Aircraft drag reduction system and internally cooled electric motor system and aircraft using same
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.
1. A fluid cooled electric motor assembly, said motor assembly comprising:
an external rotor, said external rotor comprising:
a rotor support structure; and
a plurality of magnets coupled to an interior surface of said rotor support structure;
an internal stator, said internal stator comprising:
a plurality of winding bars;
a stator support structure, said stator support structure comprising a fluid flow structure radially internal to said plurality of winding bars, wherein said plurality of winding bars is coupled to said stator support structure; and
a fluid capture cover radially outward of said plurality of winding bars, wherein said external rotor is rotationally coupled to said internal stator;
cooling fluid;
one or more heat exchangers fluidically coupled to said fluid flow passages; and
a fluid pump.
2. The fluid cooled electric motor assembly of claim 1 wherein said rotor support structure comprises:
an outer solid surface;
an inner solid surface; and
a supporting lattice between said outer solid surface and said inner solid surface.
3. The fluid cooled electric motor assembly of claim 1 wherein said one or more heat exchangers comprise one or more partial cylindrical heat exchanger segments.
4. A fluid cooled electric motor assembly, said motor assembly comprising:
an external rotor, said external rotor comprising:
a rotor support structure; and
a plurality of magnets coupled to an interior surface of said rotor support structure;
an internal stator, said internal stator comprising:
a plurality of winding bars;
a stator support structure, said stator support structure comprising a fluid flow structure radially internal to said plurality of winding bars, wherein said plurality of winding bars is coupled to said stator support structure; and
a fluid capture cover around an external peripheral surface of said plurality of winding bars, said winding bars within the fluid capture cover, wherein said external rotor is rotationally coupled to said internal stator;
cooling fluid;
one or more heat exchangers fluidically coupled to said fluid flow passages;
a fluid pump, wherein said one or more heat exchangers comprise one or more partial cylindrical heat exchanger segments; and
an air fan, said air fan adapted to suck air into said one or more partial cylindrical heat exchanger segments from an area radially outward of said one or more partial cylindrical heat exchanger segments to an area radially inward of said one or more partial cylindrical heat exchanger segments.
5. The aerial vehicle of claim 4 wherein said fluid pump is rotationally coupled to said air fan.
6. The aerial vehicle of claim 1 further comprising a drive motor for said fluid pump.
7. The aerial vehicle of claim 3 further comprising a drive motor for said fluid pump.
8. The aerial vehicle of claim 4 further comprising a drive motor rotationally coupled to said air fan.
9. The aerial vehicle of claim 5 further comprising a drive motor rotationally coupled to said air fan.
10. An aerial vehicle, said aerial vehicle comprising a plurality of electric motor driven rotor assemblies, said electric motor driven rotor assemblies comprising;
an external rotor, said external rotor comprising:
a rotor support structure; and
a plurality of magnets coupled to an interior surface of said rotor support structure;
an internal stator, said internal stator comprising:
a stator support structure, said stator support structure comprising a fluid flow structure radially internal to a plurality of winding bars;
a plurality of winding bars coupled to said stator support structure; and
a fluid capture cover radially outward of said plurality of winding bars, wherein said external rotor is rotationally coupled to said internal stator;
cooling fluid;
a heat exchanger fluidically coupled to said fluid flow structure; and
a fluid pump.
11. The aerial vehicle of claim 10 further comprising a nacelle coupled to said electric motor driven rotor assemblies, said nacelle defining an outer surface, the forward edge of said defining an air gap behind said rotor.
12. The aerial vehicle of claim 11 wherein said one or more heat exchangers comprise one or more partial cylindrical heat exchanger segments.
13. The aerial vehicle of claim 11 wherein said one or more heat exchangers comprise one or more partial cylindrical heat exchanger segments.
14. The aerial vehicle of claim 12 wherein an outer surface of said one or more partial cylindrical heat exchanger segments is fluidically coupled to said air gap.
15. The aerial vehicle of claim 13 wherein an outer surface of said one or more partial cylindrical heat exchanger segments is fluidically coupled to said air gap.
16. An aerial vehicle, said aerial vehicle comprising a plurality of electric motor driven rotor assemblies, said electric motor driven rotor assemblies comprising;
an external rotor, said external rotor comprising:
a rotor support structure; and
a plurality of magnets coupled to an interior surface of said rotor support structure;
an internal stator, said internal stator comprising:
a stator support structure;
a plurality of winding bars coupled to said stator support structure, said stator support structure comprising a fluid flow structure radially internal to a plurality of winding bars;
a fluid capture cover around an external peripheral surface of said plurality of winding bars, wherein said external rotor is rotationally coupled to said internal stator;
cooling fluid;
a heat exchanger fluidically coupled to said fluid flow structure, wherein said one or more heat exchangers comprise one or more partial cylindrical heat exchanger segments, wherein an outer surface of said one or more partial cylindrical heat exchanger segments is fluidically coupled to an air gap;
a fluid pump; and
an air fan, said air fan adapted to suck air into said one or more partial cylindrical heat exchanger segments from an area radially outward of said one or more partial cylindrical heat exchanger segments to an area radially inward of said one or more partial cylindrical heat exchanger segments.
17. The aerial vehicle of claim 10 wherein said rotor support structure comprises:
an outer solid surface;
an inner solid surface; and
a supporting lattice between said outer solid surface and said inner solid surface.
18. The aerial vehicle of claim 16 wherein said rotor support structure comprises:
an outer solid surface;
an inner solid surface; and
a supporting lattice between said outer solid surface and said inner solid surface.