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公开(公告)号：US20220169362A1
公开(公告)日：2022-06-02
申请号：US17586801
申请日：2022-01-28
Applicant: Joby Aero, Inc.
Inventor： JoeBen Bevirt , Gregor Veble Mikic , Joey Milia , Rob Thodal , Vishnu Vithula
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.
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2.发明申请公开(公告)号：US20190329859A1
公开(公告)日：2019-10-31
申请号：US16355745
申请日：2019-03-16
Applicant: Joby Aero, Inc.
Inventor： JoeBen Bevirt , Gregor Veble Mikic , Joey Milia , Rob Thodal , Vishnu Vithula
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.
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3.发明申请公开(公告)号：US20190329858A1
公开(公告)日：2019-10-31
申请号：US16355742
申请日：2019-03-16
Applicant: Joby Aero, Inc.
Inventor： JoeBen Bevirt , Gregor Veble Mikic , Joey Milia , Rob Thodal , Vishnu Vithula
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.
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