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High temperature thrust chamber for spacecraft
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Copyright Year | 1998 |
| Description | 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. |
| File Size | 436748 |
| Page Count | 5 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_20080004604 |
| Archival Resource Key | ark:/13960/t3518xx2s |
| Language | English |
| Publisher Date | 1998-02-24 |
| Access Restriction | Open |
| Subject Keyword | Spacecraft Propulsion And Power Thrust Chambers Iridium Alloys Patents Rhenium High Temperature Spacecraft Temperature Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Patent |
