Suscripción a Biblioteca: Guest
International Journal of Energetic Materials and Chemical Propulsion

Publicado 6 números por año

ISSN Imprimir: 2150-766X

ISSN En Línea: 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

COMBUSTION ISSUES AND APPROACHES FOR CHEMICAL MICROTHRUSTERS

Volumen 6, Edición 4, 2007, pp. 393-424
DOI: 10.1615/IntJEnergeticMaterialsChemProp.v6.i4.10
Get accessGet access

SINOPSIS

In the present paper, results from the development of a meso/micro scale liquid-propellant thruster are reported along with a discussion of the usage of microthrusters in small spacecraft and the effects of downsizing on combustion performance. In particular, combustion of liquid nitromethane in a thruster combustion chamber with a volume of 108 mm3 and diameter of 5 mm was experimentally investigated. The meso-scale combustor utilized a vortex combustion concept, in which monopropellants were injected tangentially from the front end of the cylindrical combustor and combustion products exited the chamber tangentially at the other end. Although combustion was achievable at pressures as low as 150 psig, pressures as high as 350 psig were required for complete combustion. Combustion at atmospheric pressure was achieved only with the addition of small quantities of oxygen. To complement the experiments, a comprehensive numerical analysis was developed to study the combustion of liquid monopropellant in a small-volume vortex chamber based on a two-phase flow analysis using the level-set approach. The model allows for a detailed investigation of the liquid-film motion and gas-phase flow development. Combustion chambers and nozzles were fabricated from ceramics (alumina) because of the high flame temperatures required to sustain gas-phase reactions. Operation of thrusters on hydrogen-air-oxygen mixtures at a combustion chamber pressure of 40 psig was demonstrated to produce characteristic velocity efficiencies of approximately 90%.

CITADO POR
  1. Louisos William F., Hitt Darren L., Numerical Studies of Supersonic Flow in Bell-Shaped Micronozzles, Journal of Spacecraft and Rockets, 51, 2, 2014. Crossref

  2. Ran Jingyu, Li Liya, Du Xuesen, Wang Ruirui, Pan Wenli, Tang Weimin, Numerical investigations on characteristics of methane catalytic combustion in micro-channels with a concave or convex wall cavity, Energy Conversion and Management, 97, 2015. Crossref

  3. Kundu Pijus, Sinha Arun Kumar, Bhattacharyya Tarun K., Das Soumen, $\hbox{MnO}_{2}$ Nanowire Embedded Hydrogen Peroxide Monopropellant MEMS Thruster, Journal of Microelectromechanical Systems, 22, 2, 2013. Crossref

  4. Baird James K., Lang Joshua R., Hiatt Andrew T., Frederick Robert A., Electrolytic Combustion in the Polyvinyl Alcohol Plus Hydroxylammonium Nitrate Solid Propellant, Journal of Propulsion and Power, 33, 6, 2017. Crossref

  5. Rahman Asad, Chin Jitkai, Kabir Feroz, Hung Yew Mun, Characterization and thrust measurements from electrolytic decomposition of ammonium dinitramide (ADN) based liquid monopropellant FLP-103 in MEMS thrusters, Chinese Journal of Chemical Engineering, 26, 9, 2018. Crossref

  6. Chai Wai Siong, Chin Jitkai, Cheah Kean How, Koh Kai Seng, Ku Chik Tengku F.Wahida, Calorimetric study on electrolytic decomposition of hydroxylammonium nitrate (HAN) ternary mixtures, Acta Astronautica, 162, 2019. Crossref

  7. Chai Wai Siong, Sun Dashan, Cheah Kean How, Li Gang, Meng Hua, Co-Electrolysis-Assisted Decomposition of Hydroxylammonium Nitrate–Fuel Mixtures Using Stainless Steel–Platinum Electrodes, ACS Omega, 5, 31, 2020. Crossref

  8. Baird James K., Frederick Robert A., Thermochemistry of Combustion in Polyvinyl Alcohol + Hydroxylammonium Nitrate, Aerospace, 8, 5, 2021. Crossref

  9. Li Yueh-Heng, Peng Kuan-Hsun, Kao Hsiao-Hsuan, Interaction between flow structure and chemical reaction around the perforated gap of stainless steel–platinum catalytic partition reactor, International Journal of Heat and Mass Transfer, 176, 2021. Crossref

  10. Wu Ming-Hsun, Yetter Richard, Yang Vigor, Development and Characterization of Ceramic Micro Chemical Propulsion and Combustion Systems, 46th AIAA Aerospace Sciences Meeting and Exhibit, 2008. Crossref

Portal Digitalde Biblioteca Digital eLibros Revistas Referencias y Libros de Ponencias Colecciones Precios y Políticas de Suscripcione Begell House Contáctenos Language English 中文 Русский Português German French Spain