface of said nacelle defining an air inlet gap behind said rotor, said air inlet gap fluidically coupled to an interior of said nacelle, wherein said nacelle comprises an airflow exit, said airflow exit fluidically coupled to an interior of said nacelle;

a multi-channel diffuser, said diffuser comprising one or more diffuser plates, said diffuser fluidically coupled to said air inlet gap, said diffuser fluidically coupled to said interior of said nacelle;
an air fan, said air fan adapted to suck air into said air inlet gap, said air fan structurally coupled to said stator, said air fan downstream from said diffuser, wherein said air fan is a segmented fan, said segmented fan adapted to transfer momentum of a first portion of the airflow through said fan to a second portion of the airflow through said fan, and
an air flow channel structures adapted to channelize the airflow through said diffuser into different intake areas of said segmented fan,

wherein said motor driven rotor assembly is adapted to ingest air during flight into said air inlet gap at a flow volume fraction of greater than 0.5.

10. An aerial vehicle with a drag reduction system, said aerial vehicle comprising:
a motor driven rotor assembly, said motor driven rotor assembly comprising:
a rotor;
a stator, said rotor rotationally coupled to said stator;
a nacelle, said nacelle defining an outer surface, said rotor forward of a forward edge of the nacelle, the forward edge of said outer surface of said nacelle defining an air inlet gap behind said rotor, said air inlet gap fluidically coupled to an interior of said nacelle; and
a segmented fan, said segmented fan adapted to transfer momentum of a first portion of the airflow through said fan to a second portion of the airflow through said fan; and
air flow channel structures adapted to channelize the airflow through a diffuser into different intake areas of said segmented fan.

11. The aerial vehicle of claim 10 wherein said air inlet gap comprises a ring gap behind the outer periphery of said rotor.

12. The aerial vehicle of claim 10 wherein said motor driven rotor assembly is adapted to ingest air during flight into said air inlet gap at a flow volume fraction of greater than 0.2.

13. The aerial vehicle of claim 10 wherein said motor driven rotor assembly is adapted to ingest air during flight into said air inlet gap at a flow volume fraction of greater than 0.5.

14. The aerial vehicle of claim 10 wherein said motor driven rotor assembly is adapted to ingest air during flight into said air inlet gap at a flow volume fraction of greater than 1.0.

15. The aerial vehicle of claim 10 , wherein said air inlet gap is defined between said rotor and a front rim of said nacelle.

16. The aerial vehicle of claim 11 wherein said air inlet gap is defined between said rotor and a front rim of said nacelle.

Assignees

• Joby Aero Inc

Inventors

• Bevirt Joeben
• Mikic Gregor Veble
• Milia Joey
• Thodal Rob
• Vithala Vishnu

Classifications

• Y02T50/60

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

• B64D27/34

  All-electric aircraft · CPC title

• B64D27/31

  within, or attached to, wings · CPC title

• B64D27/30

  Aircraft characterised by electric power plants · CPC title

• B64D29/02 Primary

  associated with wings · CPC title