Accession Number : ADA269048

Title :   Space Storable Rocket Technology Program (SSRT).

Descriptive Note : Final contractor rept.,

Corporate Author : TRW SPACE AND TECHNOLOGY GROUP REDONDO BEACH CA APPLIED TECHNOLOGY DIV

Personal Author(s) : Chazen, Melvin L. ; Mueller, Thomas ; Rust, Thomas

Report Date : 05 AUG 1993

Pagination or Media Count : 95

Abstract : The SSRT Option 1 Program has continued to establish a technology base for a new class high performance/long life L02-N2H4 space storable engines. The Option 1 Program evaluated two new injector elements, two different methods of injector thermal protection, high temperature rhenium properties and methods of joining rhenium thrust chamber to columbium injector and nozzle. Additional critical experiments were conducted to evaluate the effects of G02 injection into the chamber, GHe injection into the main L02, splash plate effects and decreasing aspect ratio impact on the 120-slot element. Summarization of results follows: Decreasing the aspect ratio improved performance; however, the 60-slot hybrid injector was still best. Testing demonstrated L02 conditions at injection was the performance driver. Both thermal block and film cooling adaptors demonstrated thermal stability but low performance due to low L02 injection temperatures. G02 injection downstream of L02 injection and GHe injection into main L02 demonstrated thermal stability but below maximum performance. Removal of splash plate improves performance. CVD rhenium properties were evaluated(70-3400F). Brazing was the effective method of joining rhenium to columbium. Performance >345 seconds(e=204)was demonstrated-a 30-second improvement over best existing flight apogee engine.... Rocket engines, Satellite propulsion, Bipropellant engines, Space storable, High performance engines, Long life engines.

Descriptors :   *ROCKET ENGINES, APOGEE, ARTIFICIAL SATELLITES, ASPECT RATIO, BIPROPELLANTS, BRAZING, CHAMBERS, FILM COOLING, FLIGHT, HIGH TEMPERATURE, IMPACT, INJECTION, INJECTORS, JOINING, LONG LIFE, NIOBIUM, NOZZLES, PLATES, PROTECTION, RATIOS, REDUCTION, REMOVAL, RHENIUM, SLOTS, SPLASH, STABILITY, TEMPERATURE, THERMAL STABILITY, THRUST CHAMBERS.

Subject Categories : Rocket Engines

Distribution Statement : APPROVED FOR PUBLIC RELEASE