Patents by Inventor Joseph H. Campana
Joseph H. Campana 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: 11932398Abstract: A horizontal stabilizer assembly includes a stabilizer connector assembly having a center multi-spar box, a first horizontal stabilizer having a first multi-spar box connected to a first side of the center multi-spar box with a plurality of first lug and clevis connections, and a second horizontal stabilizer having a second multi-spar box connected to a second side of the center multi-spar box, opposite the first side, with a plurality of second lug and clevis connections.Type: GrantFiled: May 3, 2021Date of Patent: March 19, 2024Assignee: The Boeing CompanyInventors: Joseph H. Campana, Kevin P. Ryder, William H. Pearson, James R. Harrison
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Patent number: 11511846Abstract: An aircraft has a vertical stabilizer having a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has a pair of middle longitudinal lugs between a front and rear of the base rib assembly, a pair of front lateral lugs along the front of the base rib assembly, and a pair of rear lateral lugs along the rear of the base rib assembly. There are no lateral lugs between the pairs of middle lugs. A pair of middle clevises extend through corresponding apertures in an outer skin of the fuselage and are secured to one of the plurality of frame members and a plurality of retaining members are inserted through mounting holes in each middle longitudinal lug and mounting holes in each middle clevis to secure the vertical stabilizer to the aircraft fuselage.Type: GrantFiled: May 27, 2020Date of Patent: November 29, 2022Assignee: THE BOEING COMPANYInventors: Joseph H. Campana, William H. Pearson, Charles R. Coates, Kevin P. Ryder, Peter J. Newnham
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Patent number: 11370523Abstract: An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.Type: GrantFiled: May 27, 2020Date of Patent: June 28, 2022Assignee: THE BOEING COMPANYInventors: Joseph H. Campana, William H. Pearson, Charles R. Coates, Kevin P. Ryder, Peter J. Newnham
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Publication number: 20220055735Abstract: A horizontal stabilizer assembly includes a stabilizer connector assembly having a center multi-spar box, a first horizontal stabilizer having a first multi-spar box connected to a first side of the center multi-spar box with a plurality of first lug and clevis connections, and a second horizontal stabilizer having a second multi-spar box connected to a second side of the center multi-spar box, opposite the first side, with a plurality of second lug and clevis connections.Type: ApplicationFiled: May 3, 2021Publication date: February 24, 2022Inventors: Joseph H. Campana, Kevin P. Ryder, William H. Pearson, James R. Harrison
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Publication number: 20210371079Abstract: An aircraft has a vertical stabilizer with a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has front longitudinal lugs, rear longitudinal lugs, and opposing middle longitudinal lugs. Front clevises corresponding to the front longitudinal lugs are secured to frame members of the fuselage of the aircraft and each has a first, second, and third mounting arms. Rear clevises corresponding to the rear longitudinal lugs are secured to frame members and each has a first, second, and third mounting arms. Middle clevises corresponding to the middle longitudinal lugs are secured to frame members and each has only first and second mounting arms. Retaining members inserted through mounting holes in each longitudinal lug and mounting holes in each corresponding clevis secures the vertical stabilizer to the fuselage.Type: ApplicationFiled: May 27, 2020Publication date: December 2, 2021Inventors: Joseph H. Campana, William H. Pearson, Charles R. Coates, Kevin P. Ryder, Peter J. Newnham
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Publication number: 20210371080Abstract: An aircraft has a vertical stabilizer having a multi-spar box and a base rib assembly secured to the multi-spar box. The base rib assembly has a pair of middle longitudinal lugs between a front and rear of the base rib assembly, a pair of front lateral lugs along the front of the base rib assembly, and a pair of rear lateral lugs along the rear of the base rib assembly. There are no lateral lugs between the pairs of middle lugs. A pair of middle clevises extend through corresponding apertures in an outer skin of the fuselage and are secured to one of the plurality of frame members and a plurality of retaining members are inserted through mounting holes in each middle longitudinal lug and mounting holes in each middle clevis to secure the vertical stabilizer to the aircraft fuselage.Type: ApplicationFiled: May 27, 2020Publication date: December 2, 2021Inventors: Joseph H. Campana, William H. Pearson, Charles R. Coates, Kevin P. Ryder, Peter J. Newnham
