Toughened uni-piece, fibrous, reinforced,...

Coating processes – With pretreatment of the base

Reexamination Certificate

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C428S137000, C428S138000

Reexamination Certificate

active

07314648

ABSTRACT:
A composite thermal protection structure, for applications such as atmospheric re-entry vehicles, that can withstand temperatures as high as 3600° F. The structure includes an exposed surface cap having a specially formulated coating, an insulator base adjacent to the cap with another specially formulated coating, and one or more pins that extend from the cap through the insulator base to tie the cap and base together, through ceramic bonding and mechanical attachment. The cap and insulator base have corresponding depressions and projections that mate and allow for differences in thermal expansion of the cap and base. A thin coating of a reaction cured glass formulation is optionally provided on the structure to allow reduce oxidization and/or to reduce catalytic efficiency.

REFERENCES:
patent: 4083771 (1978-04-01), O'Hara
patent: 4093771 (1978-06-01), Fletcher et al.
patent: 4148962 (1979-04-01), Leiser et al.
patent: 4713275 (1987-12-01), Riccitiello et al.
patent: 5079082 (1992-01-01), Leiser et al.
patent: 5985433 (1999-11-01), Leiser et al.
patent: 6225248 (2001-05-01), Leiser et al.
patent: 6497390 (2002-12-01), Fischer et al.
Curry, et al., Material Characteristics of Space Shuttle Rein . . . , Proc of the 24th National Symposium and Exhibition,Book 2, May 8-10, 1979, 1524-1539, San Francisco, CA, USA.
Riccitello, et al., A Ceramic Matrix Composite Thermal Protection System for Hypersonic Vehicles, SAMPE Quarterly, May 1, 1993, 10-17,24-4, USA.
Stewart, et al., Thermal Response of Integrated Multicomponent Com . . . , Ceramic Engineering and Science Proc, Jul. 1987, 613-625, vol. 8-No. 7-8, American Ceramic Society, Inc.
First Office Action, dated Oct. 20, 2006, from patent application U.S. Appl. No. 10/779,504, parent to the above identified application.

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