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公开(公告)号：US20230249811A1
公开(公告)日：2023-08-10
申请号：US17665432
申请日：2022-02-04
Applicant: Lockheed Martin Corporation
Inventor： Evan S. Tobin , Daniel George Schuster , David N. Schmaling , Evan Medrano , Masruk Siddique , Erik M. Byrne , James Orbon
CPC classification number: B64C27/48 , B64C27/10 , B64C27/35 , B64C27/327
Abstract: A rotor blade retention assembly is configured to connect a rotor blade to a central hub comprising a hub arm coupled to and extending radially outward from a hub bowl. The hub arm includes a hub arm lug. The rotor blade retention assembly includes a tension-torsion strap with an inboard end and an outboard end, the inboard end including an inboard pin hole and the outboard end including an outboard pin hole. The rotor blade retention assembly further includes an inboard blade pin and an outboard blade pin. The inboard blade pin is configured to extend through the hub arm lug and the inboard pin hole and to couple the inboard end of the tension-torsion strap to the hub arm. The outboard blade pin is configured to extend through a blade lug of a rotor blade and the outboard pin hole and to couple the outboard end of the tension-torsion strap to the rotor blade.
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公开(公告)号：US20230136833A1
公开(公告)日：2023-05-04
申请号：US17518370
申请日：2021-11-03
Applicant: Lockheed Martin Corporation
Inventor： Daniel George Schuster , Evan S. Tobin , David N. Schmaling
Abstract: A rotor blade retention assembly includes a central hub, a rotor blade including an upper outer surface, a lower outer surface, a blade hole, and a proximal end coupled to the central hub, a strap member extending along a portion of the rotor blade such that a distal end receiving portion extends into the blade hole, and a retainer assembly disposed within the blade hole and coupled to the strap member. The retainer assembly includes an upper bushing and a lower bushing slidably disposed within the blade hole. The upper bushing includes a counterbored portion. The retainer assembly also includes an outboard blade pin disposed within the distal end receiving portion and includes a blade pin inner cavity.
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Patent Agency Ranking
公开(公告)号：US11772784B2
公开(公告)日：2023-10-03
申请号：US16933019
申请日：2020-07-20
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： James Breen Orbon , James McCollough , Evan S. Tobin , Xiaole Xie , Jonathan Frydman
CPC classification number: B64C27/46 , B64C27/12 , B64D13/006 , B64C2027/8272
Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.
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公开(公告)号：US20220017214A1
公开(公告)日：2022-01-20
申请号：US16933019
申请日：2020-07-20
Applicant: LOCKHEED MARTIN CORPORATION
Inventor： James Breen Orbon , James McCollough , Evan S. Tobin , Xiaole Xie , Jonathan Frydman
Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.
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公开(公告)号：US20250074583A1
公开(公告)日：2025-03-06
申请号：US18239711
申请日：2023-08-29
Applicant: Lockheed Martin Corporation
Inventor： Daniel George Schuster , David N. Schmaling , Evan S. Tobin , Eric M. Bogert
Abstract: A rotor assembly for a rotary wing aircraft includes a rotor hub including a hub arm and a central opening. The rotor assembly further includes a hydraulic actuation cylinder positioned in the central opening, a pitch change shaft assembly including a pitch change shaft positioned partially within the hydraulic actuation cylinder, a pitch beam coupled to a distal end of the pitch change shaft and configured to be coupled to a rotor blade rotatably mounted to the hub arm. The rotor assembly additionally includes at least one guide rod coupled to the rotor hub and slidably coupled to an opening in the pitch change shaft.
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公开(公告)号：US11999472B2
公开(公告)日：2024-06-04
申请号：US17518370
申请日：2021-11-03
Applicant: Lockheed Martin Corporation
Inventor： Daniel George Schuster , Evan S. Tobin , David N. Schmaling
CPC classification number: B64C27/48 , B64C27/10 , B64C27/35 , B64C27/26 , B64C2027/8236 , B64C2027/8272 , B64C2027/8281
Abstract: A rotor blade retention assembly includes a central hub, a rotor blade including an upper outer surface, a lower outer surface, a blade hole, and a proximal end coupled to the central hub, a strap member extending along a portion of the rotor blade such that a distal end receiving portion extends into the blade hole, and a retainer assembly disposed within the blade hole and coupled to the strap member. The retainer assembly includes an upper bushing and a lower bushing slidably disposed within the blade hole. The upper bushing includes a counterbored portion. The retainer assembly also includes an outboard blade pin disposed within the distal end receiving portion and includes a blade pin inner cavity.
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公开(公告)号：US20240017824A1
公开(公告)日：2024-01-18
申请号：US18373172
申请日：2023-09-26
Applicant: Lockheed Martin Corporation
Inventor： James Breen Orbon , James McCollough , Evan S. Tobin , Xiaole Xie , Jonathan Frydman
CPC classification number: B64C27/46 , B64D13/006 , B64C27/12 , B64C2027/8272
Abstract: A propeller system for a tail section of an aircraft includes a propeller hub located at the tail section of the aircraft, a plurality of propeller blades mounted to and extending outwardly from the propeller hub, a propeller shaft coupled to the propeller hub and operable to rotate the propeller hub about an axis of rotation, and a propeller gearbox connected to the propeller shaft. The propeller gearbox is fluidly cooled by an airflow within the tail section. A spinner assembly surrounds the propeller hub. The spinner assembly includes at least one outlet opening formed therein downstream from the propeller hub relative to the airflow. The spinner assembly is rotatable to draw the airflow into at least one cooling flow inlet formed in the tail section and across the propeller gearbox to cool the propeller gearbox and out the at least one outlet opening.
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