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Patent number: 9187168Abstract: A bulkhead employs a substantially spherical dome having a periphery and an apex with an axis perpendicular to the dome at the apex. A first plurality of straps emanate from a periphery of the dome on geodesics defined by a first pair of virtual poles beyond the periphery of the dome. A second plurality of straps emanate from the periphery of the dome on second geodesics defined by a second pair of virtual poles beyond the periphery of the dome, wherein any overlap on an individual strap in the first plurality of straps is singular to only one individual strap in the second plurality of straps.Type: GrantFiled: July 30, 2013Date of Patent: November 17, 2015Assignee: The Boeing CompanyInventors: Richard R. Rosman, Joseph H. Campana
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Publication number: 20150037541Abstract: A bulkhead employs a substantially spherical dome having a periphery and an apex with an axis perpendicular to the dome at the apex. A first plurality of straps emanate from a periphery of the dome on geodesics defined by a first pair of virtual poles beyond the periphery of the dome. A second plurality of straps emanate from the periphery of the dome on second geodesics defined by a second pair of virtual poles beyond the periphery of the dome, wherein any overlap on an individual strap in the first plurality of straps is singular to only one individual strap in the second plurality of straps.Type: ApplicationFiled: July 30, 2013Publication date: February 5, 2015Applicant: The Boeing CompanyInventors: Richard R. Rosman, Joseph H. Campana
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Patent number: 8517312Abstract: A method for connecting a wing. A frame for a wing may be positioned relative to a fuselage of an aircraft. The frame may have bays and comprise a front spar, a rear spar, and a number of spars located between the front and rear spars. A first number of skin panels may be on a first side of the frame, and a second number of skin panels may be on a second side of the frame. The first side may be opposite to the second side. Openings may be in the first and second numbers of skin panels. The openings may be in locations such that each bay has an opening and such that the openings may alternate between the first side and the second side between adjacent bays in the bays. The frame may be attached to the fuselage using the openings to access an interior of the frame.Type: GrantFiled: December 20, 2012Date of Patent: August 27, 2013Assignee: The Boeing CompanyInventor: Joseph H. Campana
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Patent number: 8348196Abstract: A method for connecting a wing. A frame for a wing may be positioned relative to a fuselage of an aircraft. The frame may have bays and comprise a front spar, a rear spar, and a number of spars located between the front and rear spars. A first number of skin panels may be on a first side of the frame, and a second number of skin panels may be on a second side of the frame. The first side may be opposite to the second side. Openings may be in the first and second numbers of skin panels. The openings may be in locations such that each bay has an opening and such that the openings may alternate between the first side and the second side between adjacent bays in the bays. The frame may be attached to the fuselage using the openings to access an interior of the frame.Type: GrantFiled: August 17, 2010Date of Patent: January 8, 2013Assignee: The Boeing CompanyInventor: Joseph H. Campana
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Publication number: 20120043422Abstract: A method for connecting a wing. A frame for a wing may be positioned relative to a fuselage of an aircraft. The frame may have bays and comprise a front spar, a rear spar, and a number of spars located between the front and rear spars. A first number of skin panels may be on a first side of the frame, and a second number of skin panels may be on a second side of the frame. The first side may be opposite to the second side. Openings may be in the first and second numbers of skin panels. The openings may be in locations such that each bay has an opening and such that the openings may alternate between the first side and the second side between adjacent bays in the bays. The frame may be attached to the fuselage using the openings to access an interior of the frame.Type: ApplicationFiled: August 17, 2010Publication date: February 23, 2012Applicant: THE BOEING COMPANYInventor: Joseph H. Campana
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Patent number: 6161839Abstract: The invention is a valve seal assembly (43) illustrated in the context of a compressor bleed valve (36) for a gas turbine engine. The seal assembly includes a seal carrier (44) having a circumferentially extending groove (72) bordered by a pair of opposing flanges (74). The flanges cooperate to define a recess (76) portion of the groove and a throat (78) portion of the groove. The seal assembly also includes one or more seal elements (46) each having a base (82), conformal with the recess, and longitudinally captured in the recess by the flanges. A stem (84) extends from the base and projects through the throat, and a sealing bead (86) extends from the stem. An insert (88) extends circumferentially in the base for stiffening the base about a circumferential bending axis (C). An access port (96) facilitates installation and removal of the seal elements (46) and a cover (98) traps the seal elements in the carrier (44).Type: GrantFiled: February 27, 1998Date of Patent: December 19, 2000Assignee: United Technologies CorporationInventors: Kevin A. Walton, Joseph H. Campana