Abstract
Fuel-rich solid propellants have been studied to use them in hybrid rocket motors by many researchers. However, there remains much to be understood about these propellants. In this study, the combustion characteristics of fuel-rich solid propellants are investigated theoretically and experimentally. A quasi-steady and one dimensional flame model has been developed for solid-propellant combustion. The steady burning rate of fuel-rich solid propellants is analyzed using this simple flame model. In addition, the ignition delay experiments of fuel-rich solid propellants were performed at atmospheric pressure by a high-power infrared lamp. Also, the linear burning rate of these propellants was measured at subatmospheric pressure. As a result, effects of ammonium perchlorate content on the steady-state combustion and the ignition are revealed experimentally.
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