Patents by Inventor Peter A. Hogenson
Peter A. Hogenson 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: 8864073Abstract: A thermal protection system for a vehicle may include a substantially rigid, relatively thin outer aeroshell, a relatively low density insulation layer, and a resiliently compressible conformal layer. The vehicle may include a substructure. The aeroshell may be configured to be fastened to the substructure. The insulation layer may be disposed against the aeroshell. The conformal layer may be disposable against the insulation layer. The conformal layer may be compressively preloaded against the substructure when the aeroshell is fastened to the substructure.Type: GrantFiled: July 27, 2011Date of Patent: October 21, 2014Assignee: The Boeing CompanyInventors: Ben Y. Won, Peter A. Hogenson, Vann Heng, Mary M. Litwinski, Robert J. Perez, Caroline Neri Kim
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Publication number: 20090044896Abstract: A thermal protection paste as described herein can be used by itself, or impregnated into a high temperature resistant fabric to form a repair patch, to repair a thermal protection structure. The paste includes a ceramic composition that includes ceramic material having at least a first controlled particle size and a second controlled particle size that is larger than the first controlled particle size. The ceramic composition is mixed into a high temperature ceramic precursor resin to form the paste. The paste (or patch) is applied to the structure under repair and initially heated to cure the paste and to secure it in place. When the paste and/or patch is cured, it becomes a cross-linked polymer having high thermal protection characteristics. When the paste is exposed to very high temperature, e.g., spacecraft reentry temperatures, it pyrolizes and retains its high thermal protection characteristics.Type: ApplicationFiled: October 24, 2008Publication date: February 19, 2009Inventors: Steven J. Adam, Peter A. Hogenson, James V. Tompkins, Gordon R. Toombs, Douglas G. Soden
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Patent number: 7296769Abstract: A cryogenic fuel tank assembly 10 is provided comprising a cryogenic fuel tank wall 22. A foam assembly 24 is affixed to the cryogenic fuel tank wall 22, the foam assembly 24 having an inner surface 30 and an outer surface 32. A first solid film 40 bonded to the outer surface 32 to provide a uniform outer bonding surface 42. A thermal protection system assembly 38 is bonded to the uniform outer bonding surface 42.Type: GrantFiled: October 11, 2003Date of Patent: November 20, 2007Assignee: The Boeing CompanyInventors: Peter A. Hogenson, Keith Chong, Peter Duong
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Publication number: 20060234579Abstract: A thermal protection paste as described herein can be used by itself, or impregnated into a high temperature resistant fabric to form a repair patch, to repair a thermal protection structure. The paste includes a ceramic composition that includes ceramic material having at least a first controlled particle size and a second controlled particle size that is larger than the first controlled particle size. The ceramic composition is mixed into a high temperature ceramic precursor resin to form the paste. The paste (or patch) is applied to the structure under repair and initially heated to cure the paste and to secure it in place. When the paste and/or patch is cured, it becomes a cross-linked polymer having high thermal protection characteristics. When the paste is exposed to very high temperature, e.g., spacecraft reentry temperatures, it pyrolizes and retains its high thermal protection characteristics.Type: ApplicationFiled: April 14, 2005Publication date: October 19, 2006Inventors: Steven Adam, Peter Hogenson, James Tompkins, Gordon Toombs, Douglas Soden
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Publication number: 20050089661Abstract: A cryogenic fuel tank assembly 10 is provided comprising a cryogenic fuel tank wall 22. A foam assembly 24 is affixed to the cryogenic fuel tank wall 22, the foam assembly 24 having an inner surface 30 and an outer surface 32. A first solid film 40 bonded to the outer surface 32 to provide a uniform outer bonding surface 42. A thermal protection system assembly 38 is bonded to the uniform outer bonding surface 42.Type: ApplicationFiled: October 11, 2003Publication date: April 28, 2005Applicant: THE BOEING COMPANYInventors: Peter Hogenson, Keith Chong, Peter Duong
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Publication number: 20040056151Abstract: A ruddervator for an aerospacecraft including a monolithic, one-piece, oxide/oxide-based ceramic matrix composite (Oxide-CMC) shell having a hollowed interior area. A graphite composite structural member is inserted into the hollowed interior area and bonded thereto. The Oxide-CMC shell is comprised of one or more plies of Oxide-CMC fabric which are fused over a thick substrate of rigid ceramic foam insulation to form the monolithic shell. An outer mold line ply of the Oxide-CMC shell is further infused with a high-emissivity coating such as reaction-cured glass (RCG) to provide plasma heating re-radiation outward to reduce internal temperatures in the ruddervator. A torque box transition structure is secured to the graphite composite structural member to interface the ruddervator to a fuselage actuator spindle of the aerospacecraft. The ruddervator is reusable and formed from a reduced number of independent component parts, and weighs less than previously developed ruddervators.Type: ApplicationFiled: May 7, 2003Publication date: March 25, 2004Inventors: Robert A. DiChiara, Robert E. French, Conley Siddoway Thatcher, Edward A. Zadorozny, Peter A. Hogenson
