Space Storable Rocket Technology program (SSRT). Option 1 program

The Space Storable Rocket Technology (SSRT) Option 1 Program was initiated in October 1991 after completion of the Basic Program. The program was restructured in mid-July 1992 to incorporate a Rhenium Technology Task and reduce the scope of the LO2-N2H4 engine development. The program was also extended to late February 1993 to allow for the Rhenium Technology Task completion. The Option 1 Program was devoted to evaluation of two new injector elements, evaluation of two different methods of thermal protection of the injector, evaluation of high temperature material properties of rhenium and evaluation of methods of joining the rhenium thrust chamber to the columbium injector and nozzle extension. In addition, critical experiments were conducted (Funded by Option 2) to evaluate mechanisms to understand the effects of GO2 injection into the chamber, helium injection into the main LO2, effect of the splash plate and effect of decreasing the aspect ratio of the 120-slot (-13a) element. The performance and thermal models were used to further correlate the test results with analyses. The results of the work accomplished are summarized

High temperature thrust chamber for spacecraft

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