Robert J Rothschilds

US Patent:

61140503, Sep 5, 2000

Filed:

Dec 29, 1998

Appl. No.:

9/222371

Inventors:

Willard N. Westre - Bellevue WA
Heather C. Allen-Lilly - Renton WA
Donald J. Ayers - Snohomish WA
Samuel E. Cregger - Kent WA
David W. Evans - Kent WA
Donald L. Grande - Des Moines WA
Daniel J. Hoffman - Federal Way WA
Mark E. Rogalski - Issaquah WA
Robert J. Rothschilds - Kent WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B32B 312
B32B 1508
B64C 100

US Classification:

428608

Abstract:

The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.

US Patent:

58662723, Feb 2, 1999

Filed:

Jan 11, 1996

Appl. No.:

8/585304

Inventors:

Willard N. Westre - Bellevue WA
Heather C. Allen-Lilly - Renton WA
Donald J. Ayers - Snohomish WA
Samuel E. Cregger - Kent WA
David W. Evans - Kent WA
Donald L. Grande - Des Moines WA
Daniel J. Hoffman - Federal Way WA
Mark E. Rogalski - Issaquah WA
Robert J. Rothschilds - Kent WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

B32B 312
B32B 1508
B64C 100

US Classification:

428593

Abstract:

The invention provides a hybrid laminate and skin panels of hybrid laminate structure that are suitable for a supersonic civilian aircraft. The hybrid laminates include layups of layers of titanium alloy foil and composite plies, that are optimally oriented to counteract forces encountered in use, that are bonded to a central core structure, such as titanium alloy honeycomb. The reinforcing fibers of the composite plies are selected from carbon and boron, and the fibers are continuous and parallel oriented within each ply. However, some plies may be oriented at angles to other plies. Nevertheless, in a preferred embodiment of the invention, a substantial majority of, or all of, the fibers of the hybrid laminates are oriented in a common direction. The outer surfaces of the laminates include a layer of titanium foil to protect the underlying composite-containing structure from the environment, and attack by solvents, and the like.