Accession Number:

ADA261774

Title:

Advanced Small Rocket Chambers. Phase 2. Option 1, 14 Lbf Ir-Re Rocket

Descriptive Note:

Final rept.

Corporate Author:

AEROJET PROPULSION DIV SACRAMENTO CA

Personal Author(s):

Report Date:

1992-08-01

Pagination or Media Count:

229.0

Abstract:

A high performance Ir-Re 14 1bf 62 N chamber and nozzle which can be a direct replacement for a production engine was designed, built, hot fired and vibration acceptance tested. It passed all acceptance tests satisfactorily and demonstrated a 20 sec increase in Is over the conventional 14 1bf silicide coated Cb chamber. The high performance engine uses the production valve and injector without modification. Incorporation of a secondary mixing device or Boundary Layer Trip within the combustion chamber results in elimination of the fuel film coolant, improvement in flow uniformity, the 20 sec performance increase, and reduction of a potential source of spacecraft contamination. Measured specific impulse Is was 305 sec at 751 area ratio, with monomethylhydrazine and nitrogen tetroxide propellants. Qualification tests remain to be done.... Rockets, Satellite propulsion, Rhenium thrusters, Iridium coatings, Chemical vapor deposition, Bipropellants, Radiation cool, High performance, High temperature, Long life.

Subject Categories:

  • Metallurgy and Metallography
  • Rockets

Distribution Statement:

APPROVED FOR PUBLIC RELEASE