Patents by Inventor Daniel Zameroski
Daniel Zameroski has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11867123Abstract: An engine mount device includes a housing, a carrier within a cavity in the housing, and a flexure flexibly connecting the carrier to the housing, with a pin disposed in a hole in the carrier to support an engine. A method of providing isolation in the engine mount device includes transmitting a force from the pin into the carrier; mechanically isolating the carrier from the housing via the flexure; and providing, via the flexure, a higher stiffness in one or more radial directions of the hole compared to a stiffness provided in an axial direction of the hole.Type: GrantFiled: April 20, 2018Date of Patent: January 9, 2024Assignee: Lord CorporationInventor: Daniel Zameroski
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Patent number: 11306794Abstract: Devices, systems, and methods for damping vibration of a structural component or power-transmission shafts are disclosed. Damping devices, systems, and methods utilize a lightweight damping device, which is targeted at reducing the resonant amplitude of the first several beaming modes and/or torsional modes of bending a structural component comprising a hollow shaft or strut. The damping device includes a stiff concentric tube with damping elements disposed at each end. The device is inserted within the original structural component or shaft and attached thereto. When the primary shaft undergoes bending due to modal characteristics, the damping elements react to dissipate energy, which effectively reduces the resonant amplitude.Type: GrantFiled: May 11, 2016Date of Patent: April 19, 2022Assignee: LORD CorporationInventors: Gerald P. Whiteford, Daniel Zameroski
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Patent number: 10899462Abstract: Aft-mounting systems, devices, and methods for turboprop and turboshaft engines include two or more coupling elements 201, 211, 221 that are configured to couple an aft portion of an engine of an aircraft to a support structure of the aircraft. The two or more coupling elements are together configured to react forces generated in a vertical direction and in a lateral direction transverse to the engine but allow substantially unrestricted rotation of the engine with respect to the support structure about an axis of rotation of the engine.Type: GrantFiled: August 31, 2016Date of Patent: January 26, 2021Assignee: Lord CorporationInventors: Daniel Zameroski, Gerald Whiteford
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Patent number: 10829234Abstract: Aircraft isolator devices, systems, and methods for isolating a structural component within an aircraft can include an engine interface, airframe, and one or more (e.g., a plurality of) isolator devices attached to the engine interface and the airframe. In some aspects, the isolator devices have a housing, which has a first surface and a second surface that together at least partially define a perimeter of the housing and is configured for attachment to the airframe; an engine attachment component configured for attachment to the engine interface and disposed at least partially inside of the housing; and a plurality of elastomeric elements disposed on or over each of the first and second surfaces of the housing The plurality of elastomeric elements are spaced apart from the engine attachment component via the housing for improved heat dissipation from the engine, reducing operational temperatures of the elastomeric elements to prolong their use.Type: GrantFiled: May 12, 2017Date of Patent: November 10, 2020Assignee: LORD CorporationInventor: Daniel Zameroski
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Publication number: 20200123978Abstract: An engine mount device includes a housing, a carrier within a cavity in the housing, and a flexure flexibly connecting the carrier to the housing, with a pin disposed in a hole in the carrier to support an engine. A method of providing isolation in the engine mount device includes transmitting a force from the pin into the carrier; mechanically isolating the carrier from the housing via the flexure; and providing, via the flexure, a higher stiffness in one or more radial directions of the hole compared to a stiffness provided in an axial direction of the hole.Type: ApplicationFiled: April 20, 2018Publication date: April 23, 2020Inventor: Daniel ZAMEROSKI
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Patent number: 10494111Abstract: Aircraft support structures, systems, and methods are disclosed. In one embodiment, an aircraft system includes a rotating component and a support (e.g. strut) that supports the rotating component. The support includes a locking assembly (P1) that is configured to lock, automatically, an inner member (214) of the support with respect to an outer member (208) of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation. The aircraft support structures, systems, and methods herein utilize self-locking and self-unlocking supports (e.g. struts) for increasing or decreasing a stiffness of the support.Type: GrantFiled: September 12, 2016Date of Patent: December 3, 2019Assignee: LORD CorporationInventors: Benjamin Bozon, Alexandre Kursner, Baptiste Narbon, Daniel Zameroski