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Patent number: 6676077Abstract: A ruddervator for an aerospacecraft including a monolithic, one-piece, oxide/oxide-based ceramic matrix composite (Oxide-CMC) shell having a hollowed interior area. A graphite composite structural member is inserted into the hollowed interior area and bonded thereto. The Oxide-CMC shell is comprised of one or more plies of Oxide-CMC fabric which are fused over a thick substrate of rigid ceramic foam insulation to form the monolithic shell. An outer mold line ply of the Oxide-CMC shell is further infused with a high-emissivity coating such as reaction-cured glass (RCG) to provide plasma heating re-radiation outward to reduce internal temperatures in the ruddervator. A torque box transition structure is secured to the graphite composite structural member to interface the ruddervator to a fuselage actuator spindle of the aerospacecraft. The ruddervator is reusable and formed from a reduced number of independent component parts, and weighs less than previously developed ruddervators.Type: GrantFiled: November 1, 2000Date of Patent: January 13, 2004Assignee: The Boeing CompanyInventors: Robert A. DiChiara, Jr., Robert E. French, Conley Siddoway Thatcher, Edward A. Zadorozny, Peter A. Hogenson
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Patent number: 6419189Abstract: A ruddervator for an aerospacecraft. The ruddervator is formed by a plurality of airfoil sections nestably disposed in side by side fashion and supported by a pair of titanium box beam frame elements extending through central openings in each of the airfoil sections. Each airfoil section includes an oxide fiber/oxide matrix-based ceramic matrix composite (oxide-CMC) panel made up of multiple plies of oxide-CMC fabric which are fused over a rigid ceramic foam insulation member. The lower ends of the frame elements are secured to a transition component comprising a conventional torque box. The ruddervator can be manufactured with less cost and lower weight over previous ruddervator designs which require one or more large skin sections which are mechanically fastened to a substructure. The ruddervator of the present invention further minimizes fabrication costs by using a common design for the nesting airfoil sections so that a common female lay-up mold can be used for fabricating all of the airfoil sections.Type: GrantFiled: November 1, 2000Date of Patent: July 16, 2002Assignee: The Boeing CompanyInventors: Robert A. DiChiara, Jr., Robert E. French, Conley Siddoway Thatcher, Edward A. Zadorozny, Peter A. Hogenson
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Patent number: 5626951Abstract: A thermal insulation system comprising an insulator core formed of ceramic material and, an outer layer integrally connected on an inner surface to a first side of the insulator core, the outer layer comprising a woven material impregnated with a ceramic matrix. In one embodiment, a thermal insulation blanket is formed having a flexible insulator core formed of ceramic fibrous materials, an outer layer integrally connected to one side of the insulator core, and an inner layer connected to a second side of that core. The inner layer is formed of woven material. In a second embodiment, a thermal insulation tile is formed including a rigid insulator core formed of ceramic material and an outer layer integrally connected to an inner surface to a first side of insulator core. The outer layer comprises a woven ceramic material impregnated with a ceramic matrix.Type: GrantFiled: April 3, 1995Date of Patent: May 6, 1997Assignee: Rockwell International CorporationInventor: Peter A. Hogenson
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Patent number: 4695619Abstract: A polymeric or plastic coating is provided which protects coated structures by forming an intumescent insulative fire resistant barrier. The coating is formed from the product of mixing an aromatic polyisocyanate, an aromatic polycarboxylic compound and about 1 to about 20% by weight of furfuryl alcohol. The structure to be protected is coated with the product of the mixture and the coating is dried. An intumescent polyimide fire resistant foam is formed when the coating is exposed to a (non-flame) heat source at temperature ranging from about 110.degree. C. to about 140.degree. C.Type: GrantFiled: July 17, 1985Date of Patent: September 22, 1987Assignee: Rockwell International CorporationInventors: Charles L. Hamermesh, Paul J. Dynes, Peter A. Hogenson
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Patent number: 4303727Abstract: A plastic coating is provided which protects coated structures from flame. The coating is a product resulting from mixing an aromatic polyisocyanate, an aromatic polycarboxylic compound, and furfuryl alcohol at a temperature less than 80.degree. C. The structure to be protected from flame is coated with the product and the product is then dried. If the coated structure is exposed to flame, the coating intumesces to form a flame-resistant foam which protects the structure.Type: GrantFiled: October 14, 1980Date of Patent: December 1, 1981Assignee: Rockwell International CorporationInventors: Charles L. Hamermesh, Chiang-Ying M. Tung, Peter A. Hogenson