This project presents the conceptual design of a micro-Pulsed Plasma Thruster (microPPT) and a propulsion module consisting of eight micro-PPTs for applications on a three-unit Cube Satellite (3U CubeSat). The computer aided mechanical design of the micro-PPT, the propulsion module and its integration in the 1U are presented. Material selection identifies Torlon 4203 for housing and Tungsten-plated copper for electrodes. Finite element stress analysis shows that the micro-PPT will sustain expected launch loads. The electric circuit for the main and initial discharge are designed and simulated for power and voltage levels expected in a 3U Cubesat. Finite element thermal analysis provides estimates of the temperature distribution in the micro-PPT and module for a typical discharge.

• This report represents the work of one or more WPI undergraduate students submitted to the faculty as evidence of completion of a degree requirement. WPI routinely publishes these reports on its website without editorial or peer review.

Creator

• Marchetto, Jordan David
• Scougal, Erik Alexander
• Eslava, Sebastian Ariel

Publisher

• Worcester Polytechnic Institute

Identifier

• E-project-031714-101538

Advisor

• Gatsonis, Nikolaos A.

Year

• 2014

Date created

• 2014-03-17

Resource type

• Major Qualifying Project

Major

• Aerospace Engineering

Rights statement

• In Copyright