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Design And Analysis Of Reusable Nozzles For Cal Poly’S Hybrid Rocket Lab, Cheyne Austin, Jose Vargas
Design And Analysis Of Reusable Nozzles For Cal Poly’S Hybrid Rocket Lab, Cheyne Austin, Jose Vargas
Aerospace Engineering
Two nozzles were designed and constructed for testing in the Cal Poly propulsion laboratory to explore which nozzle was the most capable in producing the most thrust. A 15 degree and 30 degree converging-diverging nozzles were machined and tested. Theory suggest that a bell nozzle would be the most efficient since all of the gasses generated in the combustion chamber are directed and accelerated by the throat leave the nozzle traveling along the thrust axis. All of the momentum of the gasses are directed axially thus resulting in maximum thrust. Thrust should also be produced by the converging-diverging nozzle and …
Smore Revision: Ignition And User Interface, Arash Mehrparvar
Smore Revision: Ignition And User Interface, Arash Mehrparvar
Aerospace Engineering
The Static Methanol Oxygen Rocket Engine (SMORE) has undergone several revisions since its inception. This latest revision aimed to increase startup reliability and user safety in the operation of the rocket. The implementation of maintenance procedures, safeguards in the ignition system, as well as construction of a new control box and redesign of the igniter itself have accomplished these goals while keeping costs down and without modifying the current rocket setup. Startup reliability has increased drastically, so long as all other rocket setup procedures are followed properly. 250 subsequent firings of the rocket have proven an igniter reliability of more …
Global Launch Vehicle Selector, Keisuke Suzuki
Global Launch Vehicle Selector, Keisuke Suzuki
Aerospace Engineering
No abstract provided.