Patents by Inventor Jeffrey G. Sauer
Jeffrey G. Sauer 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: 10696413Abstract: A heater mat assembly for a rotor blade spar is provided including a plurality of electrically conductive heater wires extending in a spaced parallel configuration along a path of the rotor blade spar. An electrical current is flowed through the plurality of heater wires to inhibit ice accumulation on a portion of the rotor blade spar. At least one layer of a first insulating material is arranged adjacent a first side of each of the plurality of heater wires such that the at least one layer of the first insulating material is disposed between the plurality of heater wires and an adjacent surface of the rotor blade spar. The first insulating material comprises a thermally and electrically insulating material.Type: GrantFiled: August 27, 2015Date of Patent: June 30, 2020Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Robert A. Lacko, Joseph B. Ozelski, David P. Baranowski, Jeffrey G. Sauer, Frank Caputo
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Publication number: 20190186184Abstract: A pin of a hinge system movable between a first position and a second position is provided, wherein in the first position, the pin is received within a first component and a second component. The pin includes a cylindrical body coupled to an actuator for movement along an axis between the first position and the second position. A tip is removably attached to an end of the cylindrical body. The tip is configured to contact at least one of the first component and the second component when the pin is in the first position.Type: ApplicationFiled: February 11, 2019Publication date: June 20, 2019Inventors: Jonathan Bremmer, Darryl Mark Toni, David J. Goldschmidt, James S. Giampapa, Jeffrey G. Sauer
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Patent number: 10247273Abstract: A composite wrap is provided for damping vibration in an elongated quill shaft having a cylindrical body. The composite wrap includes interior layering for disposition about a cylindrical body, exterior layering configured to define an exterior composite wrap shape and sequential cured-in-place, vibration damping, fibrous epoxy layers. The sequential cured-in-place, vibration damping, fibrous epoxy layers are radially interposed between the interior and exterior layering to dampen vibrations of and/or to adjust a resonance frequency of the cylindrical body.Type: GrantFiled: June 13, 2016Date of Patent: April 2, 2019Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Jeffrey G. Sauer, Robert A. Lacko, Shihong G. Song, John H. Meeson, Jr.
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Publication number: 20180094467Abstract: A pin of a hinge system movable between a first position and a second position is provided, wherein in the first position, the pin is received within a first component and a second component. The pin includes a cylindrical body coupled to an actuator for movement along an axis between the first position and the second position. A tip is removably attached to an end of the cylindrical body. The tip is configured to contact at least one of the first component and the second component when the pin is in the first position.Type: ApplicationFiled: December 11, 2015Publication date: April 5, 2018Inventors: Jonathan Bremmer, Darryl Mark Toni, David J. Goldschmidt, James S. Giampapa, Jeffrey G. Sauer
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Publication number: 20180065277Abstract: A method of manufacturing a fabricated part having complex geometry is provided. The method includes generating a digital model of a tooling having a complex geometry; additively manufacturing a tooling based on the digital model from tooling material; laying-up fabrication materials on the tooling; curing the fabrication materials on the tooling to form a fabricated part; and removing the tooling from the fabricated part.Type: ApplicationFiled: January 22, 2016Publication date: March 8, 2018Inventors: Jonathan Bremmer, Darryl Mark Toni, Jeffrey G. Sauer, Robert A. Lacko, Juan J. Prieto, JR., Christopher John Foti
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Patent number: 9776385Abstract: A tool for forming a panel including a core area, at which plies sandwich a core, and a trim area surrounding the core, at which the plies are bonded together, is provided and includes a body having a surface on which the panel is formable, an assembly to apply bonding pressure to the plies at least at the core and trim areas and a clamping device external to the assembly to apply a clamping force to the vacuum bag and the plies.Type: GrantFiled: April 5, 2011Date of Patent: October 3, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Jeffrey G. Sauer, III, William E. Hovan, III, Christian A. Rogg, Paul H. Denavit, Robert A. Lacko, Neil W. Cawthra
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Publication number: 20170275006Abstract: A heater mat assembly for a rotor blade spar is provided including a plurality of electrically conductive heater wires extending in a spaced parallel configuration along a path of the rotor blade spar. An electrical current is flowed through the plurality of heater wires to inhibit ice accumulation on a portion of the rotor blade spar. At least one layer of a first insulating material is arranged adjacent a first side of each of the plurality of heater wires such that the at least one layer of the first insulating material is disposed between the plurality of heater wires and an adjacent surface of the rotor blade spar. The first insulating material comprises a thermally and electrically insulating material.Type: ApplicationFiled: August 27, 2015Publication date: September 28, 2017Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Robert A. Lacko, Joseph B. Ozelski, David P. Baranowski, Jeffrey G. Sauer, Frank Caputo
