NASA NTRS · 19690000280
Two-step rocket engine bipropellant valve concept
Abstract
Initiating combustion of altitude control rocket engines in a precombustion chamber of ductile material reduces high pressure surges generated by hypergolic propellants. Two-step bipropellant valve concepts control initial propellant flow into precombustion chamber and subsequent full flow into main chamber.
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Capps, J. E., Ferguson, R. E., Pohl, H. O.. 1969-08-01. Two-step rocket engine bipropellant valve concept. https://ntrs.nasa.gov/citations/19690000280
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