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Coolant passage segmentation influence on regenerative-cooling effectiveness for small spacecraft thrusters
(2020-05)
The purpose of this thesis is to examine the effect of varying the number of cooling passages in a regeneratively-cooled rocket combustion chamber and nozzle analog for a small spacecraft thruster producing 22N (5lbf) ...
Design, analysis, and integration of a turboelectric propulsion and power system for unmanned aircraft
(2020-05)
Electrically powered small unmanned aerial systems face limited range and endurance due to the inherently low energy density of current level of technology batteries. Hybrid gas-electric systems are under development and ...