公开(公告)号：US11498671B2

公开(公告)日：2022-11-15

申请号：US16690447

申请日：2019-11-21

Applicant: LOCKHEED MARTIN CORPORATION

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

IPC: B64C27/46 ,  B64F5/40

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：US20210323660A1

公开(公告)日：2021-10-21

申请号：US16850682

申请日：2020-04-16

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Frank M. Caputo ,  Timothy James Conti ,  Claude G. Matalanis

IPC: B64C27/473

Abstract: A rotor blade of a rotary wing aircraft includes a core defining a trailing edge of the rotor blade and a skin extending from the trailing edge defining an opening including the core. The skin defines an aerodynamic surface of the rotor blade. The rotor blade additionally includes at least one trim tab assembly including a trim portion extending from the core beyond the trailing edge of the rotor blade and an actuation system including at least one actuator disposed within the core. The actuation system is operable to adjust an angle of the trim portion relative to the rotor blade.

公开(公告)号：US20250010983A1

公开(公告)日：2025-01-09

申请号：US18887678

申请日：2024-09-17

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

Abstract: A rotor blade includes a spar with forward end, an aft end, and a substantially oval cross-section. The cross-section includes an upper portion tapering from a first thickness to a smaller, second thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end, and a lower portion tapering from a third thickness to a smaller, fourth thickness beginning between about 55% and about 65% of the distance to the aft end from the forward end and ending between about 65% and about 75% of the distance to the aft end measured from the forward end. The rotor blade further includes an upper blade skin, a lower blade skin, and a leading edge sheath.

公开(公告)号：US12110104B2

公开(公告)日：2024-10-08

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：US20240140600A1

公开(公告)日：2024-05-02

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

CPC classification number: 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：US20240043116A1

公开(公告)日：2024-02-08

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：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：US20230054703A1

公开(公告)日：2023-02-23

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

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：US11325695B2

公开(公告)日：2022-05-10

申请号：US16850682

申请日：2020-04-16

Applicant: LOCKHEED MARTIN CORPORATION

Inventor： Frank M. Caputo ,  Timothy James Conti ,  Claude G. Matalanis

IPC: B64C27/473 ,  B64C27/00 ,  B64C27/72

Abstract: A rotor blade of a rotary wing aircraft includes a core defining a trailing edge of the rotor blade and a skin extending from the trailing edge defining an opening including the core. The skin defines an aerodynamic surface of the rotor blade. The rotor blade additionally includes at least one trim tab assembly including a trim portion extending from the core beyond the trailing edge of the rotor blade and an actuation system including at least one actuator disposed within the core. The actuation system is operable to adjust an angle of the trim portion relative to the rotor blade.