Two prototype bismuth propellant feed systems were constructed and operated in conjunction with a propellant vaporizer. One system provided bismuth to a vaporizer using gas pressurization but did not include a means to measure the flow rate. The second system incorporated an electromagnetic pump to provide fine control of the hydrostatic pressure and a new type of in-line flow sensor that was developed for accurate, real-time measurement of the mass flow rate. High-temperature material compatibility was a driving design requirement for the pump and flow sensor, leading to the selection of Macor for the main body of both components. Posttest inspections of both components revealed no degradation of the material. The gas pressurization system demonstrated continuous pressure control over a range from zero to 200 torr. In separate proof-of-concept experiments, the electromagnetic pump produced a linear pressure rise as a function of current that compared favorably with theoretical pump pressure predictions, producing a pressure rise of 10 kPa at 30 A. Preliminary flow sensor operation indicated a bismuth flow rate of 6 mg/s with an uncertainty of plus or minus 6%. An electronics suite containing a real-time controller was successfully used to control the entire system, simultaneously monitoring all power supplies and performing data acquisition duties. Polzin, K. A. and Markusic, T. E. and Stanojev, B. J. Jet Propulsion Laboratory; Marshall Space Flight Center NASA/TM-2007-214958, M-1187 NAS7-03001 ANODES; BISMUTH; LIQUID ROCKET PROPELLANTS; SPECIFIC IMPULSE; FEED SYSTEMS; PROTOTYPES; DATA ACQUISITION; FLOW VELOCITY; REAL TIME OPERATION; ELECTROMAGNETIC PUMPS; CONTROL SYSTEMS DESIGN; MASS FLOW RATE; PRESSURE REGULATORS