公开(公告)号：US10183744B2

公开(公告)日：2019-01-22

申请号：US15040428

申请日：2016-02-10

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: B64C29/00 ,  B64C27/30

Abstract: In one embodiment, a hybrid aircraft includes a fixed-wing propulsion system and a multirotor propulsion system. The multirotor propulsion system includes a propeller coupled to a motor shaft. A motor drives the propeller via the motor shaft. The hybrid aircraft further includes a magnetic orientation detent to prevent the propeller of the multirotor propulsion system from rotating when power to the multirotor propulsion system is removed. The magnetic orientation detent further includes a plurality of magnets coupled to the circumference of the motor shaft and a detent magnet magnetically coupled to the plurality of magnets.

公开(公告)号：US10458393B2

公开(公告)日：2019-10-29

申请号：US15269229

申请日：2016-09-19

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: B64C27/08 ,  F03D9/32 ,  B64C27/10 ,  B64C27/14 ,  B64C27/80 ,  B64C27/50 ,  F03D17/00 ,  B64C27/52

Abstract: A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first and second rotor assembly, wherein the first rotor assembly comprises a first motor coupled to a first rotor, the first rotor comprising a plurality of first fixed-pitch blades and the second rotor assembly comprises a second motor coupled to a second rotor, the second rotor comprising a plurality of second fixed-pitch blades. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to at least one of the first or second gimbal motors in order to orient the plurality of first and second fixed-pitch blades into a position that permits wind to rotate the first and second fixed-pitch blades and thereby charge the power source.

公开(公告)号：US10479496B2

公开(公告)日：2019-11-19

申请号：US15338832

申请日：2016-10-31

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble ,  Gordon Jennings ,  Justin Neel

IPC: B64C29/00 ,  H02K11/21 ,  H02K11/33 ,  H02K7/00 ,  H02K7/02 ,  H02K7/14 ,  H02P3/02 ,  B64C27/30

Abstract: In one embodiment, a magnetic orientation detent includes a motor coupled to a motor shaft, the motor mechanically coupled to a motor mount. The magnetic orientation detent may also include a flywheel mechanically coupled to a distal end of the motor shaft. The magnetic orientation detent may further include a first plurality of magnets coupled to the motor mount and a second plurality of magnets coupled to the flywheel. The second plurality of magnets couple magnetically to the first plurality of magnets.

公开(公告)号：US10370089B2

公开(公告)日：2019-08-06

申请号：US15085540

申请日：2016-03-30

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: B64C27/08 ,  B64C17/04 ,  B64C27/10 ,  B64C27/52 ,  B64C11/28 ,  B64C25/34 ,  B64C25/66 ,  B64C27/14 ,  B64C39/02 ,  B64D47/08 ,  B64C25/32

Abstract: A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.

公开(公告)号：US20170284371A1

公开(公告)日：2017-10-05

申请号：US15269229

申请日：2016-09-19

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: F03D9/32 ,  F03D17/00 ,  B64C27/80 ,  B64C27/50 ,  B64C27/10 ,  B64C27/14

Abstract: A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first and second rotor assembly, wherein the first rotor assembly comprises a first motor coupled to a first rotor, the first rotor comprising a plurality of first fixed-pitch blades and the second rotor assembly comprises a second motor coupled to a second rotor, the second rotor comprising a plurality of second fixed-pitch blades. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to at least one of the first or second gimbal motors in order to orient the plurality of first and second fixed-pitch blades into a position that permits wind to rotate the first and second fixed-pitch blades and thereby charge the power source.

公开(公告)号：US20240367790A1

公开(公告)日：2024-11-07

申请号：US18312336

申请日：2023-05-04

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: B64U30/10 ,  B64U30/40

Abstract: In one embodiment, systems and methods include an aircraft vehicle comprising a body, a first wing coupled to the body, and a second wing coupled to the body, wherein the second wing has a length greater than the first wing, wherein each of the first wing and the second wing comprises a plurality of segments, wherein the second wing comprises a wing pylon system. The wing pylon system comprises one of the plurality of segments of the second wing, a payload, and a pylon coupling the payload to the one of the plurality of segments, the pylon being disposed underneath the one of the plurality of segments, and the payload being disposed underneath the pylon. A center of lift and a center of gravity for the aircraft vehicle are aligned and each is offset from a central axis of the body.

公开(公告)号：US20240092498A1

公开(公告)日：2024-03-21

申请号：US17932424

申请日：2022-09-15

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: B64D37/04 ,  B64C3/00 ,  B64C39/02 ,  B64D27/24 ,  H01M8/04007 ,  H01M8/04082 ,  H01M8/04089 ,  H01M8/12

CPC classification number: B64D37/04 ,  B64C3/00 ,  B64C39/024 ,  B64D27/24 ,  H01M8/04059 ,  H01M8/04074 ,  H01M8/04089 ,  H01M8/04216 ,  H01M8/12 ,  H01M2008/1293 ,  H01M2250/20

Abstract: In one embodiment, systems and methods include using an evaporator coil with a solid oxide fuel cell generator to generate energy for an aircraft vehicle. The system comprises a solid oxide fuel cell generator operable to generate energy. The system further comprises a first tank fluidly coupled to the solid oxide fuel cell generator configured to discharge a fluid to the solid oxide fuel cell generator and to receive the fluid from an evaporator coil coupled to the solid oxide fuel cell generator. The system further comprises a second tank fluidly coupled to the first tank and having a volume of the fluid, wherein the second tank is configured to discharge the fluid to the first tank, wherein the evaporator coil receives the discharged fluid from the second tank and increases the temperature of the discharged fluid prior to the first tank receiving the discharged fluid.

公开(公告)号：US10046850B2

公开(公告)日：2018-08-14

申请号：US15088615

申请日：2016-04-01

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble ,  Matthew Curran

IPC: B64C3/42 ,  B64C1/26 ,  B64C39/02

CPC classification number: B64C3/42 ,  B64C1/26 ,  B64C1/28 ,  B64C3/38 ,  B64C3/385 ,  B64C39/024 ,  B64C39/026 ,  B64C2201/028 ,  B64C2201/10

Abstract: An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle.

公开(公告)号：US20180118335A1

公开(公告)日：2018-05-03

申请号：US15338832

申请日：2016-10-31

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble ,  Gordon Jennings ,  Justin Neel

IPC: B64C29/00 ,  H02K7/14 ,  H02K7/02 ,  H02K11/33 ,  H02K11/21 ,  H02P3/02 ,  H02K7/00

Abstract: In one embodiment, a magnetic orientation detent includes a motor coupled to a motor shaft, the motor mechanically coupled to a motor mount. The magnetic orientation detent may also include a flywheel mechanically coupled to a distal end of the motor shaft. The magnetic orientation detent may further include a first plurality of magnets coupled to the motor mount and a second plurality of magnets coupled to the flywheel. The second plurality of magnets couple magnetically to the first plurality of magnets.

公开(公告)号：US20170283042A1

公开(公告)日：2017-10-05

申请号：US15085540

申请日：2016-03-30

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble

IPC: B64C17/04 ,  B64C27/10 ,  B64C11/28 ,  B64C27/14 ,  B64C25/34 ,  B64C25/66 ,  B64C39/02 ,  B64D47/08

CPC classification number: B64C17/04 ,  B64C11/28 ,  B64C25/34 ,  B64C25/66 ,  B64C27/10 ,  B64C27/14 ,  B64C27/52 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/127 ,  B64D47/08

Abstract: A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.