Advanced Small Rocket Chambers. Phase 2. Option 1, 14 Lbf Ir-Re Rocket
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 75:1 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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Aug 01, 1992
- Accession Number
- ADA261774
Entities
People
- Donald M. Jassowski
- Mark L. Gage
Organizations
- Aerojet Rocketdyne Holdings