Pulsed Induction Thruster-Capstone Project
Faculty Mentor Name
Daniel White, Richard Mangum
Format Preference
Poster
Abstract
Modern-day space technology and space exploration is limited by numerous factors. One major factor is the cost of space missions. The sources of cost come from many components of a satellite, but the most glaring one is the cost of a capable electric thruster. Expensive components such as cathode, anode, magnetic circuits, and screen grids are all critical components in thrusters used today. Xenon, being the most widely used propellant in electric propulsion, is one of the most expensive and scarce noble gases, which is an issue we are looking to resolve. To solve these issues, we decided to work on a pulsed inductive thruster. We began to approach a solution in which many different propellants can be used, like argon, carbon dioxide, water, or nitrogen. This would lead to an increased lifespan since refueling could take place simply by passing by another planet's atmosphere. We also decided to change existing designs, such as the one from Northrop Grumman. After looking into papers produced by researchers at Northrop Grumman, we've concluded that if we replace the injection system with a more practical design utilizing modern technology, we can produce similar results at a lower cost. This design would consist of 12 injectors placed radially around the extremity of the engine, pointing the gas towards an inductor plate. With rapidly changing current, the inductor plate will create an EMF which will ionize the gas and in turn, create plasma. To develop the design, we took several measurements of the vacuum chamber on campus, which lead our size restrictions. We then modeled it in SolidWorks and simulated fluid flow in a vacuum. This helped us understand how our design would affect the propellant in space since this thruster's main applications is satellite propulsion.
Pulsed Induction Thruster-Capstone Project
Modern-day space technology and space exploration is limited by numerous factors. One major factor is the cost of space missions. The sources of cost come from many components of a satellite, but the most glaring one is the cost of a capable electric thruster. Expensive components such as cathode, anode, magnetic circuits, and screen grids are all critical components in thrusters used today. Xenon, being the most widely used propellant in electric propulsion, is one of the most expensive and scarce noble gases, which is an issue we are looking to resolve. To solve these issues, we decided to work on a pulsed inductive thruster. We began to approach a solution in which many different propellants can be used, like argon, carbon dioxide, water, or nitrogen. This would lead to an increased lifespan since refueling could take place simply by passing by another planet's atmosphere. We also decided to change existing designs, such as the one from Northrop Grumman. After looking into papers produced by researchers at Northrop Grumman, we've concluded that if we replace the injection system with a more practical design utilizing modern technology, we can produce similar results at a lower cost. This design would consist of 12 injectors placed radially around the extremity of the engine, pointing the gas towards an inductor plate. With rapidly changing current, the inductor plate will create an EMF which will ionize the gas and in turn, create plasma. To develop the design, we took several measurements of the vacuum chamber on campus, which lead our size restrictions. We then modeled it in SolidWorks and simulated fluid flow in a vacuum. This helped us understand how our design would affect the propellant in space since this thruster's main applications is satellite propulsion.