Advanced hybrid rocket motor experiments |
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| Institution: | 3. Prins Maurits Laboratory TNO, Postbus 45, 2280AA Rijswijk ZH, The Netherlands;7. ESTEC, Noordwijk, The Netherlands;1. School of Astronautics, Beihang University, Beijing 100191, China;2. China Academy of Launch Vehicle Technology, Beijing 100076, China;1. School of Astronautics, Beihang University, Beijing, 100191, China;2. China Academy of Launch Vehicle Technology, Beijing, China;3. Science and Technology on Space Physics Laboratory, China Academy of Launch Vehicle Technology, Beijing, China;1. Institute of Heat Engineering, Warsaw University of Technology, Warsaw, 00-665, Poland;2. Łukasiewicz Research Network – Institute of Aviation, Warsaw, 02-256, Poland |
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| Abstract: | Results of experiments performed with an advanced, automated measuring system and dealing with combusion of polymethylmethacrylate and polyethylene with oxygen and different mixtures of oxygen and nitrogen are reported.Factors affecting the regression rate of the fuel are the mass flux, the geometry, the pressure level and the presence of oscillations, the composition of the oxidizer and the burning time. The effect of pressure on the regression rate appears to be stronger at lower pressures. A newly developed technique allows the measurement of the local instantaneous regression rate. The dependence of this regression rate on the various above mentioned parameters varies from location to location in the motor. The characteristic velocity depends on the mixture ratio and on the residence time of the reacting gases. A rearward facing step increases the mean regression rate and changes the profile of the burned fuel grain. Such a step is necessary to obtain combustion with mixtures containing 20% oxygen and 80% nitrogen. |
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