Abo Bibliothek: Guest
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

INVESTIGATION OF SOLID OXIDIZER AND GASEOUS FUEL COMBUSTION PERFORMANCE USING AN ELEVATED PRESSURE COUNTERFLOW EXPERIMENT FOR REVERSE HYBRID ROCKET ENGINE

Volumen 11, Ausgabe 6, 2012, pp. 511-536
DOI: 10.1615/IntJEnergeticMaterialsChemProp.2013005785
Get accessGet access

ABSTRAKT

Pressurized counter/low burner and static-fired motor studies were conducted to explore the possibility of a reverse hybrid system, having a solid oxidizer and gaseous fuel. Theoretical performance analysis indicates such a system may yield specific impulse and density specific impulse similar to composite solid propellants. Pressurized counter/low flame studies, conducted using pressed ammonium perchlorate (AP) pellets and gaseous ethylene, show three pressure dependent combustion regimes. AP decomposition, for pressures below 1 MPa, is controlled by heat transfer from the resulting diffusion flame, which forms between the fuel and decomposition products of AP. In this low pressure regime, the AP burning rate is found to increase with flame strain rate and pressure, yielding measured values between 0.1 to 0.5 mm/s. As pressure increases, the monopropellant flame moves closer to the oxidizer surface until the pressure reaches the self-decomposition limit, at which point the monopropellant flame becomes nearly independent of the diffusion flame. Further increasing the pressure yields burning rates between 0.4 to 0.7 cm/s, which are consistent with the literature. Variation of flame strain rate under these conditions has little or no influence on the AP burning rate for the range of flow conditions tested. Similar studies conducted with methane suggest burning rates are unaffected by fuel type. Lab-scale static motor firings were conducted to examine ignition, variation of fuel flow rate and initial motor pressure, and system performance. Results indicate that successful motor operation requires initial pressures capable of boosting the system into the higher burning rate regimes.

REFERENZIERT VON
  1. Connell Terrence L., Risha Grant A., Yetter Richard A., Young Gregory, Combustion of Boron and Fluorocarbon Solid Fuels in a Hybrid Rocket, 49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, 2013. Crossref

  2. Connell Terrence L., Risha Grant A., Yetter Richard A., Roberts Colin W., Young Gregory, Boron and Polytetrafluoroethylene as a Fuel Composition for Hybrid Rocket Applications, Journal of Propulsion and Power, 31, 1, 2015. Crossref

  3. Isert Sarah, Son Steven F., The Relationship Between Flame Structure and Burning Rate for Ammonium Perchlorate Composite Propellants, in Energetic Materials, 25, 2017. Crossref

  4. Hendley Coit T., Connell Terrence L., Wilson Daniel, Young Gregory, Catalytic Decomposition of Nitrous Oxide for Use in Hybrid Rocket Motors, Journal of Propulsion and Power, 37, 3, 2021. Crossref

Digitales Portal Digitale Bibliothek eBooks Zeitschriften Referenzen und Berichte Forschungssammlungen Preise und Aborichtlinien Begell House Kontakt Language English 中文 Русский Português German French Spain