Propellant injection for MPD thrustersThe propellant gas for a pulsed self-field MPD thruster must be supplied by a valve which will necessarily be separated from the thruster injectors by some ullage volume. A model and experimental data are presented showing the effect of the ullage volume on the propellant pulse shape, along with a discussion of the proper location for the propellant flow choke point(s). Prospective MPD pulse valves are surveyed and the performance of two solenoid valves, one with a pulse length less than 2 milliseconds, is included. Pulse shape data is presented for a thruster specially modified to reduce the ullage volume.
Document ID
19800026220
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jones, R. M. (California Institute of Technology, Jet Propulsion Laboratory, Electrical Power and Propulsion Section, Pasadena Calif., United States)
Date Acquired
August 10, 2013
Publication Date
October 1, 1979
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 79-2074
Meeting Information
Meeting: International Electric Propulsion Conference