Fluidic proportional thruster for SPARCS 4
Design, development, fabrication, and acceptance test results for two fluidic proportional thrusters for use in SPARCS 4
Honda, T. S.↗
SEARCH · Engineering Papers
Results for “Thrusters”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
A survey of Kaufman thruster cathodes
Survey of various cathodes used in Kaufman ion thruster
Nakanishi, S.↗
Kaufman thruster development at Lewis Research Center
Optimization of mercury electron bombardment thrusters in SERT program
Kerslake, W. R.↗
Quasi-steady and short pulse discharge thruster experiments
Propulsive performance and erosion behavior of accelerator nozzle operating as short pulse discharge or quasi-steady solid Teflon propellant plasma thruster
Guman, W. J.↗
Preliminary investigations of ion thruster cathodes
Mercury vapor fed hollow cathodes for electron bombardment ion thrusters
Goldstein, R.↗
Development of a platinum-thorium oxide alloy for resistojet thruster use
Platinum-thorium oxide alloy for resistojet thruster showing increase in stress rupture life
Albert, H. J.↗
Experiments on a permanent-magnet, completely radiation-cooled magnetoplasmadynamic arc thruster
Performance tests of permanent-magnet, radiation cooled magnetoplasmadynamic arc thruster
Bishop, A. R.↗
A 1000-hour test of a dual grid, electrostatic beam deflection accelerator system on a 5-centimeter-diameter Kaufman thruster
Dual grid accelerator system with electrostatic beam deflection capability tested on 5-cm diameter Kaufman thruster for 1000 hours
Lathem, W. C.↗
Maximum propellant utilization in an electron-bombardment thruster
Maximum propellant utilization in electron bombardment ion thrusters using mercury for propellant
Kaufman, H. R.↗
Effect of neutralizer position on accelerator wear for a 30 centimeter diameter ion bombardment thruster
Neutralizer location for minimum accelerator erosion on 30 centimeter diameter ion bombardment thruster
Bechtel, R. T.↗
Deflectable beam linear strip cesium contact ion thruster system
Deflectable dual beam, linear strip cesium contact, ion thruster system design and performance testing
Dulgeroff, C. R.↗
Effect of facility backsputtered material on performance of glass-coated accelerator grids for Kaufman thrusters
Facility backsputtered material effect on performance of glass-coated accelerator grids for Kaufman electron bombardment thrusters
Banks, B. A.↗
Preliminary results of the operation of a SERT II thruster on argon
SERT II electron bombardment thruster operation with Ar and Hg propellants
Schertier, R. J.↗
Integration of a flight prototype power conditioner with a 20-cm ion thruster
Oxide hollow cathode ion thruster power conditioner, evaluating electrical efficiency, weight, reliability integration and testing
Benson, G. C.↗
Pressure measurements in the exhaust of a pulsed megawatt MPD ARC thruster
Pulsed megawatt MPD arc thruster exhaust pressure measurements, discussing time dependence, peak dynamic and static pressures, etc
Michels, C. J.↗
A study of environmental effects caused by cesium from ion thrusters
The ATS-F satellite will carry two cesium ion thrusters. Cesium is a material that is not present in the upper atmosphere, and there is concern that the introduction of this material may result in some unexpected behavior. A study has been conducted to assess the magnitude of the effects that are to be expected. No observable effects were found as a result of the study. Consideration was given to the origin and destination of the material and the various reactions that could occur. The origin was considered to be anywhere in space from altitudes of about 100 km upward. The probable short term destination is in the form of cesium ions trapped in the earth's magnetic field or as ions and atoms in the heterosphere. The maximum possible number of cesium atoms in the field of view of an earth based observer is of the order of one million per square centimeter, far too few to be observable by visible, near-visible, or radio-frequency means. Further, no phenomena could be found that would result in the occurance of an observable event.
Source record↗
Ion-thruster propellant utilization
The evaluation and understanding of maximum propellant utilization, with mercury used as the propellant are presented. The primary-electron region in the ion chamber of a bombardment thruster is analyzed at maximum utilization. The results of this analysis, as well as experimental data from a range of ion-chamber configurations, show a nearly constant loss rate for unionized propellant at maximum utilization over a wide range of total propellant flow rate. The discharge loss level of 1000 eV/ion was used as a definition of maximum utilization, but the exact level of this definition has no effect on the qualitative results and little effect on the quantitative results. There are obvious design applications for the results of this investigation, but the results are particularly significant whenever efficient throttled operation is required.
Kaufman, H. R.↗
Design and development of a small structurally integrated ion thruster system
A 5 cm structurally integrated ion thruster has been developed for attitude control and stationkeeping of synchronous satellites. With 2-D vectorable grids, thrust is 0.56 mlb at a beam voltage of 1200 V, total mass efficiency is 64%, and electrical efficiency is 46.8%. Nonvectoring thrust of 0.41 is demonstrated at very low specific impulse with dielectric coated grids. Structural integrity is demonstrated with dielectric coated grids for shock (30 G), sinusoidal (9 G), and random (19 G squared/Hz) accelerations. System envelope is 31.6 cm long by 14 cm flange B.C. with a mass of 8.5 kg including 6.2 Kg mercury propellant.
Hyman, J., Jr.↗