公开(公告)号：US11230389B2

公开(公告)日：2022-01-25

申请号：US15688037

申请日：2017-08-28

Applicant: Lockheed Martin Corporation

Inventor： Dustin E. Gamble ,  Matthew Curran

IPC: B64F1/02 ,  B64F1/08 ,  B64C11/46 ,  B64C39/02

Abstract: A method of capturing an aerial vehicle comprises rotating a first blade of the aerial vehicle, the first blade coupled to a hub of the aerial vehicle and having a contour configured to facilitate entanglement of a payload line of a winch system around the aerial vehicle. The method further comprises contacting, by a leading edge of the first blade, the payload line of the winch system and pulling the payload line towards the hub of the aerial vehicle, wherein the payload line is pulled towards the hub as the first blade continues to rotate and wherein continued rotation of the first blade causes the payload line to be tangled around the hub of the aerial vehicle.

公开(公告)号：US10814968B2

公开(公告)日：2020-10-27

申请号：US15447845

申请日：2017-03-02

Applicant: Lockheed Martin Corporation

Inventor： Dustin E. Gamble ,  Matthew Curran ,  Brian Miller

IPC: B64C27/39 ,  B64C27/48 ,  B64C27/50 ,  B64C27/10 ,  B64C39/02 ,  B64C17/04 ,  B64C27/52 ,  B64C25/32

Abstract: A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

公开(公告)号：US10519013B2

公开(公告)日：2019-12-31

申请号：US15444686

申请日：2017-02-28

Applicant: Lockheed Martin Corporation

Inventor： Matthew Curran ,  Dustin E. Gamble ,  Gordon Jennings ,  Justin Neel

IPC: B66D1/48 ,  B66D1/74 ,  B64D1/08 ,  B66D1/12 ,  B66D1/36

Abstract: A method for a winch system includes receiving, from a controller, instructions to spool a payload line, the payload line comprising a first end and a second end, the first end coupled to a main reel of the winch system and the second end configured to couple to a payload. The method further includes operating, based on the instructions, one or more of a first motor of the winch system and a second motor of the winch system, wherein the one or more of the first motor and the second motor are operated in order to control a position of the second end of the payload line.

公开(公告)号：US10384782B2

公开(公告)日：2019-08-20

申请号：US15444649

申请日：2017-02-28

Applicant: Lockheed Martin Corporation

Inventor： Matthew Curran ,  Dustin E. Gamble

IPC: B64D1/22 ,  B64C39/02 ,  G05D1/00 ,  B64D1/12 ,  B66D1/60

Abstract: A method for an airborne payload system includes receiving, from a sensor on a payload line, information about the payload line, wherein the payload line comprises a first end wound about a main reel of a winch system and a second end configured to couple to a payload. The method further includes providing instructions, based on the received information, to the unmanned aircraft and the winch system in order to control a position of the second end of the payload line.

公开(公告)号：US11667397B2

公开(公告)日：2023-06-06

申请号：US17582457

申请日：2022-01-24

Applicant: Lockheed Martin Corporation

Inventor： Dustin E. Gamble ,  Matthew Curran

IPC: B64F1/02 ,  B64F1/08 ,  B64C11/46 ,  B64C39/02 ,  B64U10/25 ,  B64U30/10 ,  B64U50/13 ,  B64U70/30

CPC classification number: B64F1/029 ,  B64C11/46 ,  B64C39/024 ,  B64F1/0295 ,  B64F1/08 ,  B64U10/25 ,  B64U30/10 ,  B64U50/13 ,  B64U70/30

Abstract: A method of capturing an aerial vehicle comprises rotating a first blade of the aerial vehicle, the first blade coupled to a hub of the aerial vehicle and having a contour configured to facilitate entanglement of a payload line of a winch system around the aerial vehicle. The method further comprises contacting, by a leading edge of the first blade, the payload line of the winch system and pulling the payload line towards the hub of the aerial vehicle, wherein the payload line is pulled towards the hub as the first blade continues to rotate and wherein continued rotation of the first blade causes the payload line to be tangled around the hub of the aerial vehicle.

公开(公告)号：US20180244509A1

公开(公告)日：2018-08-30

申请号：US15444686

申请日：2017-02-28

Applicant: Lockheed Martin Corporation

Inventor： Matthew Curran ,  Dustin E. Gamble ,  Gordon Jennings ,  Justin Neel

IPC: B66D1/48 ,  B66D1/12 ,  B66D1/36 ,  B64D1/08

Abstract: A method for a winch system includes receiving, from a controller, instructions to spool a payload line, the payload line comprising a first end and a second end, the first end coupled to a main reel of the winch system and the second end configured to couple to a payload. The method further includes operating, based on the instructions, one or more of a first motor of the winch system and a second motor of the winch system, wherein the one or more of the first motor and the second motor are operated in order to control a position of the second end of the payload line.

公开(公告)号：US20220144449A1

公开(公告)日：2022-05-12

申请号：US17582457

申请日：2022-01-24

Applicant: Lockheed Martin Corporation

Inventor： Dustin E. Gamble ,  Matthew Curran

IPC: B64F1/02 ,  B64F1/08 ,  B64C11/46 ,  B64C39/02

Abstract: A method of capturing an aerial vehicle comprises rotating a first blade of the aerial vehicle, the first blade coupled to a hub of the aerial vehicle and having a contour configured to facilitate entanglement of a payload line of a winch system around the aerial vehicle. The method further comprises contacting, by a leading edge of the first blade, the payload line of the winch system and pulling the payload line towards the hub of the aerial vehicle, wherein the payload line is pulled towards the hub as the first blade continues to rotate and wherein continued rotation of the first blade causes the payload line to be tangled around the hub of the aerial vehicle.

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：US20170320565A1

公开(公告)日：2017-11-09

申请号：US15447845

申请日：2017-03-02

Applicant: Lockheed Martin Corporation

Inventor： DUSTIN E. GAMBLE ,  Matthew Curran ,  Brian Miller

IPC: B64C27/39 ,  B64C27/10 ,  B64C39/02 ,  B64C27/48 ,  B64C27/50

CPC classification number: B64C27/39 ,  B64C17/04 ,  B64C27/10 ,  B64C27/48 ,  B64C27/50 ,  B64C27/52 ,  B64C39/024 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/165

Abstract: A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

公开(公告)号：US20170283033A1

公开(公告)日：2017-10-05

申请号：US15088615

申请日：2016-04-01

Applicant: Lockheed Martin Corporation

Inventor： Dustin Eli Gamble ,  Matthew Curran

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

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.