Patents by Inventor Edward Joseph Fabian
Edward Joseph Fabian 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).
-
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
-
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
-
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
-
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
-
Publication number: 20130344295Abstract: 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: ApplicationFiled: February 9, 2012Publication date: December 26, 2013Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Paul H. Denavit, Edward Joseph Fabian, Jeffrey G. Sauer, William E. Hovan, III, Darryl Mark Toni
-
Patent number: 8613252Abstract: A caul plate system for a laminate structure includes a plurality of layers of curable caul plies disposed over a laminate structure and substantially conforming to a surface of the laminate structure. A resin is applied to the plurality of layers of caul plies. Co-curing of the plurality of layers of caul plies with the laminate structure hardens the plurality of layers of caul plies such that a normal pressure is applied to the laminate structure during cure of the laminate structure.Type: GrantFiled: February 14, 2011Date of Patent: December 24, 2013Assignee: Sikorsky Aircraft CorporationInventors: Jonathan Bremmer, Jeffrey G. Sauer, Edward Joseph Fabian, Robert A. Lacko, Neil W. Cawthra, Christian A. Rogg, Paul H. Denavit, William E. Hovan, III
-
Publication number: 20130095284Abstract: 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: ApplicationFiled: October 17, 2011Publication date: April 18, 2013Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Jeffrey G. Sauer, Edward Joseph Fabian, Paul H. Denavit, Darryl Mark Toni, William E. Hovan, III
-
Publication number: 20120204741Abstract: A caul plate system for a laminate structure includes a plurality of layers of curable caul plies disposed over a laminate structure and substantially conforming to a surface of the laminate structure. A resin is applied to the plurality of layers of caul plies. Co-curing of the plurality of layers of caul plies with the laminate structure hardens the plurality of layers of caul plies such that a normal pressure is applied to the laminate structure during cure of the laminate structure.Type: ApplicationFiled: February 14, 2011Publication date: August 16, 2012Applicant: SIKORSKY AIRCRAFT CORPORATIONInventors: Jonathan Bremmer, Jeffrey G. Sauer, Edward Joseph Fabian, Robert A. Lacko, Neil W. Cawthra, Christian A. Rogg, Paul H. Denavit, William E. Hovan, III
-
Patent number: 5674586Abstract: A pressure tolerant composite panel has an inner fiber reinforced layer, an outer fiber reinforced layer and an core disposed therebetween. In one embodiment of the invention, the inner layer has weakening structures incorporated at the peripheral edges thereof, and has an outer layer of a different and lower modulus of elasticity than the inner layer to provide some degree of elongation. When high internal forces are encountered, the weakening structures allow the inner layer to separate, with the outer layers stretching to absorb the forces without failure. Optionally, strengthening straps are position about the panel such that it is compartmentalized into discrete sections to contain damage in localized areas. In an alternative embodiment of the invention, the inner core is produced of a crushable material which has a yield strength sufficient to provide structural support under normal operating conditions.Type: GrantFiled: June 7, 1995Date of Patent: October 7, 1997Assignee: United Technologies CorporationInventors: Darryl Mark Toni, Bruce Henry Barr, Edward Joseph Fabian, Bruce Fredric Kay, Joaquin Terceno, Kenneth Morgan Furnes, Alan Lee Dobyns