Study made to determine performance characteristics of systems in thrust range required for attitude control systems; characteristic exhaust velocities for hydrazine and nitrogen tetroxide were measured with triplet and 2-on-2 injectors in 50 lb thrust uncooled combustion chamber at chamber pressure of 10 psia; steady state performance for oxidant fuel mixture ratios from 0.7 to 1.2; peak characteristic exhaust velocity was 5280 fps or 92% of theoretical value.
Performance of low-thrust storable-bipropellant rocket at very low chamber pressure
NASA -- Tech Note
1961
22 pages
Report
Englisch
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