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Peter A Hogenson, Age 935563 Seaside Way, Long Beach, CA 90803

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Known as:
Peter J Hogenson Peter Allen Christensen
Related to:
Anne E Hogenson 46 Robert J Hogenson

Peter Hogenson Phones & Addresses

5563 Seaside Way, Long Beach, CA 90803 (562) 439-3361

5563 Seaside Walk, Long Beach, CA 90803 (562) 439-3361

Desert Hot Springs, CA

Palm Springs, CA

Los Alamitos, CA

Rancho Mirage, CA

Los Angeles, CA

5563 E Seaside Walk, Long Beach, CA 90803

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Mentions for Peter A Hogenson

Peter Hogenson resumes & CV records

Resumes

Peter Hogenson Photo 10

Owner, Beyond Type Creative

Location:
Greater Los Angeles Area
Industry:
Graphic Design
Peter Hogenson Photo 11

Thermal Protection And Hot Structure Engineering Consultant

Location:
Long Beach, CA
Industry:
Aviation & Aerospace
Work:
Vector Launch Inc.
Thermal Protection and Hot Structure Engineering Consultant North Amerian Aviation Rockwell International Safran Boeing Pah & Associates Jul 1959 - Jul 2017
Materials and Processes Engineering - Manager, Consultant, Project and Program Management
Education:
Yale University
Skills:
Aircraft, Aviation, Systems Engineering, Engineering, Engineering Management, Program Management, Aerospace
Peter Hogenson Photo 12

Peter Hogenson

Publications & IP owners

Us Patents

Hot Ruddervator Apparatus And Method For An Aerospacecraft

US Patent:
6419189, Jul 16, 2002
Filed:
Nov 1, 2000
Appl. No.:
09/703568
Inventors:
Robert E. French - San Gabriel CA
Conley Siddoway Thatcher - Placentia CA
Edward A. Zadorozny - Redondo Beach CA
Peter A. Hogenson - Long Beach CA
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64C 100
US Classification:
244123, 244124, 244 35 R, 244 87, 244131, 416223 R
Abstract:
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.

High Temperature Resistant Airfoil Apparatus For A Hypersonic Space Vehicle

US Patent:
6676077, Jan 13, 2004
Filed:
Nov 1, 2000
Appl. No.:
09/703947
Inventors:
Robert E. French - San Gabriel CA
Conley Siddoway Thatcher - Placentia CA
Edward A. Zadorozny - Redondo Beach CA
Peter A. Hogenson - Long Beach CA
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64G 100
US Classification:
244117R, 244158 A, 244123, 244133
Abstract:
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. The manufacturing cost of the ruddervator is reduced by utilizing the reduced tooling complexities of Oxide-CMC over CMC fabrication processes.

Cryogenic Fuel Tank Insulation Assembly

US Patent:
7296769, Nov 20, 2007
Filed:
Oct 11, 2003
Appl. No.:
10/605599
Inventors:
Peter A. Hogenson - Long Beach CA, US
Keith Chong - Placentia CA, US
Peter Duong - La Puente CA, US
Assignee:
The Boeing Company - Chicago IL
International Classification:
B64G 1/58
US Classification:
2441717, 22056015
Abstract:
A cryogenic fuel tank assembly is provided comprising a cryogenic fuel tank wall. A foam assembly is affixed to the cryogenic fuel tank wall , the foam assembly having an inner surface and an outer surface. A first solid film bonded to the outer surface to provide a uniform outer bonding surface. A thermal protection system assembly is bonded to the uniform outer bonding surface.

High Temperature Resistant Airfoil Apparatus For A Hypersonic Space Vehicle

US Patent:
2004005, Mar 25, 2004
Filed:
May 7, 2003
Appl. No.:
10/431414
Inventors:
Robert DiChiara - Carlsbad CA, US
Robert French - San Gabriel CA, US
Conley Thatcher - Placentia CA, US
Edward Zadorozny - Redondo Beach CA, US
Peter Hogenson - Long Beach CA, US
International Classification:
B64C001/00
B64D001/00
B64C030/00
US Classification:
244/11700R
Abstract:
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. The manufacturing cost of the ruddervator is reduced by utilizing the reduced tooling complexities of Oxide-CMC over CMC fabrication processes.

High Temperature Ceramic-Based Thermal Protection Material

US Patent:
2006023, Oct 19, 2006
Filed:
Apr 14, 2005
Appl. No.:
11/106763
Inventors:
Steven Adam - Orange CA, US
Peter Hogenson - Long Beach CA, US
James Tompkins - Huntington Beach CA, US
Gordon Toombs - Long Beach CA, US
Douglas Soden - San Pedro CA, US
International Classification:
B32B 17/02
B32B 27/12
B32B 27/04
US Classification:
442136000, 442172000, 442178000, 501088000, 501087000, 501096100, 501096300
Abstract:
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.

High Temperature Ceramic-Based Thermal Protection Material

US Patent:
2009004, Feb 19, 2009
Filed:
Oct 24, 2008
Appl. No.:
12/257571
Inventors:
Steven J. Adam - Orange CA, US
Peter A. Hogenson - Long Beach CA, US
James V. Tompkins - Huntington Beach CA, US
Gordon R. Toombs - Long Beach CA, US
Douglas G. Soden - San Pedro CA, US
International Classification:
B05D 3/02
US Classification:
156 94
Abstract:
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.

Intumescent Flame-Resistant Coating Composition

US Patent:
4695619, Sep 22, 1987
Filed:
Jul 17, 1985
Appl. No.:
6/755872
Inventors:
Charles L. Hamermesh - Westlake Village CA
Paul J. Dynes - Los Angeles CA
Peter A. Hogenson - Long Beach CA
Assignee:
Rockwell International Corporation - El Segundo CA
International Classification:
B32B 326
B32B 2740
B32B 518
B05D 302
US Classification:
528 73
Abstract:
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.

Intumescent Flame-Resistant Coating

US Patent:
4303727, Dec 1, 1981
Filed:
Oct 14, 1980
Appl. No.:
6/196905
Inventors:
Charles L. Hamermesh - Westlake Village CA
Peter A. Hogenson - Long Beach CA
Assignee:
Rockwell International Corporation - El Segundo CA
International Classification:
B32B 326
B32B 518
B32B 2740
B05D 302
US Classification:
428314
Abstract:
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.

Possible Relatives

Kim H Hogenson  Andrew C Hogenson  Charles S Hogenson  Christopher L Hogenson  Peter D Stamps  Peter J Standish  Peter G Johnston  Peter D Jones  Peter Y Stangl  Peter W Stanislaw 

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