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国际能源材料和化学驱动期刊
ESCI SJR: 0.149 SNIP: 0.16 CiteScore™: 0.29

ISSN 打印: 2150-766X
ISSN 在线: 2150-7678

国际能源材料和化学驱动期刊

DOI: 10.1615/IntJEnergeticMaterialsChemProp.2013005683
pages 323-351

GLYCIDYL AZIDE POLYMER−COMBUSTION MECHANISM AND ITS APPLICATION TO HYBRID ROCKET MOTORS

Keiichi Hori
Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency (JAXA), 3-1-1 Yoshinodai, Chuo-Ku, Sagamihara, Kanagawa 252-5210, Japan
Makihito Nishioka
University of Tsukuba, 1-1-1, Tennodai, Tsukuba, Ibaraki, 305-8577, Japan

ABSTRACT

A one-dimensional three-phase mode combustion model of GAP [glycidyl azide polymer, poly (3-nitratoethyl-3-methyloxetane)] was developed. Combustion residues; soot (black color), high-viscosity residue, and yellow powder which was only observed at high pressures were analyzed by means of scanning electron microscopy and Fourier transform infrared, and the mass balance was also measured. Modifications of the combustion model were made taking these residue analysis results into account as the "blow off mechanism," and the simulated temperature profiles and linear burning rates coincide well with the experimental data adjusting kinetic parameters. Hybrid rockets using GAP as a solid fuel have been studied. The linear burning rate spectrum of GAP was widened with the dilution by polyethylene glycol (PEG), and basically, self-combustible mixtures are used for the gas hybrid rocket motor, and non-self-combustible mixtures for the traditional hybrid motor. Thrust control, quench, and re-ignition were successfully performed using a gas hybrid system, and simultaneous measurements of the surface regression rate and temperature of the traditional hybrid motor have been conducted using an ultrasonic technique with a special combustion chamber. GAP, mixtures of GAP and PEG, PEG and hydroxyl-terminated polybutadiene fuels have been tested and experimental results are summarized and discussed in this paper.


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