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公开(公告)号：US20180222583A1
公开(公告)日：2018-08-09
申请号：US15890506
申请日：2018-02-07
Applicant: Aurora Flight Sciences Corporation
Inventor： Robert W. Parks , Riley C. Griffin , Christopher Courtin , Amanda Kaufman , Thomas Clancy
CPC classification number: B64C39/024 , B64C19/00 , B64C37/02 , B64C2201/021 , B64C2201/12 , B64C2201/141 , B64D5/00
Abstract: Disclosed herein is a booster aircraft system having a host aircraft and one or more booster UAVs coupled thereto. When necessary, such as during takeoff and climb of the host aircraft, the booster UAVs operate to boost the thrust of the host aircraft. The booster UAVs are configured to detach from the host aircraft when no longer needed (e.g., at cruising altitude/speed), thus removing their weight from the host aircraft. Each booster UAV includes wings, one or more propulsors, a control system, and landing gear, which enable the booster UAV to return autonomously to a predetermined location once detached from the host aircraft to be refueled and reused.
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公开(公告)号：US10899461B2
公开(公告)日：2021-01-26
申请号：US15866655
申请日：2018-01-10
Applicant: Aurora Flight Sciences Corporation
Inventor： Evangelos Livieratos , Riley Griffin , Nathan Varney , Amanda Kaufman
IPC: B64D27/24 , B64D27/04 , B64C27/08 , F02B41/04 , F02D13/02 , F02N11/04 , B64C39/02 , F02B63/04 , B64D27/02 , F02B75/34 , F02D29/06
Abstract: A hybrid-electric aerial vehicle is disclosed comprising: an airframe; a plurality of longitudinal booms extending radially from the airframe; a passively charged internal combustion engine operatively coupled with a fuel tank, a generator operatively coupled with the passively charged internal combustion engine; a battery bank operatively coupled with the generator; and a plurality of motors. The passively charged internal combustion engine has an intake engine valve, an exhaust engine valve, and a combustion chamber, wherein the intake engine valve is delayed to provide an expansion ratio in the combustion chamber that is greater than a compression ratio in the combustion chamber. Each of said plurality of motors may be positioned at a distal end of one of said plurality of longitudinal booms and be operatively coupled with a propeller, wherein the plurality of motors is electrically coupled with the battery bank and the generator.
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公开(公告)号：US20190291856A1
公开(公告)日：2019-09-26
申请号：US15928372
申请日：2018-03-22
Applicant: Aurora Flight Sciences Corporation
Inventor： Amanda Kaufman , Riley C. Griffin , Kevin Uleck , Martin Kearney-Fischer , James D. Paduano
IPC: B64C27/12 , B64C27/08 , B64C27/473
Abstract: Disclosed is an aerial vehicle having a reduced noise signature. The aerial vehicle may be a vertical take-off and landing (VTOL) aerial vehicle. The aerial vehicle comprises an airframe and a plurality of rotors operatively coupled with one or more motors. The plurality of rotors may comprise a first, second, third, and fourth rotor. Each of the first, second, third, and fourth rotors may be arranged in a single plane and oriented to direct thrust downward relative to the airframe. In certain aspects, at least two of the plurality of rotors employ a different geometry to generate a targeted noise signature.
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Patent Agency Ranking
公开(公告)号：US11008093B2
公开(公告)日：2021-05-18
申请号：US15928372
申请日：2018-03-22
Applicant: Aurora Flight Sciences Corporation
Inventor： Amanda Kaufman , Riley C. Griffin , Kevin Uleck , Martin Kearney-Fischer , James D. Paduano
IPC: B64C27/08 , B64C27/14 , B64C27/32 , B64C27/12 , B64C27/473 , B64C11/18 , G10K11/178
Abstract: Disclosed is an aerial vehicle having a reduced noise signature. The aerial vehicle may be a vertical take-off and landing (VTOL) aerial vehicle. The aerial vehicle comprises an airframe and a plurality of rotors operatively coupled with one or more motors. The plurality of rotors may comprise a first, second, third, and fourth rotor. Each of the first, second, third, and fourth rotors may be arranged in a single plane and oriented to direct thrust downward relative to the airframe. In certain aspects, at least two of the plurality of rotors employ a different geometry to generate a targeted noise signature.
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公开(公告)号：US10942041B2
公开(公告)日：2021-03-09
申请号：US16047727
申请日：2018-07-27
Applicant: Aurora Flight Sciences Corporation
Inventor： Amanda Kaufman , William Robert Bosworth , James Donald Paduano , Riley C. Griffin , Sachin Jain
Abstract: An aircraft, system, and method for sensing and/or releasing chemical agents by an aircraft is disclosed. The aircraft, system, and method may employ a chemical sensor, a wind sensor, an imaging device for capturing environmental features, and/or a processor operably coupled therewith. The processor may be used for collecting data from the chemical sensor, the wind sensor, and the imaging device to identify a navigational waypoint and to provide commands to the chemical sensor or to the aircraft based at least in part on collected data.
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公开(公告)号：US20200033157A1
公开(公告)日：2020-01-30
申请号：US16047727
申请日：2018-07-27
Applicant: Aurora Flight Sciences Corporation
Inventor： Amanda Kaufman , William Robert Bosworth , James Donald Paduano , Riley C. Griffin , Sachin Jain
Abstract: An aircraft, system, and method for sensing and/or releasing chemical agents by an aircraft is disclosed. The aircraft, system, and method may employ a chemical sensor, a wind sensor, an imaging device for capturing environmental features, and/or a processor operably coupled therewith. The processor may be used for collecting data from the chemical sensor, the wind sensor, and the imaging device to identify a navigational waypoint and to provide commands to the chemical sensor or to the aircraft based at least in part on collected data.
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公开(公告)号：US10315742B2
公开(公告)日：2019-06-11
申请号：US15682938
申请日：2017-08-22
Applicant: Aurora Flight Sciences Corporation
Inventor： Amanda Kaufman
Abstract: A marine propeller is disclosed having two blades. The shape of the propeller blades remains constant through the radial position of the propeller blades. The blade length of the propeller blades changes as a function of the radial position of the propeller blade. The twist angle of each blade starts at approximately 63 degrees at the propeller hub (proximal end) and decreases to about 15 degrees at the blade tip (distal end).
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公开(公告)号：US20190061891A1
公开(公告)日：2019-02-28
申请号：US15682938
申请日：2017-08-22
Applicant: Aurora Flight Sciences Corporation
Inventor： Amanda Kaufman
Abstract: A marine propeller is disclosed having two blades. The shape of the propeller blades remains constant through the radial position of the propeller blades. The blade length of the propeller blades changes as a function of the radial position of the propeller blade. The twist angle of each blade starts at approximately 63 degrees at the propeller hub (proximal end) and decreases to about 15 degrees at the blade tip (distal end).
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