Pulse combustion propulsion devices are currently being considered as alternatives to conventional constant-pressure engines. Potential advantages include reduction or elimination of pumps and/or compressors, and improved Isp for a given feed system supply pressure. In this paper a model is presented for a monopropellant-fueled, constant-volume, pulse combustor which includes finite- rate processes. A zero-dimensional model is used for the combustion chamber and a one-dimensional, quasi-steady approximation is used for the nozzle flow. The liquid spray is assumed to have a log-normal distribution of spherical droplets and the reaction rate is based on a strand burner correlation. This model was developed as a tool for designing an experimental rocket. In this paper it is used to explore the time and dimensional scales of the problem and to predict the performance and optimal geometry. The pulsed propulsion device is found to have nearly identical specific impulse as the steady-state engine operating with the same mass flow and throat area, furthermore, the nozzle optimizes at the same area ratio. Pulsed combustor behavior is found to depend on two time scales: the ratio of the heat release time to the chamber blow- down time, and the ratio of the blow-down time to the injector pulsing period. Finally, the model is used to assess potential benefits of pulsed engines for satellite applications. We briefly consider the application of pulse combustion devices in pressure-fed satellite propulsion systems and examine the effect on satellite mission.


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