公开(公告)号：US12037108B2

公开(公告)日：2024-07-16

申请号：US17977965

申请日：2022-10-31

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Joseph Pantalone, III ,  Timothy James Conti ,  Daniel Caleb Sargent ,  Benjamin Edward Isabella ,  Masruk Siddique

IPC: B64C27/46 ,  B64F5/40

CPC classification number: B64C27/463 ,  B64F5/40 ,  Y10T29/49732

Abstract: A replacement tip section for a rotor blade, from which a legacy tip section was removed, includes a blade tip portion configured to be attached to an intermediate section of the rotor blade after removal of the legacy section. The intermediate section has a connection feature at an end of the intermediate section to which the blade tip portion is attachable. The replacement tip section includes a transition region configured to be attached to a forward end of the connection feature. The transition region is configured to form a leading edge of the rotor blade and extends from the blade tip portion to form an opening into which the intermediate section is attached. The transition region includes a first end having a first airfoil that conforms to the intermediate section airfoil at the connection feature, and a second end having a second airfoil that conforms to the blade tip portion.

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：US11919627B2

公开(公告)日：2024-03-05

申请号：US17881497

申请日：2022-08-04

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Timothy James Conti ,  Frank M. Caputo

IPC: B64C27/48

CPC classification number: B64C27/48

Abstract: A method of modifying a rotor blade is provided for a rotor blade including a spar having an inboard portion with a substantially constant overall height, the inboard portion further including a top layer having a substantially constant first thickness and a bottom layer having a substantially constant second thickness. The method includes removing a root portion of the inboard portion to thereby modify the rotor blade and installing a cuff configured to couple to the rotor blade to an aircraft.

公开(公告)号：US12252240B2

公开(公告)日：2025-03-18

申请号：US18409652

申请日：2024-01-10

Applicant: Lockheed Martin Corporation

Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Timothy James Conti ,  Frank M. Caputo

IPC: B64C27/48

Abstract: A rotor blade configured to be installed on a rotary wing aircraft includes a spar including an inboard portion extending from a root of the rotor blade to a first spanwise position of the rotor blade and an outboard portion meeting the inboard portion at the first spanwise position. The rotor blade further includes an upper skin and a lower skin coupled the outboard portion of the spar. The first spanwise position is defined by a most inboard point at which the upper and lower skins are coupled to the spar. The inboard portion includes a top layer, a bottom layer, and an inner cavity. The top layer has a substantially constant first thickness and the bottom layer has a substantially constant second thickness, and the distance between an outer surface of the top layer and an outer surface of the bottom layer is substantially constant.

公开(公告)号：US12214872B2

公开(公告)日：2025-02-04

申请号：US18132330

申请日：2023-04-07

Applicant: Lockheed Martin Corporation

Inventor： Timothy James Conti ,  Eric S. Parsons ,  Joshua A. Breon ,  Benjamin E. Isabella ,  William Paul Adams ,  Christopher Michael Colschen

IPC: B64C27/46 ,  B64C27/473

Abstract: A rotor blade configured to be installed on a rotary-wing aircraft includes a main blade body including an inboard end configured to be coupled to a rotor blade hub and an outboard end. The rotor blade includes a blade tip removably coupled to the outboard end of the main blade body, the blade tip including an inner cavity. The rotor blade further includes a tip block including an inboard portion coupled to the outboard end of the main blade body and a cantilevered portion extending beyond the outboard end of the rotor blade and into the inner cavity of the blade tip.

公开(公告)号：US20240336357A1

公开(公告)日：2024-10-10

申请号：US18132330

申请日：2023-04-07

Applicant: Lockheed Martin Corporation

Inventor： Timothy James Conti ,  Eric S. Parsons ,  Joshua A. Breon ,  Benjamin E. Isabella ,  William Paul Adams ,  Christopher Michael Colschen

IPC: B64C27/46 ,  B64C27/473

CPC classification number: B64C27/463 ,  B64C27/473

Abstract: A rotor blade configured to be installed on a rotary-wing aircraft includes a main blade body including an inboard end configured to be coupled to a rotor blade hub and an outboard end. The rotor blade includes a blade tip removably coupled to the outboard end of the main blade body, the blade tip including an inner cavity. The rotor blade further includes a tip block including an inboard portion coupled to the outboard end of the main blade body and a cantilevered portion extending beyond the outboard end of the rotor blade and into the inner cavity of the blade tip.

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：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：US20240067333A1

公开(公告)日：2024-02-29

申请号：US17900780

申请日：2022-08-31

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Joshua A. Breon ,  Eric S. Parsons ,  Christopher M. Sutton ,  William Paul Adams ,  Timothy James Conti ,  Jared Anapolle ,  Evan Medrano

IPC: B64C27/467 ,  B64C27/473

CPC classification number: B64C27/467 ,  B64C27/473

Abstract: A rotor blade for a rotary wing aircraft includes a leading edge and a trailing edge defining a chordwise direction. The leading edge defines a forward end of the rotor blade and the trailing edge defines an aft end of the rotor blade. The rotor blade has a center of gravity and an aerodynamic center along the chordwise direction. The center of gravity is aft of the aerodynamic center.

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.