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Vahrenkamp, R. P.

Publications and source records attributed to Vahrenkamp, R. P..

7 records
All sourcesNASA NTRSDOE OSTI
NASA NTRS1976

A doubly charged ion model for ion thrusters

A theoretical equilibrium model of doubly charged ion production and loss processes in electron bombardment ion thrusters is presented. The model is shown to predict double ion density levels accurately for 15 and 30 cm diameter thrusters operating with several different grid sets and at several different power levels. The model indicates the dominant mechanism of double ion production involves the singly charged ground state. This result is used to develop a much simpler model which, along with correlations of the average plasma properties, can be used to determine the double ion density in thrusters with acceptable accuracy.

Peters, R. R.↗
NASA NTRS1976

High power operation of a 30-cm mercury bombardment ion thruster

The nominal input power of a 30-cm mercury bombardment ion thruster is 2.5 kW. A representative 30-cm thruster has been operated at higher power levels by increasing either the ion beam voltage or current. Initial results indicate that higher voltage (high specific impulse) operation requires only minor modifications in thruster design. Higher current (low specific impulse) operation, on the other hand, requires improvements in the capabilities of the discharge chamber and ion optics assembly designs to meet lifetime and/or performance specifications. Experimental data is presented and considerations for high power operation (up to 10 kW) are discussed.

Poeschel, R. L.↗
NASA NTRS1976

Characteristics of a 30-cm thruster operated with small hole accelerator grid ion optics

Small hole accelerator grid ion optical systems have been tested as a possible means of improving 30-cm ion thruster performance. The effects of small hole grids on the critical aspects of thruster operation including discharge chamber performance, doubly-charged ion concentration, effluent beam characteristics, and plasma properties have been evaluated. In general, small hole accelerator grids are beneficial in improving thruster performance while maintaining low double ion ratios. However, extremely small accelerator aperture diameters tend to degrade beam divergence characteristics. A quantitative discussion of these advantages and disadvantages of small hole accelerator grids, as well as resulting variations in thruster operation characteristics, is presented.

Vahrenkamp, R. P.↗
NASA NTRS1975

Performance mapping of a 30 cm engineering model thruster

A 30 cm thruster representative of the engineering model design has been tested over a wide range of operating parameters to document performance characteristics such as electrical and propellant efficiencies, double ion and beam divergence thrust loss, component equilibrium temperatures, operational stability, etc. Data obtained show that optimum power throttling, in terms of maximum thruster efficiency, is not highly sensitive to parameter selection. Consequently, considerations of stability, discharge chamber erosion, thrust losses, etc. can be made the determining factors for parameter selection in power throttling operations. Options in parameter selection based on these considerations are discussed.

Poeschel, R. L.↗