A Pulsed Plasma Thruster (PPT) is a type of electric propulsion considered for use on spacecraft flying in formation. The use of a PPT near other spacecraft requires characterization of the light emission when fired. This project’s goal was to measure the emission spectra from an Aerojet Corp. laboratory model PPT. Prior to testing, gas leaks in the used vacuum chamber were located and repaired. A PPT mount and plume baffle were also designed and fabricated to support the PPT and protect the chamber walls from exhaust plume carbon deposition. Moreover, custom cabling for both command and telemetry were assembled, tested and installed in the vacuum chamber. Finally, a LabVIEW program was designed, tested, and incorporated in the test setup to allow computer controlled, automated operation.

• 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

• Khaled, Narimane
• Theriot, Timothy Peter
• Gonzalez, Luis Alexander
• White, Justin Ryan

Publisher

• Worcester Polytechnic Institute

Identifier

• E-project-043014-152717

Advisor

• Blandino, John J.

Year

• 2014

Date created

• 2014-04-30

Resource type

• Major Qualifying Project

Major

• Aerospace Engineering

Rights statement

• In Copyright