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Patent number: 10472080Abstract: An engine mount assembly for mounting an engine which produces a torque to a body having a persistent troublesome frequency vibration is disclosed. The engine mount assembly includes two fluid elastomeric chambers groundable to the body, an intermediate cradle link disposed between the two fluid chambers, a lateral link grounded to the body and the intermediate cradle, and a fluid conduit connecting the two fluid chambers. When subjected to torque a positive fluid pressure is generated within the fluid chambers and fluid conduit with the two fluid chambers share a plurality of loads while a transfer of the persistent troublesome frequency vibration from the body to the engine is inhibited.Type: GrantFiled: May 23, 2017Date of Patent: November 12, 2019Assignee: LORD CorporationInventor: Daniel Zameroski
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Publication number: 20190144124Abstract: Aircraft isolator devices, systems, and methods for isolating a structural component within an aircraft can include an engine interface, airframe, and one or more (e.g., a plurality of) isolator devices attached to the engine interface and the airframe. In some aspects, the isolator devices have a housing, which has a first surface and a second surface that together at least partially define a perimeter of the housing and is configured for attachment to the airframe; an engine attachment component configured for attachment to the engine interface and disposed at least partially inside of the housing; and a plurality of elastomeric elements disposed on or over each of the first and second surfaces of the housing The plurality of elastomeric elements are spaced apart from the engine attachment component via the housing for improved heat dissipation from the engine, reducing operational temperatures of the elastomeric elements to prolong their use.Type: ApplicationFiled: May 12, 2017Publication date: May 16, 2019Inventor: Daniel ZAMEROSKI
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Publication number: 20190009918Abstract: Aft-mounting systems, devices, and methods for turboprop and turboshaft engines include two or more coupling elements 201, 211, 221 that are configured to couple an aft portion of an engine of an aircraft to a support structure of the aircraft. The two or more coupling elements are together configured to react forces generated in a vertical direction and in a lateral direction transverse to the engine but allow substantially unrestricted rotation of the engine with respect to the support structure about an axis of rotation of the engine.Type: ApplicationFiled: August 31, 2016Publication date: January 10, 2019Applicant: LORD CorporationInventors: Daniel ZAMEROSKI, Gerald WHITEFORD
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Patent number: 10155594Abstract: The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.Type: GrantFiled: July 20, 2017Date of Patent: December 18, 2018Assignee: LORD CorporationInventors: Gerald P. Whiteford, Daniel Zameroski
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Publication number: 20180244395Abstract: Aircraft support structures, systems, and methods are disclosed. In one embodiment, an aircraft system includes a rotating component and a support (e.g. strut) that supports the rotating component. The support includes a locking assembly (P1) that is configured to lock, automatically, an inner member (214) of the support with respect to an outer member (208) of the support for stiffening the support in response to reaching or exceeding a predetermined threshold amount of displacement, load, stress, or rotation. The aircraft support structures, systems, and methods herein utilize self-locking and self-unlocking supports (e.g. struts) for increasing or decreasing a stiffness of the support.Type: ApplicationFiled: September 12, 2016Publication date: August 30, 2018Applicant: LORD CorporationInventors: Benjamin BOZON, Alexandre KURSNER, Baptiste NARBON, Daniel ZAMEROSKI
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Publication number: 20180094687Abstract: Devices, systems, and methods for damping vibration of a structural component or power-transmission shafts are disclosed. Damping devices, systems, and methods utilize a lightweight damping device, which is targeted at reducing the resonant amplitude of the first several beaming modes and/or torsional modes of bending a structural component comprising a hollow shaft or strut. The damping device includes a stiff concentric tube with damping elements disposed at each end. The device is inserted within the original structural component or shaft and attached thereto. When the primary shaft undergoes bending due to modal characteristics, the damping elements react to dissipate energy, which effectively reduces the resonant amplitude.Type: ApplicationFiled: May 11, 2016Publication date: April 5, 2018Inventors: Gerald P. WHITEFORD, Daniel ZAMEROSKI
