ライブラリ登録: Guest
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

NOZZLE EROSION CHARACTERIZATION IN A NON-METALLIZED SOLID-PROPELLANT ROCKET MOTOR SIMULATOR

巻 7, 発行 3, 2008, pp. 209-222
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i3.40
Get accessGet access

要約

An understanding of the nozzle throat erosion processes and developing methods for mitigation of erosion rate can allow higher operating pressure of rocket motors. To evaluate the individual effects of oxidizing species on the chemical erosion rates of rocket nozzles (e.g., G-90 graphite material), a solid-propellant rocket motor simulator (RMS) was designed and tested. The RMS simulates the mass fractions of the oxidizing product species (like H2O, OH, CO2) and product composition temperature generated from a non-metallized composite propellant, called Propellant S, at the throat region. Test firings of the RMS have been conducted at various chamber pressures up to 6.9 MPa (1,000 psia). This instrumented RMS test setup incorporates the use of a realtime X-ray radiography system for measurement of the instantaneous contour of the rocket nozzle throat region. The instantaneous erosion rates of the G-90 nozzle throat were deduced from the recorded X-ray images. Holding oxidizing species concentrations and gas temperature constant, nozzle erosion rates measured from the RMS were correlated to operating pressure. The correlation shows the strong effect of increased heat transfer rates at higher pressures on increased nozzle erosion rates. To avoid nozzle throat erosion, an optional nozzle boundary-layer control system (NBLCS) was utilized in the RMS and was found to work efficiently for preventing nozzle erosion of G-90 graphite material.

参考
  1. Chiaverini, M.J., Sauer, J.A., and Munson, S.M., Laboratory Characterization of Vortex-Cooled Thrust Chambers for Methane/O2 and H2/O2.

  2. Abu-Irshaid, E.M. and Majdalani, J., Hydrodynamic Instability of the Bidirectional Vortex.

  3. Bradley, D., Dixon-Lewis, G., Habik, S.E., and Mushi, E.M.J., The Oxidation of Graphite Powder in Flame Reaction Zones.

  4. Kuo, K.K., Acharya, R., Boyd, E., and Thynell, S.T., Succinic Acid/Poly-Vinyl Acetate Pyrolysis Study for Boundary Layer Control in High-Pressure Graphite Rocket Nozzles.

  5. Chiaverini, M.J., Malecki, M.J., Sauer, J.A., Knuth, W.H., Grammer, D.J., and Majdalani, J., Vortex Thrust Chamber Testing and Analysis for O2-H2 Propulsion Applications.

Begell Digital Portal Begellデジタルライブラリー 電子書籍 ジャーナル 参考文献と会報 リサーチ集 価格及び購読のポリシー Begell House 連絡先 Language English 中文 Русский Português German French Spain