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Publication number: 20170058990Abstract: A composite wrap is provided for damping vibration in an elongated quill shaft having a cylindrical body. The composite wrap includes interior layering for disposition about a cylindrical body, exterior layering configured to define an exterior composite wrap shape and sequential cured-in-place, vibration damping, fibrous epoxy layers. The sequential cured-in-place, vibration damping, fibrous epoxy layers are radially interposed between the interior and exterior layering to dampen vibrations of and/or to adjust a resonance frequency of the cylindrical body.Type: ApplicationFiled: June 13, 2016Publication date: March 2, 2017Inventors: Jonathan Bremmer, Jeffrey G. Sauer, Robert A. Lacko, Shihong G. Song, John H. Meeson
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Patent number: 9539769Abstract: A composite structure includes a first laminate, a second laminate, and at least one core component located between the first laminate and the second laminate. The at least one core component includes a honeycomb core and at least one locking ply extending from the honeycomb core between the first laminate and the second laminate. The at least one locking ply is configured such that a pressure applied during a cure cycle of the composite structure retains the at least one locking ply between the first laminate and the second laminate thereby preventing movement of core component.Type: GrantFiled: October 17, 2011Date of Patent: January 10, 2017Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Jeffrey G. Sauer, Edward Joseph Fabian, Paul H. Denavit, Darryl Mark Toni, William E. Hovan, III
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Publication number: 20160375668Abstract: A method of forming a sandwich composite structure by placing a core under a compressive force or a tensile force and applying a first layer to a first surface of the core. The core and first layer are then heated. The compressive or tensile force is then released, allowing the composite structure to take shape.Type: ApplicationFiled: May 5, 2015Publication date: December 29, 2016Inventors: Jonathan Bremmer, Robert A. Lacko, Jeffrey G. Sauer, Darryl Mark Toni
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Patent number: 9427940Abstract: A composite panel includes a support layer including a first plurality of prepreg plies wrapped around at least one mandrel; a mid-plane impact layer including a second plurality of prepreg plies, the mid-plane impact layer adjacent to the support layer; a upper skin layer including a third plurality of prepreg plies, the upper skin layer adjacent to the mid-place impact layer; and a lower skin layer including a fourth plurality of prepreg plies, the lower skin layer adjacent to the support layer; whereby each of the first, second, third, and fourth plurality of prepreg plies are co-cured to form the composite panel.Type: GrantFiled: November 12, 2013Date of Patent: August 30, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Darryl Mark Toni, William E. Hovan, III, Allan R. Macallister, Jr., Jeffrey G. Sauer, Christian A. Rogg, Robert A. Lacko, David M. Lent, Andrew Varga
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Patent number: 9409358Abstract: A composite structure includes a first laminate and a second laminate. At least one core assembly is located between the first laminate and the second laminate. The at least one core assembly includes a core component and a layer of filler material disposed at a first face of the core component. The layer of filler material at least partially fills selected cells of the core component to a fill depth such that the filler material rigidizes when cured to prevent movement and/or crushing of core component under a pressure applied during a cure cycle of the composite structure.Type: GrantFiled: October 15, 2012Date of Patent: August 9, 2016Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Darryl Mark Toni, Jeffrey G. Sauer, Edward Joseph Fabian, Paul H. Denavit, William E. Hovan, III, Gregory A. Davidson
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Patent number: 9192985Abstract: A composite core for forming a passage in an investment casting mold is provided including a core element. A generally hollow structural element is positioned about an exterior of the core element. The structural element is configured to deform when a force is applied to the structural element. A rigid shell element is integrally formed about the structural element. The shell element is configured to break when the structural element deforms.Type: GrantFiled: October 7, 2013Date of Patent: November 24, 2015Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Shihong G. Song, Jeffrey G. Sauer, James S. Giampapa
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Patent number: 9162419Abstract: A laminate design is provided and includes a substrate formed to define through-holes, an initially uncured pre-preg laminate disposed proximate to the substrate and an initially uncured pre-preg staple. The staple includes a main member and legs extending from the main member and being disposable with the legs extending through the through-holes to pierce the laminate. The staple is co-curable with the laminate.Type: GrantFiled: October 2, 2013Date of Patent: October 20, 2015Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Darryl Mark Toni, Jeffrey G. Sauer, William E. Hovan, Christian A. Rogg, Andrew Varga, David M. Lent, Robert A. Lacko, Allan R. Macallister
