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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

Indexed in

OPTIMIZATION OF GRAIN AND STRUCTURE DESIGN OF A SOLID ROCKET MOTOR

Volumen 7, Ausgabe 5, 2008, pp. 437-451
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i5.60
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ABSTRAKT

This work discusses the development of representative subsystem physical models and methods for the optimization of a solid rocket motor. The effect of the grain configuration on the optimum design is examined in detail along with other subsystems (winded case, case and nozzle insulation, etc.), which are modelled and integrated with the trajectory calculations to achieve the specified mission. The insulation mass and volumetric loading are affected by the grain design and are modelled as a function of the web fraction, thrust profile, and length-to-diameter ratio. The parameters optimized (via a genetic algorithm) are motor pressure, expansion ratio, burn time, thrust profile, nozzle exit angle, and grain length-to-diameter ratio. The effects of the various parameters and their relative influence on the optimum design are discussed through a single-stage launch of a capsule to a height of 100 km.

REFERENZEN
  1. Chiang, M.J., Su, Y.P., and Chang, S.D., The Optimization of Solid Rocket Vehicles.

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  3. Shelton, J., Frederick, R.A., and Wilhite, A.W., Launch Vehicle Propulsion Design with Multiple Selection Criteria.

  4. Kamm, Y., Horowitz, D., Brauner, N., and Gany, A., Design Optimization of a Solid Rocket Motor for a Suborbital Space Flight.

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