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Publication number: 20170327239Abstract: The invention includes an aircraft engine mounting system for mounting an aircraft engine to an aircraft. The mounting system includes a yoke member having a first end and a second end, with an aircraft attachment between the first end and the second end, the aircraft attachment for interfacing the yoke member with the aircraft, the yoke member having a yoke member length (YL) from the first end to the second end. The mounting system preferably includes a first engine mount, the yoke member first end contained by the first engine mount, with the first engine mount having first engine mount housing grounded to the aircraft engine. The mounting system preferably includes a second engine mount, the yoke member second end contained by the second engine mount, with the second engine mount having a second engine mount housing grounded to the aircraft engine.Type: ApplicationFiled: July 20, 2017Publication date: November 16, 2017Inventors: Gerald P. WHITEFORD, Daniel ZAMEROSKI
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Publication number: 20170259930Abstract: In an embodiment the invention includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).Type: ApplicationFiled: May 23, 2017Publication date: September 14, 2017Inventor: Daniel ZAMEROSKI
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Patent number: 9745073Abstract: An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.Type: GrantFiled: November 18, 2016Date of Patent: August 29, 2017Assignee: LORD CorporationInventors: Gerald P. Whiteford, Daniel Zameroski
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Patent number: 9663235Abstract: In an embodiment the system includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).Type: GrantFiled: December 8, 2014Date of Patent: May 30, 2017Assignee: LORD CorporationInventor: Daniel Zameroski
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Publication number: 20170137140Abstract: An aircraft mounting system is provided having a yoke that is interlocked with engine mounts securable to the engine and the yoke is interchangeable with other yokes on other engines. An aft engine mount is also provided.Type: ApplicationFiled: November 18, 2016Publication date: May 18, 2017Inventors: Gerald P. WHITEFORD, Daniel ZAMEROSKI
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Patent number: 9527598Abstract: In an embodiment the invention includes an aircraft engine mounting system (20) for mounting an aircraft engine to an aircraft. The aircraft engine mounting system preferably includes an airframe structure member having a first engine end (28) and a distal second engine end (30), with an aircraft attachment between the first engine end and the distal second engine end, the aircraft attachment for interfacing the airframe structure member with the aircraft, the airframe structure member having an airframe structure member length (YL) from the first engine end to the distal second engine end. The aircraft engine mounting system preferably includes a first engine attachment structure member (36), the airframe structure member first engine end (28) contained by the first engine attachment structure member, with the first engine attachment structure member having an outer engine mount member (38) grounded to the aircraft engine.Type: GrantFiled: January 26, 2010Date of Patent: December 27, 2016Assignee: LORD CorporationInventors: Gerald P. Whiteford, Daniel Zameroski
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Publication number: 20160130008Abstract: In an embodiment the invention includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).Type: ApplicationFiled: December 8, 2014Publication date: May 12, 2016Inventor: Daniel ZAMEROSKI
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Patent number: 8905368Abstract: In an embodiment the invention includes a method of mounting an engine in a rotary wing aircraft. The method includes providing a rotary wing aircraft having an aircraft body supported in flight through an exterior air space by a rotary wing system rotating with an operational rotating frequency (P) with a plurality of (N) rotary wings, the rotary wing aircraft body having a persistent in flight operational rotating frequency vibration. The method includes providing a first engine, the first engine for providing power to rotate the rotary wing system at the rotary wing system operational rotating frequency (P).Type: GrantFiled: June 14, 2011Date of Patent: December 9, 2014Assignee: LORD CorporationInventor: Daniel Zameroski