Abstract
Requirements for the control system of a ramjet were established and used to design a fluidic fuel control system. The system consisted of a fuel mass flow rate sensor (fixed impedance type), an air mass flow rate sensor (variable impedance), an equivalence ratio computer, and a fuel throttling valve. Each component was tested before integration into a breadboard model. The integrated system was tested with air and with prospective ramjet propellants (air and hydrogen). With the exception of the mechanical fuel valve, all components performed within the established specifications. The fuel control system successfully metered the fuel over the entire ranges of air flow, engine inlet total pressure, and engine exit impedance in accordance with the equivalence ratio command that was inserted mechanically.
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