Patents by Inventor Andrew E. Modin
Andrew E. Modin 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: 9056448Abstract: Fiber reinforced composite structures having curved stepped surfaces are fabricated by laying up plies of fiber reinforced material over a tool having a stepped tool feature. The plies are rotated about a fixed axis as they are laid up to substantially form a fixed axis rosette pattern. The plies are angularly oriented such that at least certain of the plies have fiber orientations other than 0, +45, ?45 and 90 degrees. Potential bridging of the fibers over the stepped tool features is reduced or eliminated by cutting slits in the plies in the area of the stepped features, so that the plies can be fully compacted.Type: GrantFiled: April 24, 2013Date of Patent: June 16, 2015Assignee: THE BOEING COMPANYInventors: Andrew E. Modin, Jack A. Woods, Robert D. Hawkins
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Patent number: 8974212Abstract: Methods and systems for manufacturing fiber-reinforced resin parts are disclosed herein. In one embodiment, a method for manufacturing a fiber-reinforced resin part includes positioning a plurality of fibers on a mold surface of a female tool, and covering the fibers with a sealing layer. The method further includes pressing a portion of the covered fibers against an interior transition region (e.g., an internal radius) of the mold surface. While the portion of covered fibers is pressed against the interior transition region, air is removed from between the sealing layer and the mold surface to draw at least a partial vacuum between the sealing layer and the mold surface.Type: GrantFiled: October 9, 2009Date of Patent: March 10, 2015Assignee: The Boeing CompanyInventors: Thomas R. Cundiff, Dennis J. Hanks, Jack A. Woods, Val G. Brustad, Andrew E. Modin
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Patent number: 8944128Abstract: An apparatus for tensioning a preform may include a mandrel to receive a preform. The mandrel may have a first mandrel end and a second mandrel end. The preform may have a first preform end and a second preform end. The apparatus may include an anchoring groove disposed at the first mandrel end, and an anchoring device being configured and located to urge the first preform end towards the anchoring groove to secure the first preform end therebetween. The apparatus may include a tensioning groove disposed between the first mandrel end and the second mandrel end, and a tensioning device being configured and located to urge at least a portion of the preform into the tensioning groove.Type: GrantFiled: June 25, 2012Date of Patent: February 3, 2015Assignee: The Boeing CompanyInventors: Michael L. Glain, David J. Kehrl, Andrew E. Modin, Scott A. Harris, Robert A. Coleman, Andrew Head, Steven C. Stenard, Thomas R. Cundiff, Joo Hyun Han, Timothy D. Aquino
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Publication number: 20140190625Abstract: A plurality of identical fabrication modules are linked together and configurable to fabricate any of a plurality of differing laminate structures in a family of structures having common features. Each of the fabrication modules is locally adapted to fabricate a section of the laminate structure on a corresponding tool. A controller controls and coordinates automated operation of the fabrication modules.Type: ApplicationFiled: May 24, 2013Publication date: July 10, 2014Applicant: The Boeing CompanyInventors: James N. Buttrick, Dennis Wayne Stewart, Andrew E. Modin, David Paul Banks, Edoardo Depase, Jesus Sanchez
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Publication number: 20140069576Abstract: A method of manufacturing curved composite structural elements can include fabricating a web ply in a flat curve over a removable substrate and laying up the ply on a curved web surface of a manufacturing tool. The method also can include laying up a diagonal ply with fibers oriented at +/?45° from the centerline of the web surface. The method further can include cutting a unidirectional composite tape into segments and laying up the tape segments to form a cross ply with a fiber orientation normal to the centerline of the web surface. One or both edges of the diagonal and cross plies may be folded over one or two sides of the manufacturing tool to form one or two flange surfaces. Additionally, a cap ply can be laid up on one or both flange surfaces using composite tape. The structural element layup can then be inspected and any excess composite material can be trimmed away.Type: ApplicationFiled: November 18, 2013Publication date: March 13, 2014Applicant: The Boeing CompanyInventors: Todd A. Brown, Stephen Douglas Friddell, Christopher G. Harris, Andrew E. Modin
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Publication number: 20140027048Abstract: A method is presented. The method comprises identifying a desired shape of a ply on a tool, in which the ply has a fiber orientation; identifying a cut shape for the ply, in which the cut shape is different than the desired shape; cutting a composite prepreg ply to have the cut shape, the composite prepreg ply having the fiber orientation; using a deformable carrier to apply the composite prepreg ply having the cut shape to the tool such that the composite prepreg ply has the desired shape on the tool.Type: ApplicationFiled: October 7, 2013Publication date: January 30, 2014Applicant: The Boeing CompanyInventors: Robert D. Hawkins, Kurtis S. Willden, Andrew E. Modin, Edoardo Depase, Michael L. Glain, Benjamin Adam Mussi, Max U. Kismarton
