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Design And Analysis Of A Reusable N2o-Cooled Aerospike Nozzle For Labscale Hybrid Rocket Motor Testing, Daniel Joseph Grieb
Design And Analysis Of A Reusable N2o-Cooled Aerospike Nozzle For Labscale Hybrid Rocket Motor Testing, Daniel Joseph Grieb
Master's Theses
A reusable oxidizer-cooled annular aerospike nozzle was designed for testing on a labscale PMMA-N20[1] hybrid rocket motor at Cal Poly-SLO.[2] The detailed design was based on the results of previous research involving cold-flow testing of annular aerospike nozzles and hot-flow testing of oxidizer-cooled converging-diverging nozzles. In the design, nitrous oxide is routed to the aerospike through a tube that runs up the middle of the combustion chamber. The solid fuel is arranged in an annular configuration, with a solid cylinder of fuel in the center of the combustion chamber and a hollow cylinder of fuel lining …