Design and Construction of a Thrust Stand for Low Power Electric Propulsion

This electric propulsion (EP) project is focused on designing, constructing, testing, and optimizing a simple electrothermal propulsion system. The goal, by optimizing design parameters such as propellant mass fl ow rate, power supplied, nozzle shape/length, and tangentially injected propellant, is to optimize thrust and specifi c impulse performance levels. EP devices typically have very low thrust outputs, and ERAU Prescott currently has no equipment capable of making accurate thrust measurements in the low ranges of EP devices. Electric propulsion systems are critical to extending the life of satellites and other spacecraft, and are an increasingly important in research by space industry companies. Primary goals include enhancing student understanding, and forming a basis for future students to allow continued growth of various electric thruster projects on campus. With the capability to take thrust measurements, thrust improvements may be correlated to design changes, and our thrusters may be compared to those in current use, or in those in testing at other universities. A more thorough understanding will be possible of electric thrusters and the variables contributing to a more effective thruster, and eventually comparisons of various types of thruster will also be possible. POSTER PRESENTATION IGNITE AWAR