Preliminary Flow System Design of an Apogee Kick Motor Using N2O/C2H4

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Abstract/Contents

Abstract: This research is the preliminary flow system design of a hybrid rocket apogee kick motor using liquid nitrous oxide as oxidizer and solid high-density polyethylene as fuel. Empirical formulations of fuel regression rate and nozzle thermochemical erosion are formed based on static firing test data and included in the design process. Results show that structural and propellant mass is minimized in the cases with no nozzle erosion and a regression rate exponent of 0.5

Subject	Hybrid Rockets, Regression Rates, Propulsion
Genre	Text
Genre	Conference session

DOI	https://doi.org/10.25740/tp376dy5985
Location	https://purl.stanford.edu/tp376dy5985

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License: This work is licensed under a Creative Commons Attribution Non Commercial No Derivatives 4.0 International license (CC BY-NC-ND).

Preferred citation: Kamps, L., Biswas, P., Sakurai, K., Uchiyama, E., and Nagata, H., Preliminary Flow System Design of an Apogee Kick Motor Using N2O/C2H4. 15th International Conference on Flow Dynamics, Sendai, Miyagi (2018)

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