Accomplishment and prospect of isas electric propulsion

Toki, Kyoichiro; Kuninaka, Hitoshi; Shimizu, Yukio; Kuriki, K.

doi:10.1016/s0094-5765(01)00177-1

Cited by 5 publications

(3 citation statements)

References 5 publications

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“…These make the arcjet thruster one of the most practical technologies for north-south station-keeping of communication satellites [1]. Research efforts on the performance of arcjet thruster and related physics are continuing for developing various special applications of different power levels, propellant types and working situation [2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Plume Parameters and Thruster Properties of a Low Power Arcjet

Pan¹,

Meng²,

Huang³

et al. 2010

AIP Conference Proceedings

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Abstract.A low power arcjet-thruster of 1 kW-class with gas mixture of H 2 -N 2 or pure argon as the propellant is fired at a chamber pressure about 10 Pa. The nozzle temperature is detected with an infrared pyrometer; a plate set perpendicular to the plume axis and connected to a force sensor is used to measure the thrust; a probe with a tapered head is used for measuring the impact pressure in the plume flow; and a double-electrostatic probe system is applied to evaluate the electron temperature. Results indicate that the high nozzle temperature could adversely affect the conversion from enthalpy to kinetic energy. The plume flow deviates evidently from the LTE condition, and the rarefied-gas dynamic effect should be considered under the high temperature and low-pressure condition in analyzing the experimental phenomena.

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Section: Introductionmentioning

confidence: 99%

Plume Parameters and Thruster Properties of a Low Power Arcjet

Pan¹,

Meng²,

Huang³

et al. 2010

AIP Conference Proceedings

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“…The use of arcjets for satellite propulsion has expanded the operating realm of these devices and has increased the desire for better understanding of the physical basics in the process [1]. There are several key factors that affect the performance of arc discharges in an arcjet thruster, among which the arc-electrode interaction and electrode erosion are important.…”

Section: Introductionmentioning

confidence: 99%

“…In arcjet thrusters, the measurement of electrode temperatures and the study of arc attachment are often difficult due to the fact that these electrode surfaces are seemingly inaccessible, and that the plasma arc itself is a likely source of optical interference. Using specially designed anode/nozzle, the arc root behavior under steady working condition was studied [1,2]. However, the dynamic development of the arc root attachment from the time of ignition to the stably working condition is of great interest, as failure analysis show that most electrode erosion occur in the arcjet ignition process [3].…”

Section: Introductionmentioning

confidence: 99%

Plasma and Electrode Emissions from a 1 kW Hydrogen-Nitrogen Arcjet Thruster

Huang

Pan²,

Meng³

et al. 2010

AIP Conference Proceedings

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Electric propulsion reliability: Statistical analysis of on-orbit anomalies and comparative analysis of electric versus chemical propulsion failure rates

Saleh

Geng

et al. 2017

Acta Astronautica

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With a few hundred spacecraft launched to date with electric propulsion (EP), it is possible to conduct an epidemiological study of EP's on orbit reliability. The first objective of the present work was to undertake such a study and analyze EP's track record of on orbit anomalies and failures by different covariates. The second objective was to provide a comparative analysis of EP's failure rates with those of chemical propulsion. Satellite operators, manufacturers, and insurers will make reliability-and risk-informed decisions regarding the adoption and promotion of EP on board spacecraft. This work provides evidence-based support for such decisions. After a thorough data collection, 162 EP-equipped satellites launched between January 1997 and December 2015 were included in our dataset for analysis. Several statistical analyses were conducted, at the aggregate level and then with the data stratified by severity of the anomaly, by orbit type, and by EP technology. Mean Time To Anomaly (MTTA) and the distribution of the time to (minor/major) anomaly were investigated, as well as anomaly rates.The important findings in this work include the following: (1) Post-2005, EP's reliability has outperformed that of chemical propulsion; (2) Hall thrusters have robustly outperformed chemical propulsion, and they maintain a small but shrinking reliability advantage over gridded ion engines. Other results were also provided, for example the differentials in MTTA of minor and major anomalies for gridded ion engines and Hall thrusters. It was shown that: (3) Hall thrusters exhibit minor anomalies very early on orbit, which might be indicative of infant anomalies, and thus would benefit from better ground testing and acceptance procedures; (4) Strong evidence exists that EP anomalies (onset and likelihood) and orbit type are dependent, a dependence likely mediated by either the space environment or differences in thrusters duty cycles; (5) Gridded ion thrusters exhibit both infant and wear-out failures, and thus would benefit from a reliability growth program that addresses both these types of problems.

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Accomplishment and prospect of isas electric propulsion

Cited by 5 publications

References 5 publications

Plume Parameters and Thruster Properties of a Low Power Arcjet

Plume Parameters and Thruster Properties of a Low Power Arcjet

Plasma and Electrode Emissions from a 1 kW Hydrogen-Nitrogen Arcjet Thruster

Electric propulsion reliability: Statistical analysis of on-orbit anomalies and comparative analysis of electric versus chemical propulsion failure rates

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