Plasma properties and performance of mercury ion thrusters
Electron bombardment mercury ion thrustor plasma properties and performance, computing ion beam current, discharge losses and propellant utilization efficiency
Masek, T. D.↗
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SERT II - Mission, thruster performance, and in-flight thrust measurements
SERT 2 spacecraft ion thrustor ground tests and flight operation, tabulating performance data
Goldman, R. G.↗
Exploratory tests on a downstream-cathode MPD thruster
Low power MPD arc thrustor performance with downstream cathode, using Xe propellant
Burkhart, J. A.↗
Operation of a lightweight power conditioner with a hollow-cathode ion thruster
Hollow cathode ion thrustor and lightweight power conditioner of solar-electric propulsion system for unmanned deep space probes
Costogue, E. N.↗
A 30 cm mercury ion thruster module
Low specific impulse hollow cathode mercury thrustor for deep space electric propulsion, using SERT 2 configuration
King, H. J.↗
Bombardment thruster investigations at the Lewis Research Center - 1971
NASA Lewis Research Center Hg electron bombardment ion thrustors research programs
Kerslake, W. R.↗
Cold-flow optimization of gaseous oxygen/gaseous hydrogen injectors for the Space Shuttle APS thruster
Gaseous oxygen/gaseous hydrogen auxiliary propulsion engines, considering cold flow experiments with nonreactive simulant gases
Clapp, S. D.↗
Status of a five-centimeter-diameter ion thruster technology program
Ion thrustor technology and subsystem development program status, describing design and performance characteristics
Banks, B. A.↗
Vectoring of the beam from ion bombardment thrusters
Beam vector control from ion bombardment thrustors with dual grid electrostatic, movable screen electrode and discharge chamber extraction systems
Collett, C. R.↗
Mathematical representation of current density profiles from ion thrusters
Ion thrustor ion beam current density profiles mathematical representation by two parameter equation
Reynolds, T. W.↗
Feasibility studies on an auxiliary propulsion system using MPD thrusters
Auxiliary propulsion system using low power MPD thrustors, discussing feasibility of thrust vectoring with skewed magnetic coil arrangement
Burkhart, J. A.↗
Tests of permanent magnet and superconducting magnet MPD thrusters
Radiation cooled MPD thrustor with permanent and superconducting magnets, describing test facilities and measurement techniques for performance tests
Bishop, A. R.↗
High-pressure gaseous hydrogen/gaseous oxygen thruster
High pressure gaseous hydrogen oxygen auxiliary propulsion systems /APS/ thrustor design and cold flow and hot fire testing for space shuttle requirements
Domokos, S. J.↗
Application of a deflagration plasma gun as a space propulsion thruster
Space propulsion by plasma deflagration gun, measuring specific impulse by piezoelectric probe and pendulum methods
Cheng, D. Y.↗
Throttleable thruster system Final report
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Reeves, D. F.↗
Temporal survey of electron number density and electron temperature in the exhaust of a megawatt MPD-Arc thruster
Temporal and radial profiles are obtained 30 cm downstream from the anode for two peak arc currents (11.2 kA and 20 kA) and for various auxiliary magnetic fields (0, 1.0 T, and 2.0T) using the Thomson scattering technique. Average density and temperature are relatively constant for over 100 microseconds with significant fluctuations. Radial profiles obtained are relatively flat for 4 cm from the axis. Compared to earlier 20 cm data, the exhaust density has decreased significantly, the average temperature (4.6 eV) has not changed, and the density hole with an auxiliary magnetic field has enlarged.
Michels, C. J.↗
Quasi-linear theory of electron density and temperature fluctuations with application to MHD generators and MPD arc thrusters
Fluctuations in electron density and temperature coupled through Ohm's law are studied for an ionizable medium. The nonlinear effects are considered in the limit of a third order quasi-linear treatment. Equations are derived for the amplitude of the fluctuation. Conditions under which a steady state can exist in the presence of the fluctuation are examined and effective transport properties are determined. A comparison is made to previously considered second order theory. The effect of third order terms indicates the possibility of fluctuations existing in regions predicted stable by previous analysis.
Smith, M.↗
Operational characteristics of a translation screen grid beam deflection system for a 5-cm Kaufman thruster
Measurements of beam deflection angle with respect to spring positioning power and accelerator impingement current as a function of deflection angle were made on a 5-cm diameter system. Response time measurements on the translational grid beam deflection system showed that the time for the maximum deflection angle analyzed (+16.4 deg to -16.4 deg) could be reduced by a factor of nine by increasing the heating power applied to the positioning spring from 4 to 16 watts. At 14 watts the response time for maximum deflection was about 1 minute.
Lathem, W. C.↗