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公开(公告)号：US20200247534A1
公开(公告)日：2020-08-06
申请号：US16267517
申请日：2019-02-05
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： Byung-Young Min , Patrick Ormande Bowles , Brian Ernest Wake , Margaret G. Battisti , Peter F. Lorber
Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.
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公开(公告)号：US12202596B2
公开(公告)日：2025-01-21
申请号：US17834550
申请日：2022-06-07
Applicant: Lockheed Martin Corporation
Inventor： Colin Kemater Bunting , Patrick Ormande Bowles , Peter F. Lorber , Brian Ernest Wake , Byung-Young Min
Abstract: A rotor assembly including a fixed fairing including an interface portion and a hub fairing including a depression. The depression is configured to receive at least a portion of the interface portion. The hub fairing is rotatable relative to the fixed fairing.
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Patent Agency Ranking
公开(公告)号：US11370532B2
公开(公告)日：2022-06-28
申请号：US16431341
申请日：2019-06-04
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： Patrick Ormande Bowles , Margaret G. Battisti , Brian Ernest Wake , Peter F. Lorber , Byung-Young Min
Abstract: A rotary wing aircraft and a rotor assembly of a rotary wind aircraft is disclosed. The rotary wing aircraft includes at least one engine, and the rotor assembly is coupled to the at least one engine. The rotor assembly includes a first rotor hub, a second rotor hub, and a shaft fairing between the first rotor hub to the second rotor hub, the shaft fairing defined by a chord that varies between the first rotor hub and the second rotor hub.
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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.
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公开(公告)号：US11174011B2
公开(公告)日：2021-11-16
申请号：US16267517
申请日：2019-02-05
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： Byung-Young Min , Patrick Ormande Bowles , Brian Ernest Wake , Margaret G. Battisti , Peter F. Lorber
Abstract: A rotor assembly includes a first rotor hub and a second rotor hub. The second rotor hub is coupled to the first rotor hub via a shaft fairing. The first rotor hub has a flat first surface coupled to the shaft fairing and a curved second surface opposite the flat first surface. The second rotor hub has a flat first surface on the lower side and a curved second surface opposite the flat first surface.
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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.
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公开(公告)号：US20230391448A1
公开(公告)日：2023-12-07
申请号：US17834550
申请日：2022-06-07
Applicant: Lockheed Martin Corporation
Inventor： Colin Kemater Bunting , Patrick Ormande Bowles , Peter F. Lorber , Brian Ernest Wake , Byung-Young Min
Abstract: A rotor assembly including a fixed fairing including an interface portion and a hub fairing including a depression. The depression is configured to receive at least a portion of the interface portion. The hub fairing is rotatable relative to the fixed fairing.
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