Kenneth G Gousman

US Patent:

7093542, Aug 22, 2006

Filed:

Apr 22, 2004

Appl. No.:

10/831052

Inventors:

Kenneth G. Gousman - Palmdale CA, US
Scott D. Van Weelden - Lancaster CA, US
Brian T. Rosenberger - Aledo TX, US

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

F42B 12/22

US Classification:

102493, 86 83

Abstract:

Warhead structures and features are fabricated using direct manufacturing technologies, a method for fabricating bulk warhead structures by sequential and additive deposition of melted feedstock layers. Suitable energy sources for melting the feedstock can be various high energy density technologies including laser, electron beam, plasma arc deposition, and the like. The high energy density in combination with high cooling rates results in structures with homogeneous microstructures. The feedstock can be in the form of wire or powder and is applied to a substrate by introduction to a molten pool on the substrate, accumulating to additively combine with the substrate. The approach provides for warhead structures with singular and combined unique features to include: integral constructions, tailored fragmentation patterns, use of dissimilar materials for special effects, and variable material property constructions for enhanced performance.

US Patent:

6648270, Nov 18, 2003

Filed:

Aug 7, 2002

Appl. No.:

10/157705

Inventors:

Edward L. Burnett - Ventura CA
John W. Vinson - Thousand Oaks CA
Brian Quayle - Lancaster CA
Michael C. Carter - Palmdale CA
Kenneth Gousman - Palmdale CA
Scott Wan Weelden - Lancaster CA
Steven P. Ericson - Lancaster CA
Stephen G. Justice - Santa Clarita CA

Assignee:

Lockheed Martin Corporation - Bethesda MD

International Classification:

B64C 2900

US Classification:

244 23A, 244 23 D, 244 124, 180117, 180120, 114 67 A, 114289, 114290

Abstract:

A vehicle is disclosed having a hull with a longitudinal, vertical and lateral axis, the hull further having front end and rear ends and first and second sides. A turbofan engine mounted in said hull, said engine having an exhaust duct. First and second front exhaust nozzles are mounted on the first and second sides of the front end of the hull. First and second rear exhaust nozzles are coupled to the first and second sides of said hull at said rear. All of the exhaust nozzles are rotatable from a vertically downward position to at least a partially horizontal direction and incorporating shudders to adjust the flow rate of exhaust gas from said turbofan engine therethrough. A duct system for coupling the exhaust duct of the turbofan engine to all of the nozzles.