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Портал Begell Электронная Бибилиотека e-Книги Журналы Справочники и Сборники статей Коллекции
International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN Печать: 2150-766X
ISSN Онлайн: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2014011243
pages 559-572

FEASIBILITY STUDY OF PARAFFIN-BASED FUELS FOR HYBRID ROCKET ENGINE APPLICATIONS

Elena Toson
Space Propulsion Laboratory, Aerospace Engineering Dept., Politecnico di Milano, I-20156 Milan, MI, Italy
Mario Kobald
German Aerospace Center (DLR), Institute of Space Propulsion, 74239 Hardthausen, Germany
Emanuele Cavanna
Space Propulsion Laboratory, Aerospace Engineering Dept., Politecnico di Milano, I-20156 Milan, MI, Italy
Luigi T. De Luca
Space Propulsion Laboratory (SPLab), Department of Aerospace Science and Technology, Politecnico di Milano, I-20156 Milan, Italy
Giovanni Consolati
Space Propulsion Laboratory, Aerospace Engineering Dept., Politecnico di Milano, I-20156 Milan, MI, Italy
Helmut K. Ciezki
German Aerospace Center (DLR), Institute of Space Propulsion, 74239 Hardthausen, Germany

Краткое описание

This paper describes a combined analysis performed in pure waxes and paraffin-based mixtures that can be used as solid fuels in hybrid rocket engines. Density measurements of pure waxes were performed using a dilatometer. An experimental facility was set up and, after preliminary measurements and calibration, a repeatable procedure was implemented. The implemented instrumentation setup allowed the measure of density in softening and melting intervals. Mechanical uniaxial tensile tests were performed according to Standard ISO 527-1 on pure macro paraffin and microcrystalline wax and on these waxes doped with stearic acid and graphite; elastic modulus, elongation and maximum stress were calculated. Data indicate that ductile rupture is achievable even on pure tested macro paraffin. Moreover, microcrystalline wax was mixed with a synthetic wax characterized by a higher nominal melting temperature in order to improve the softening point up to higher temperatures without compromising regression rate values. Thermal, rheological, viscosimetric, and ballistic experiments were performed on this new fuel formulation. This new formulation is promising for propulsion applications in wide temperature ranges.


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