Design and theoretical performance prediction of hydrogen peroxide hybrid thruster
A design procedure to realize a hybrid rocket engine that uses hydrogen peroxide as the oxidizer and a solid polymer as the fuel is presented. In the design procedure, the products of decomposition and of combustion at different stations are calculated by linking a standard complex chemical-equilibr...
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| Main Authors: | , , , |
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| Format: | Conference or Workshop Item |
| Published: |
2009
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| Subjects: | |
| Online Access: | http://eprints.utm.my/id/eprint/15036/ |
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| Summary: | A design procedure to realize a hybrid rocket engine that uses hydrogen peroxide as the oxidizer and a solid polymer as the fuel is presented. In the design procedure, the products of decomposition and of combustion at different stations are calculated by linking a standard complex chemical-equilibrium program of NASA. For the designed basic-configuration, applying the mass conservation principle, theoretical performance results are presented with propellant-tank pressure and grain port length as parameters. |
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