Increased capabilities of the 30-cm diameter Hg ion thruster

Rawlin, Vincent K.; Hawkins, C. E.

doi:10.2514/6.1979-910

Cited by 10 publications

(3 citation statements)

References 9 publications

(7 reference statements)

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“…6 for the small cathode orifice geometry. The maximum attainable current density Was about the same as'that of the 8 30-cm thruster.…”

supporting

confidence: 48%

Performance capabilities of the 8-cm Mercury ion thruster

Mantenieks

1981

15th International Electric Propulsion

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The 8-cm Hg ion tnruster system was developed primarily to provide N-S station keeping of satellites with masses up to about 1800 kg. The on-orbit propulsion requirements of recently proposed Large Space Systems (LSS) are beyond the capabilities of the present 8-cm thruster system operated at baseline conditions. This paper presents a preliminary characterization of the performance capabilities of the 8-cm thruster in order to initiate an evaluation of its application to LSS propulsion requirements. With minor thruster modifications, the thrust was increased by about a factor of four while the discharge voltage was reduced from 39 to 22 volts. The thruster was operated over a range of specific impulse of 1950 to 3040 seconds and a maximum total efficiency of about 54 percent was attained. Preliminary analysis of component lifetimes, as determined by temperature and spectroscopic line intensity measurements, indicated acceptable thruster lifetimes are anticipated at the high power level operation. No attempts were made as yet to optimize thruster performance.-

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“…6 for the small cathode orifice geometry. The maximum attainable current density Was about the same as'that of the 8 30-cm thruster.…”

supporting

confidence: 48%

Performance capabilities of the 8-cm Mercury ion thruster

Mantenieks

1981

15th International Electric Propulsion

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“…The addition of the third(g~id has enabled the 30-cm optics to reach minimum R values of about 0.25. 9) The reason for the difference in performance between ~,e 8-and 30-cm optics is not known at present.…”

Section: Resultsmentioning

confidence: 99%

Extended performance 8-cm mercury ion thruster

Mantenieks

1982

16th International Electric Propulsion Conference

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A slightly modified 8-cm Hg ion thruster has demonstrated significant increases in performance. Thrust, for example, nas been increased by almost a factor of five over that ot the baseline thruster. Uiscussed in this paper are (1) thruster operation with various three grid ion optics configurations, (2) thruster performance as a function of accelerator grid open area, cathode baffle, and cathode orifice size, ana (3) a life test of 614 hours at a beam current of 2bO rnA (17.5 mN thrust). Highest thruster efficiency was obtained with the smallest open area acc2ierator grid. The benefits in efficiency from the low neutral loss gr'ids were mitigated, however, by the limitation such grids place on attainable ion beam current densities. HIe thruster components suffered negligiole weight losses during the life tpst, which indicated that operation of the 8-cm thruster at extendea levels of thrust and power is possible with no significant loss of lifetime.

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“…In the opinion of the authors, advanced thrusters will be of the three grid type, (13,14) utilize a more complicated magnetic field configuration, (15916) and operate at higher power densities than the baseline thruster. A preliminary calculation of the impact of these approaches indicated that a circular 30-cm thruster would have a mass of 11.4 kg when operated at power densities of about a factor of five greater than the baseline thruster.…”

Section: Element Description Thrustermentioning

confidence: 99%