Design and Construction of a Thrust Stand for Low Power Electric Propulsion
Faculty Mentor Name
Daniel White
Document Type
Presentation
Location
Jim and Linda Lee Planetarium
Start Date
4-10-2019 3:20 PM
End Date
4-10-2019 3:30 PM
Abstract
Electric propulsion (EP) project focused on designing, constructing, testing, and ultimately optimizing a simple electrothermal propulsion system. By optimizing design parameters such as propellant mass flow rate, power supplied, nozzle shape/length, and tangentially injected propellant, we hope to optimize the thrust and specific impulse performance levels of the propulsion system. Due to the nature of EP devices, they have very low thrust outputs, and we currently do not have any equipment on campus that is capable of making accurate thrust measurements in the range required for EP devices.
Electric propulsion systems are critical to extending the lifetimes of satellites and other spacecraft. They are an increasingly important area of research for space industry companies looking to offer the longest lifetimes for commercial satellites. Our expected project outcomes primarily include enhancing student understanding of electrostatic propulsion systems, and to lay the groundwork for the students that come after us; allowing to the continued growth of the various electric thruster projects on campus. With the capability to take thrust measurements, we will be able to correlate thrust improvements to design changes, compare our thrusters to those in current use, or in those in testing in other universities. We will gain a more thorough understanding of electric thrusters, and the variables that contribute to a more effective thruster. With a thrust stand designed for EP devices, we will also be able to compare various types of thruster as the project grows and more thrusters are built.
Design and Construction of a Thrust Stand for Low Power Electric Propulsion
Jim and Linda Lee Planetarium
Electric propulsion (EP) project focused on designing, constructing, testing, and ultimately optimizing a simple electrothermal propulsion system. By optimizing design parameters such as propellant mass flow rate, power supplied, nozzle shape/length, and tangentially injected propellant, we hope to optimize the thrust and specific impulse performance levels of the propulsion system. Due to the nature of EP devices, they have very low thrust outputs, and we currently do not have any equipment on campus that is capable of making accurate thrust measurements in the range required for EP devices.
Electric propulsion systems are critical to extending the lifetimes of satellites and other spacecraft. They are an increasingly important area of research for space industry companies looking to offer the longest lifetimes for commercial satellites. Our expected project outcomes primarily include enhancing student understanding of electrostatic propulsion systems, and to lay the groundwork for the students that come after us; allowing to the continued growth of the various electric thruster projects on campus. With the capability to take thrust measurements, we will be able to correlate thrust improvements to design changes, compare our thrusters to those in current use, or in those in testing in other universities. We will gain a more thorough understanding of electric thrusters, and the variables that contribute to a more effective thruster. With a thrust stand designed for EP devices, we will also be able to compare various types of thruster as the project grows and more thrusters are built.