The project addresses the science payload and performs thermal and spacecraft charging analysis of a three-unit CubeSat under design. An infrared spectrometer and a magnetometer are selected for the circular 680-km polar CubeSat mission. Thermal analysis using SolidWorks provides the CubeSat temperature distribution under anticipated ambient and internal heat fluxes. To achieve the design temperatures thermal control is recommended with coatings and internal insulation. Charging analysis is performed using the Spacecraft Plasma Interaction System (SPIS) software under anticipated ambient plasma conditions and shows no adverse impacts. Electromagnetic interference due to the onboard propulsion solenoids is assessed using COMSOL. The analysis guides the design of a 10-cm magnetometer boom.

• 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

• Schaalman, Gregory Paul
• Staley, Simone Loretta
• Oliva, Andrew A

Publisher

• Worcester Polytechnic Institute

Identifier

• E-project-031411-150501

Advisor

• Gatsonis, Nikolaos A.

Year

• 2011

Date created

• 2011-03-14

Resource type

• Major Qualifying Project

Major

• Aerospace Engineering

Rights statement

• In Copyright