Session
Technical Session VII: 12th Annual Frank J. Redd Student Competition
Abstract
The development of a liquefied-gas micro-satellite propulsion system using butane as propellant is presented. Such thrusters would be used to provide secondary propulsion to a micro-satellite in orbit. A theoretical model consisting of four control volumes was developed. For each control volume the principles of continuity and energy were applied to obtain the governing equations. Classical, ideal gas dynamic theory was used to solve for flow through the nozzle. Using this model computer simulations were run in order to observe theoretical thruster performance. Theoretical results indicated steady thrusts of 43 mN for a starting pressure of 300 kPa. Experimental laboratory work was also done. This involved the design, manufacture and testing of a prototype system. Peak thrusts of approximately 50 mN were measured for testing in atmospheric conditions with a starting pressure of between 270 and 290 kPa. An equation to correlate the experimental data was developed. This correlated most of the experimental data to within ± 25 %.
Presentation Slides
Development of a Liquefied-gas Micro-satellite Propulsion System
The development of a liquefied-gas micro-satellite propulsion system using butane as propellant is presented. Such thrusters would be used to provide secondary propulsion to a micro-satellite in orbit. A theoretical model consisting of four control volumes was developed. For each control volume the principles of continuity and energy were applied to obtain the governing equations. Classical, ideal gas dynamic theory was used to solve for flow through the nozzle. Using this model computer simulations were run in order to observe theoretical thruster performance. Theoretical results indicated steady thrusts of 43 mN for a starting pressure of 300 kPa. Experimental laboratory work was also done. This involved the design, manufacture and testing of a prototype system. Peak thrusts of approximately 50 mN were measured for testing in atmospheric conditions with a starting pressure of between 270 and 290 kPa. An equation to correlate the experimental data was developed. This correlated most of the experimental data to within ± 25 %.
