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International Journal of Energetic Materials and Chemical Propulsion

年間 6 号発行

ISSN 印刷: 2150-766X

ISSN オンライン: 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

Indexed in

MODELING OF A SHORT ACTION MOTOR DISCHARGING A WEIGHT

巻 12, 発行 4, 2013, pp. 275-306
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2013005392
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要約

This paper investigates the interior ballistics of a unique concept for short action motors, based on a rocket-type combustion chamber discharging a weight through an exhaust tube. Depending on the overall system requirements, different kinds of propellant and weight may be considered. In the current study a system comprising a granular solid propellant and a solid weight is considered in order to capture the basic mechanisms of the impulse augmentation. A simplified lumped parameters model and a detailed two-phase flow model have been formulated and the fundamental characteristics of the propulsion system have been computed and analyzed. The study reveals that for certain system parameters with a given propellant mass the total impulse as well as the specific impulse may be significantly larger than those generated by a conventional rocket motor. The theoretical parametric investigation provides a good understanding on how different system parameters influence the in-terior ballistics processes, and can provide guidelines to the design of thrusters. Such short action motors may be beneficial for spacecraft and missile station keeping and trajectory correction, applying mini-thrusters of this kind, as well as for separating large space bodies such as missiles/launcher stages, satellites, etc.

によって引用された
  1. Michaels Dan, Gany Alon, Theoretical and experimental study of a thruster discharging a weight, Acta Astronautica, 99, 2014. Crossref

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