High temperature thrust chamber for spacecraft

Details High temperature thrust chamber for spacecraft High temperature thrust chamber for spacecraft

1995-12-19

1998-02-24

Kashnikow, Andres

Aeronautics and astronautics

Spacecraft

With fuel system details

428610, B32B 1500

Patent

active

057204519

ABSTRACT:
A high temperature thrust chamber for spacecraft (20) is provided herein. The high temperature thrust chamber comprises a hollow body member (12) having an outer surface and an internal surface (16) defining the high temperature chamber (10). The body member (12) is made substantially of rhenium. An alloy (18) consisting of iridium and at least alloying metal selected of the group consisting of rhodium, platinum and palladium is deposited on at least a portion of the internal surface (16) of the body member (12). The iridium and the alloying metal are electrodeposited onto the body member (12). A HIP cycle is performed upon the body member (12) to cause the coating of iridium and the alloying metal to form the alloy (18) which protects the body member (12) from oxidation.

REFERENCES:
patent: 3723481 (1973-03-01), Bobear
patent: 4917968 (1990-04-01), Tuffias et al.
patent: 5011566 (1991-04-01), Hoffman
patent: 5154153 (1992-10-01), MacGregor
Powder Processing in the Fabrication of Rhenium, by Boris D. Bryskin nd Frank C. Danek, Journal of Materials, Jul. 19, 1991, pp. 24-26.
Electrochemical Processing of Factory Metals, by Donald R. Sadoway, Journal of Materials, Jul. 19, 1991, pp. 15-19.
The Properties and Applications of Rhenium Produced by CVD by Andre J. Sherman, Robert H. Tuffias and Richard B. Kaplan, Journal of Materials, Jul. 19, 1991, pp. 20-23.
Letter and Report sent by TRW to NASA-LeRC, Feb., 1994.
Letter and Report sent by TRW to NASA-LeRC, Mar., 1994.

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