CONTROL OF COMBUSTION-CHAMBER PRESSURE AND OXIDANT FUEL RATIO FOR A REGENERATIVELY COOLED HYDROGEN-FLUORINE ROCKET ENGINE

摘要

The design of a chamber-pressure and mixture-ratio control system to increase the safety and speed of testing and to investigate the general controllability of a regeneratively cooled hydrogen-fluorine rocket engine is presented. The dynamics of the components:of the system and of the complete control loop are investigated. Time-history records of combustion-chamber pressure and mixture ratio illustrating control-system performance are presented. The system proved capable of starting a hydrogen-fluorine rocket engine, providing stable operation to within ±2 percent of the preset values of chamber pressure and mixture ratio, and limiting transient deviations in oxidant-fuel ratio sufficiently to avoid a stoichiometric mixture.