The fundamental objective of the program was to investigate new concepts for integration of com¬ponents for low pressure liquid propellant rocket engines. Combining the functions of many components in complete subsystems, and use of new design concepts in the subsystems greatly reduced the number of parts required to perform subsystem functions. System integration and simplification ultimately lead to im¬proved reliability and weight reduction.nTwo integrated subsystems were investigated: a system for propellant tank pressurization, and a system for propellant flow control. The pressurization system included all the functions normally provided by fill and drain valves, solenoid operated shut-off valve, pressure regulator, check-valves and relief valves. The propellant system included all the functions normally provided by fill and drain valves, check valves, shut-off valves, and propellant mixture ratio control device.
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