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Patent number: 8636936Abstract: A method for fabricating a laminated composite body including a metal foil and a plurality of fiber plies. The method includes perforating a sheet of metal foil, stacking the perforated metal foil sheet and the plurality of fiber plies in face to face relation in a predetermined order and orientation, and infusing resin into the stacked sheet and plies so that resin flows through the perforations in the metal foil sheet and intersperses between the plurality of fiber plies to form the laminated composite body.Type: GrantFiled: January 9, 2006Date of Patent: January 28, 2014Assignee: The Boeing CompanyInventors: Andrew E. Modin, Robert D. Hawkins, Robert G. Albers, Jack A. Woods
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Patent number: 8632653Abstract: A method of manufacturing curved composite structural elements can include fabricating a web ply in a flat curve over a removable substrate and laying up the ply on a curved web surface of a manufacturing tool. The method also can include laying up a diagonal ply with fibers oriented at +/?45° from the centerline of the web surface. The method further can include cutting a unidirectional composite tape into segments and laying up the tape segments to form a cross ply with a fiber orientation normal to the centerline of the web surface. One or both edges of the diagonal and cross plies may be folded over one or two sides of the manufacturing tool to form one or two flange surfaces. Additionally, a cap ply can be laid up on one or both flange surfaces using composite tape. The structural element layup can then be inspected and any excess composite material can be trimmed away.Type: GrantFiled: May 3, 2005Date of Patent: January 21, 2014Assignee: The Boeing CompanyInventors: Todd A. Brown, Stephen Douglas Friddell, Christopher G. Harris, Andrew E. Modin
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Publication number: 20130340944Abstract: A contoured composite part is made by assembling a preform charge, including aligning a plurality of plies along a preselected contour. The assembled aligned preform charge is then placed in a forming tool, where the charge is formed and cured.Type: ApplicationFiled: August 25, 2013Publication date: December 26, 2013Applicant: The Boeing CompanyInventor: Andrew E. Modin
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Patent number: 8551380Abstract: Composite prepreg is laid up over a tool by placing prepreg material on a carrier film and using the carrier film to apply the prepreg material to the tool. The prepreg is conformed to contours of the tool by deforming the carrier film.Type: GrantFiled: November 12, 2010Date of Patent: October 8, 2013Assignee: The Boeing CompanyInventors: Robert D. Hawkins, Kurtis S. Willden, Andrew E. Modin, Edoardo Depase, Michael L. Glain, Benjamin Adam Mussi, Max U. Kismarton
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Publication number: 20130236685Abstract: Fiber reinforced composite structures having curved stepped surfaces are fabricated by laying up plies of fiber reinforced material over a tool having a stepped tool feature. The plies are rotated about a fixed axis as they are laid up to substantially form a fixed axis rosette pattern. The plies are angularly oriented such that at least certain of the plies have fiber orientations other than 0, +45, ?45 and 90 degrees. Potential bridging of the fibers over the stepped tool features is reduced or eliminated by cutting slits in the plies in the area of the stepped features, so that the plies can be fully compacted.Type: ApplicationFiled: April 24, 2013Publication date: September 12, 2013Applicant: The Boeing CompanyInventors: Andrew E. Modin, Jack A. Woods, Robert D. Hawkins
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Patent number: 8449709Abstract: Fiber reinforced composite structures having curved stepped surfaces are fabricated by laying up plies of fiber reinforced material over a tool having a stepped tool feature. The plies are rotated about a fixed axis as they are laid up to substantially form a fixed axis rosette pattern. The plies are angularly oriented such that at least certain of the plies have fiber orientations other than 0, +45, ?45 and 90 degrees. Potential bridging of the fibers over the stepped tool features is reduced or eliminated by cutting slits in the plies in the area of the stepped features, so that the plies can be fully compacted.Type: GrantFiled: May 25, 2007Date of Patent: May 28, 2013Assignee: The Boeing CompanyInventors: Andrew E. Modin, Jack A. Woods, Robert D. Hawkins
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Patent number: 8303757Abstract: An apparatus to prepare a preform for fabrication includes a mandrel, anchoring groove, anchoring device, tensioning groove, and tensioning device. The mandrel receives the preform. The mandrel has a first mandrel end and a second mandrel end. The preform has a first preform end and a second preform end. The anchoring groove is disposed at the first mandrel end. The anchoring device is configured and located to urge the first preform end towards the anchoring groove to secure the first preform end therebetween. The tensioning groove is disposed between the first mandrel end and the second mandrel end. The tensioning device is configured and located to urge a portion of the preform into the tensioning groove.Type: GrantFiled: December 4, 2006Date of Patent: November 6, 2012Assignee: The Boeing CompanyInventors: Michael L. Glain, David J. Kehrl, Andrew E. Modin, Scott A. Harris, Robert A. Coleman, Andrew Head, Steven C. Stenard, Thomas R. Cundiff, Joo Hyun Han, Timothy D. Aquino
