Using the Impulse Method to Determine High-Pressure Dynamic Burning Rate of Solid Propellants
نویسندگان
چکیده
A new method for determining the burning rate of a solid propellant, called Impulse Method, is proposed in this paper. It based on proportional relationship between impulse generated and mass burned propellant. The pressure–time thrust–time curves are obtained from tubular propellant grain chamber, whose inner surface serves as initial surface. Consequently, that was off at different pressures can be determined, rates derived according to geometric parameters grain. Method applied test two types propellants twice. results show were consistent same corresponding pressures, demonstrating feasibility reliability Method. GAP-based composite 20 MPa measured using Standard Motor 22.6 mm/s, 22.2 mm/s 22.7 respectively. These findings indicate methods have comparable accuracy. However, has advantage obtaining any pressure through single test. In addition, nozzle erosion only affected not rate. Finally, rationality approach actual specific proven by comparing with those another testing method.
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ژورنال
عنوان ژورنال: Aerospace
سال: 2023
ISSN: ['2226-4310']
DOI: https://doi.org/10.3390/aerospace10090818