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International Journal of Energetic Materials and Chemical Propulsion
ESCI SJR: 0.142 SNIP: 0.16 CiteScore™: 0.29

ISSN 印刷: 2150-766X
ISSN オンライン: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v7.i3.30
pages 193-207

COMBUSTION BEHAVIOUR INVESTIGATION OF SOLID FUELS USING A MICRO-SIZED HYBRID ROCKET MOTOR

Luciano Galfetti
Politecnico di Milano
Paolo Grassi
SPLab, Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano, I - 20156 Milan
Christian Paravan
Politecnico di Milano, Department of Aerospace Science and Technology, Via La Masa 34, Milan, 20133, Italy
Viviana Luoni
SPLab, Dipartimento di Ingegneria Aerospaziale, Politecnico di Milano, I - 20156 Milan
Luigi Pietro Maria Colombo
SPLab, Department of Aerospace Engineering, Politecnico di Milano, Italy

要約

A micro-sized hybrid rocket motor was designed, built, and implemented to investigate the comparative combustion behavior of a variety of solid fuel compositions. The goal of this experimental effort is to obtain a relative grading of different solid fuel formulations in terms of regression rate, ignition delay, and radiation emission. Air and oxygen/nitrogen mixtures (up to 50% of oxygen), injected at the head-end of the micromotor, were used as oxidizer. In this phase of investigation, the average chamber pressure was changed in the range of 3.5 to 13 bar, and the volumetric flow rate, 20 to 60 lpm. Quasi-steady regression rates were measured by a proprietary video technique. Ignition delay testing was carried out by exposing solid fuel samples to a controlled laser radiant flux in the range 100 to 300 W/cm2. Spontaneous radiant energy emission was assessed by means of a microcalorimeter at 7 and 14 bar pressure and 20 and 60 lpm oxidizer flow rate. To validate the effectiveness of the experimental approach, pure HTPB-based fuel was considered in this paper. Some representative data points for aluminized HTPB and paraffin-based fuels are also reported.