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Publication number: 20120263818Abstract: An apparatus for tensioning a preform may include a mandrel to receive a preform. The mandrel may have a first mandrel end and a second mandrel end. The preform may have a first preform end and a second preform end. The apparatus may include an anchoring groove disposed at the first mandrel end, and an anchoring device being configured and located to urge the first preform end towards the anchoring groove to secure the first preform end therebetween. The apparatus may include a tensioning groove disposed between the first mandrel end and the second mandrel end, and a tensioning device being configured and located to urge at least a portion of the preform into the tensioning groove.Type: ApplicationFiled: June 25, 2012Publication date: October 18, 2012Applicant: THE BOEING COMPANYInventors: Michael L. GLAIN, David J. KEHRL, Andrew E. MODIN, Scott A. HARRIS, Robert A. COLEMAN, Andrew HEAD, Steven C. STENARD, Thomas R. CUNDIFF, Joo Hyun HAN, Timothy D. AQUINO
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Publication number: 20120258276Abstract: A contoured composite part is made by assembling a preform charge, including aligning a plurality of plies along a preselected contour. The assembled aligned preform charge is then placed in a forming tool, where the charge is formed and cured.Type: ApplicationFiled: April 5, 2011Publication date: October 11, 2012Inventor: ANDREW E. MODIN
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Publication number: 20120121866Abstract: Composite prepreg is laid up over a tool by placing prepreg material on a carrier film and using the carrier film to apply the prepreg material to the tool. The prepreg is conformed to contours of the tool by deforming the carrier film.Type: ApplicationFiled: November 12, 2010Publication date: May 17, 2012Inventors: ROBERT D. HAWKINS, Kurtis S. Willden, Andrew E. Modin, Edoardo Depase, Michael L. Glain, Benjamin Adam Mussi, Max U. Kismarton
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Patent number: 7943076Abstract: A curved composite element is laid up over a tool having first and second curved tool surfaces possessing differing radii of curvatures. A plurality of composite fiber ply segments are arranged in substantially side-by-side relationship into a group. The ply segments are formed as a group onto the first curved tool surface, and the group is then formed from the first curved tool surface onto the second curved tool surface.Type: GrantFiled: January 31, 2009Date of Patent: May 17, 2011Assignee: The Boeing CompanyInventors: Robert D. Hawkins, Andrew E. Modin, Edoardo P. Depase
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Publication number: 20100074979Abstract: Methods and systems for manufacturing fiber-reinforced resin parts are disclosed herein. In one embodiment, a method for manufacturing a fiber-reinforced resin part includes positioning a plurality of fibers on a mold surface of a female tool, and covering the fibers with a sealing layer. The method further includes pressing a portion of the covered fibers against an interior transition region (e.g., an internal radius) of the mold surface. While the portion of covered fibers is pressed against the interior transition region, air is removed from between the sealing layer and the mold surface to draw at least a partial vacuum between the sealing layer and the mold surface.Type: ApplicationFiled: October 9, 2009Publication date: March 25, 2010Applicant: The Boeing CompanyInventors: Thomas R. Cundiff, Dennis J. Hanks, Jack A. Woods, Val G. Brustad, Andrew E. Modin
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Publication number: 20100040722Abstract: A composite item is fabricated in system that includes a layer of preform, supply of resin, mandrel, and bagging film. The layer of preform corresponds to the composite item. The supply of resin is sufficient to infuse the preform. The mandrel includes a preform receiving zone to receive the layer of preform and a resin receiving zone to receive the supply of resin. The resin receiving zone is adjacent to the preform receiving zone. The bagging film is operable to generate an envelope surrounding the preform receiving zone and the resin receiving zone.Type: ApplicationFiled: November 3, 2009Publication date: February 18, 2010Applicant: The Boeing CompanyInventors: Michael L. Glain, Dennis J. Hanks, Andrew E. Modin, Jack A. Woods, Timothy D. Aquino
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Patent number: 7633040Abstract: A composite item is fabricated in system that includes a layer of preform, supply of resin, mandrel, and bagging film. The layer of preform corresponds to the composite item. The supply of resin is sufficient to infuse the preform. The mandrel includes a preform receiving zone to receive the layer of preform and a resin receiving zone to receive the supply of resin. The resin receiving zone is adjacent to the preform receiving zone. The bagging film is operable to generate an envelope surrounding the preform receiving zone and the resin receiving zone.Type: GrantFiled: November 14, 2005Date of Patent: December 15, 2009Assignee: The Boeing CompanyInventors: Michael L. Glain, Dennis J. Hanks, Andrew E. Modin, Jack A. Woods, Timothy D. Aquino