The liquid propellent rocket motor is adapted for use over wide thrust ranges. Effective control of the proportion of liquid propellants delivered to the motor is obtained without regenerative oscillations due to fluctuations in combustion chamber pressure. A valve is provided for controlling fuel flow in the rocket motor operatively responsive to oxidant delivery pressures.
Pressure Operated Valve
1965
1 pages
Report
Keine Angabe
Englisch
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