Donald James Ayers

61140503, Sep 5, 2000

Dec 29, 1998

9/222371

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

The Boeing Company - Seattle WA

B32B 312
B32B 1508
B64C 100

428608

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.

49632159, Oct 16, 1990

Jun 14, 1989

7/368165

Donald J. Ayers - Snohomish WA

The Boeing Company - Seattle WA

B32B 3100

156286

A method for forming a thermoplastic laminate having a desired laminate thickness is disclosed. Layers of composite material using precured or partially precured thermoplastic resin laminate layers are layed-up on a forming tool. A relatively constant, uniform pressure is applied to the layers to produce a preconsolidated laminate having a thickness approximately equal to the ultimate desired laminate thickness. The laminate layers are free to slide relative to one another during debulking because they are either cured or partially cured. Thus, wrinkles are avoided. The debulked laminae are then consolidated in a conventional autoclave under elevated temperature and pressure.

58662723, Feb 2, 1999

Jan 11, 1996

8/585304

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

The Boeing Company - Seattle WA

B32B 312
B32B 1508
B64C 100

428593

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.