Over 100 successful static firing tests of a ducted rocket with a hybrid gas generator have been performed. These tests took place in a connected pipe facility, simulating multiple ramjet inlet and gas generator conditions. Characteristic velocity efficiency was between 0.8 and 1. Fuel regression rate at the gas generator is displayed. Tests simulating a mission at which thrust modulation is required were executed showing that a 30% thrust increase can be easily obtained by controlling the oxidizer flow rate. This cold gas control is one of the major advantages of using a hybrid gas generator for a ducted rocket.
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