Low power hydrazine arcjet thruster study

Kurtz, H.; Zube, Dieter M.; Glocker, B.; Auweter‐Kurtz, Monika; Kinnersley, Mark; Steenborg, M.; Matthaeus, G.; Willenbockel, H.

doi:10.2514/6.1992-3116

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Cited by 7 publications

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“…The thrust and specific impulse increase and the efficiency decreases with increasing input power, agreeing with previous work. [10] It can also be seen that the rising temperature of the anode nozzle at the later stage firing from 214 s to 350 s could have an unfavorable effect on the produced thrust. That is, high nozzle temperature could somehow adversely affect the conversion of electric power expended in the arc through the enthalpy of arc-heated high-temperature gas into kinetic energy for producing thrust, by expansion in the nozzle.…”

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confidence: 99%

Effects of Anode Temperature on Working Characteristics and Performance of a Low Power Arcjet Thruster

Pan

2009

Chinese Phys. Lett.

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An arc-heated thruster of 130-800 W input power is tested in a vacuum chamber at pressures lower than 20 Pa with argon or H2-N2 gas mixture as propellant. The time-dependent arc voltage-current curve, outside-surface temperature of the anode nozzle and the produced thrust of the firing arcjet thruster are measured in situ simultaneously, in order to analyze and evaluate the dependence of thruster working characteristics and output properties, such as specific impulse and thrust efficiency, on nozzle temperature.

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confidence: 99%