A DESIGN OF A PROPULSION RESEARCH LABORATORY.
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING
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The report describes in detail a system design for a propulsion research laboratory intended to support graduate studies at the Air Force Institute of Technology. The system supports experimental rocket motors up to 500 pounds thrust. Major design considerations were the state-of-the-art, flexibility, safety, and low direct cost. A gaseous propellant system employs two stages of pressure regulation and sonic venturi flow metering. The completely electrical control system uses a flow chart control console layout and features a manually stepped control sequencer and an analog computing circuit for the real time calculation and display of propellant mass flow rates. The measurement instrumentation achieves maximum flexibility by means of a patch panel for the selection of transducers, signal conditioning circuits and oscillograph recorder channels. The signal conditioning system has been designed for local fabrication at relatively low cost and includes manually operated multi-step calibration circuits. The report includes in its appendices recommended implementation schedule, system safety considerations, a tentative operating procedure, and a visit report made in support of this design. Author