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International Journal of Energetic Materials and Chemical Propulsion

Erscheint 6 Ausgaben pro Jahr

ISSN Druckformat: 2150-766X

ISSN Online: 2150-7678

The Impact Factor measures the average number of citations received in a particular year by papers published in the journal during the two preceding years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) IF: 0.7 To calculate the five year Impact Factor, citations are counted in 2017 to the previous five years and divided by the source items published in the previous five years. 2017 Journal Citation Reports (Clarivate Analytics, 2018) 5-Year IF: 0.7 The Immediacy Index is the average number of times an article is cited in the year it is published. The journal Immediacy Index indicates how quickly articles in a journal are cited. Immediacy Index: 0.1 The Eigenfactor score, developed by Jevin West and Carl Bergstrom at the University of Washington, is a rating of the total importance of a scientific journal. Journals are rated according to the number of incoming citations, with citations from highly ranked journals weighted to make a larger contribution to the eigenfactor than those from poorly ranked journals. Eigenfactor: 0.00016 The Journal Citation Indicator (JCI) is a single measurement of the field-normalized citation impact of journals in the Web of Science Core Collection across disciplines. The key words here are that the metric is normalized and cross-disciplinary. JCI: 0.18 SJR: 0.313 SNIP: 0.6 CiteScore™:: 1.6 H-Index: 16

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LIFE TESTING AND PERFORMANCE EVALUATION OF 1.0 N THRUSTER FOR SATELLITE APPLICATIONS BASED ON "HYDROGEN PEROXIDE"

Volumen 20, Ausgabe 2, 2021, pp. 1-20
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2021032041
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ABSTRAKT

Satellite propulsion is designed to provide capability to perform certain operations such as attitude control, orbit transfer, orbit maneuver, and de-orbiting at the end of life. Use of green propellants such as hydrogen peroxide (H2O2) in satellite propulsion is not new. A significant amount of work was carried out in the 1960s at NASA laboratories on hydrogen peroxide decomposition and its applications but the effort was subsequently abandoned with the advent of effective hydrazine catalysts. Recently, hydrazine, in spite of having high specific impulse and propulsive performance, has been banned by the European Union because of its toxic nature to the environment. An alternative to hydrazine is high concentrated hydrogen peroxide (high-test peroxide, HTP), often referred to as a "Green" or low-toxicity propellant. The purpose of this research is to design a green propellant-based thruster, capable to work over a longer period of time without deterioration so that the thrusters could be mounted in future satellite as a reaction control system. The work presented in this paper is not only about brief discussion of design methodology to develop HTP-based thruster but also focuses in detail on the life testing of thruster for over 7000 s in steady-state mode with acceptable chamber pressure and roughness. Results obtained, i.e., the chamber pressure in particular, are presented and chamber pressure degradation over time has been studied. Through this work, successful life testing of thruster has been performed and the research work proved the potential of HTP-based green propellant thruster configuration for use in reaction control system of future satellites.

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