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

ISSN Imprimir: 2150-766X
ISSN On-line: 2150-7678

International Journal of Energetic Materials and Chemical Propulsion

DOI: 10.1615/IntJEnergeticMaterialsChemProp.v2.i1-6.250
pages 412-426

BURNING-RATE CHARACTERISTICS OF BORON/[BAMO/NMMO] FUEL-RICH SOLID PROPELLANT UNDER BROAD RANGES OF PRESSURE AND TEMPERATURE

A. S. Yang
Department of Mechanical Engineering, The Pennsylvania State University, University Park, PA 16802, U.S.A.
I. T. Huang
Department of Mechanical Engineering, The Pennsylvania State University, University Park, PA 16802, U.S.A.
W. H. Hsieh
Department of Mechanical Engineering, The Pennsylvania State University, University Park, PA 16802, U.S.A.

RESUMO

Burning-rate characteristics of pure and 10% boron-based 3,3-bis (azido- methyl) oxetane (BAMO), and 3-nitratomethyl 3-methyl oxetane (NMMO) copolymer fuel-rich solid propellants in air atmosphere have been studied using a pressure and temperature controlled test chamber with optical windows. The temperature and pressure ranges of test firings were −10 to 60°C and 240.5 to 1030.6 KPa (35 to 150 psia), respectively. Temperature sensitivity of the burning rate, one of the most important design parameters in practical application to solid-fuel ramjets (SFRJ) and to solid-propellant ducted rockets (SDR), was deduced from the experimental data. The thermal wave structure of boron/[BAMO/NMMO] copolymer fuel-rich solid propellants under no cross flow conditions was measured by fine-wire thermocouples. From the temperature-time traces recorded at a fixed chamber pressure, the burning surface temperature was found to increase with the initial temperature. Furthermore, the combustion residues of boron/[BAMO/NMMO] copolymer samples, recovered from the tests with different initial temperatures, were examined employing a scanning electron microscope.


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