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Patent number: 9114586Abstract: A caul system for a composite structure having one or more core elements includes a lattice grid hard caul selectively locatable at a portion of the composite structure without core elements. The caul system further includes a soft caul selectively locatable at a portion of the composite structure having a core element. A method of forming a composite structure with one or more core elements includes locating a first laminate in a tool and locating one or more core elements over the first laminate. A second laminate is located over the one or more core elements. A lattice grid hard caul is placed over the second laminate, avoiding locations having core elements of the one or more core elements disposed thereat. A soft caul is located over the one or more core elements, thereby preventing deformation of the one or more core elements.Type: GrantFiled: February 9, 2012Date of Patent: August 25, 2015Assignee: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Paul H. Denavit, Edward Joseph Fabian, Jeffrey G. Sauer, William E. Hovan, III, Darryl Mark Toni
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Publication number: 20150136308Abstract: A kit for repairing an opening formed in a composite panel having a laminate skin arranged on opposing sides of a first core material is provided including a plug and a patch. The plug is formed from a second core material and has a cured filler material arranged within at least a portion of the second core material. The patch is formed from a plurality of cured first plies arranged in a stacked orientation. The plug is configured to be received within the opening of the composite panel and the patch is configured to cover the opening of the composite panel.Type: ApplicationFiled: November 21, 2013Publication date: May 21, 2015Applicant: Sikorsky Aircraft CorporationInventors: Jonathan Bremmer, Christian A. Rogg, Jeffrey G. Sauer, Darryl Mark Toni, Allan R. Macallister, Jr., William E. Hovan, III, Paul H. Denavit, Mihail Sirbu
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Publication number: 20150133016Abstract: A composite panel includes a support layer including a first plurality of prepreg plies wrapped around at least one mandrel; a mid-plane impact layer including a second plurality of prepreg plies, the mid-plane impact layer adjacent to the support layer; a upper skin layer including a third plurality of prepreg plies, the upper skin layer adjacent to the mid-place impact layer; and a lower skin layer including a fourth plurality of prepreg plies, the lower skin layer adjacent to the support layer; whereby each of the first, second, third, and fourth plurality of prepreg plies are co-cured to form the composite panel.Type: ApplicationFiled: November 12, 2013Publication date: May 14, 2015Applicant: Sikorsky Aircraft CorporationInventors: Jonathan Bremmer, Darryl Mark Toni, William E. Hovan, III, Allan R. Macallister, JR., Jeffrey G. Sauer, Christian A. Rogg, Robert A. Lacko, David M. Lent, Andrew Varga
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Publication number: 20150096711Abstract: A composite core for forming a passage in an investment casting mold is provided including a core element. A generally hollow structural element is positioned about an exterior of the core element. The structural element is configured to deform when a force is applied to the structural element. A rigid shell element is integrally formed about the structural element. The shell element is configured to break when the structural element deforms.Type: ApplicationFiled: October 7, 2013Publication date: April 9, 2015Applicant: Sikorsky AircraftInventors: Jonathan Bremmer, Shihong G. Song, Jeffrey G. Sauer, James S. Giampapa
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Publication number: 20150093541Abstract: A laminate design is provided and includes a substrate formed to define through-holes, an initially uncured pre-preg laminate disposed proximate to the substrate and an initially uncured pre-preg staple. The staple includes a main member and legs extending from the main member and being disposable with the legs extending through the through-holes to pierce the laminate. The staple is co-curable with the laminate.Type: ApplicationFiled: October 2, 2013Publication date: April 2, 2015Applicant: Sikorsky Aircraft CorporationInventors: Jonathan Bremmer, Darryl Mark Toni, Jeffrey G. Sauer, William E. Hovan, Christian A. Rogg, Andrew Varga, David M. Lent, Robert A. Lacko, Allan R. Macallister
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Publication number: 20140106116Abstract: A composite structure includes a first laminate and a second laminate. At least one core assembly is located between the first laminate and the second laminate. The at least one core assembly includes a core component and a layer of filler material disposed at a first face of the core component. The layer of filler material at least partially fills selected cells of the core component to a fill depth such that the filler material rigidizes when cured to prevent movement and/or crushing of core component under a pressure applied during a cure cycle of the composite structure.Type: ApplicationFiled: October 15, 2012Publication date: April 17, 2014Inventors: Jonathan Bremmer, Darryl Mark Toni, Jeffrey G. Sauer, Edward Joseph Fabian, Paul H. Denavit, William E. Hovan, III, Gergory A. Davidson