公开(公告)号：US11794887B1

公开(公告)日：2023-10-24

申请号：US17714572

申请日：2022-04-06

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Matthew Walter DiPalma ,  Timothy James Conti ,  Claude George Matalanis

IPC: B64C27/467 ,  B64C27/64 ,  B64C27/57 ,  B64C27/473

CPC classification number: B64C27/467 ,  B64C27/473 ,  B64C27/57 ,  B64C27/64

Abstract: A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.

公开(公告)号：US12116119B2

公开(公告)日：2024-10-15

申请号：US17706531

申请日：2022-03-28

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Byung-Young Min ,  Vera Klimchenko ,  Annie Gao ,  Alexander F. Dunn ,  Claude George Matalanis ,  Brian Ernest Wake

IPC: B64C27/46 ,  B64C27/467 ,  B64C27/473

CPC classification number: B64C27/467 ,  B64C27/473

Abstract: A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

公开(公告)号：US12030624B2

公开(公告)日：2024-07-09

申请号：US17485192

申请日：2021-09-24

Applicant: Lockheed Martin Corporation

Inventor： Eric S. Parsons ,  Christopher Michael Colschen ,  Claude George Matalanis ,  Benjamin Edward Isabella ,  Marc A. Antonetz ,  Timothy James Conti ,  Frank M. Caputo

IPC: B64C27/473 ,  H02B1/20 ,  H02B1/26 ,  H02B1/30 ,  H02G15/007 ,  H02G15/06 ,  H02G15/18

CPC classification number: B64C27/473 ,  H02B1/202 ,  H02B1/26 ,  H02B1/305 ,  H02G15/007 ,  H02G15/06 ,  H02G15/1833

Abstract: An electrical conductor assembly for a rotor blade includes a substrate and at least one electrical conductor. The substrate includes an inboard end portion and an outboard end portion. The at least one electrical conductor is attached to the substrate and extends between the inboard end portion and the outboard end portion. The at least one electrical conductor is configured to transmit electricity along a length of the rotor blade. The inboard end portion and the outboard end portion are structured such that when the electrical conductor assembly is installed within the rotor blade, the inboard end portion is securable relative to the rotor blade and the outboard end portion is movable relative to the rotor blade.

公开(公告)号：US20230322374A1

公开(公告)日：2023-10-12

申请号：US17714572

申请日：2022-04-06

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Matthew Walter DiPalma ,  Timothy James Conti ,  Claude George Matalanis

IPC: B64C27/467 ,  B64C27/473 ,  B64C27/57 ,  B64C27/64

CPC classification number: B64C27/467 ,  B64C27/473 ,  B64C27/57 ,  B64C27/64

Abstract: A rotor blade assembly for a rotary wing aircraft includes a main rotor blade body comprising an upper blade skin, a lower blade skin, an inboard end, an outboard end, and a trailing edge. The rotor blade assembly further includes a trailing edge actuator assembly. The trailing edge actuator assembly includes an upper actuator skin and a lower actuator skin defining a cavity and a trailing edge flap, a control panel disposed in the cavity and coupled to one of the upper actuator skin or the lower actuator skin and one or more actuators disposed in the cavity and configured to apply force to the control panel to cause the trailing edge flap to deflect. The trailing edge actuator assembly is coupled to the trailing edge of the main rotor blade body.

公开(公告)号：US20230322373A1

公开(公告)日：2023-10-12

申请号：US17706531

申请日：2022-03-28

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Byung-Young Min ,  Vera Klimchenko ,  Annie Gao ,  Alexander F. Dunn ,  Claude George Matalanis ,  Brian Ernest Wake

IPC: B64C27/473 ,  B64C27/467

CPC classification number: B64C27/467 ,  B64C27/473

Abstract: A rotary wing aircraft includes a single main rotor hub configured to receive a rotor blade. The rotor blade includes a blade root, a blade tip, and a blade body. The blade body includes a leading edge and a trailing edge and defines a feathering axis. The leading edge and the trailing edge each include a first portion and a second portion that extend toward a first direction and a second portion, respectively. At a given radial location along the feathering axis, a local twist angle changes from a positive value to a negative value, a chord length decreases in value, a distance between the trailing edge and the feathering axis decreases in value, and the first portion of the leading edge extends toward the first direction. The rotor blade assembly also includes a trailing edge assembly having a trailing edge flap configured to be selectively deployed by an actuator.

公开(公告)号：US20240326994A1

公开(公告)日：2024-10-03

申请号：US18744276

申请日：2024-06-14

Applicant: Lockheed Martin Corporation

Inventor： Eric S. Parsons ,  Christopher Michael Colschen ,  Claude George Matalanis ,  Benjamin Edward Isabella ,  Marc A. Antonetz ,  Timothy James Conti ,  Frank M. Caputo

IPC: B64C27/473 ,  H02B1/20 ,  H02B1/26 ,  H02B1/30 ,  H02G15/007 ,  H02G15/06 ,  H02G15/18

CPC classification number: B64C27/473 ,  H02B1/202 ,  H02B1/26 ,  H02B1/305 ,  H02G15/007 ,  H02G15/06 ,  H02G15/1833

Abstract: A method of manufacturing an electrical conductor assembly includes attaching a substrate and at least one electrical conductor to a cable assembly machine, tensioning the substrate, and holding the substrate stationary while wrapping the at least one electrical conductor around the substrate. The at least one electrical conductor is wrapped around the substrate independent of the tension on the substrate.

公开(公告)号：US20230098029A1

公开(公告)日：2023-03-30

申请号：US17485192

申请日：2021-09-24

Applicant: Lockheed Martin Corporation

Inventor： Eric S. Parsons ,  Christopher Michael Colschen ,  Claude George Matalanis ,  Benjamin Edward Isabella ,  Marc A. Antonetz ,  Timothy James Conti ,  Frank M. Caputo

IPC: B64C27/68 ,  H01B7/18 ,  H02G15/007 ,  H02G15/06 ,  H01B13/22

Abstract: An electrical conductor assembly for a rotor blade includes a substrate and at least one electrical conductor. The substrate includes an inboard end portion and an outboard end portion. The at least one electrical conductor is attached to the substrate and extends between the inboard end portion and the outboard end portion. The at least one electrical conductor is configured to transmit electricity along a length of the rotor blade. The inboard end portion and the outboard end portion are structured such that when the electrical conductor assembly is installed within the rotor blade, the inboard end portion is securable relative to the rotor blade and the outboard end portion is movable relative to the rotor blade.