Aerodynamic stability analysis of a CubeSat in high-speed rarefied flow

Small satellites, such as CubeSats and SmallSats, are seeing increased use in Low Earth Orbit, particularly at altitudes with measurable aerodynamic effects. It is important to design these spacecraft, which often have modest control authority, such that the resultant aerodynamic forces and moments do not cause unstable motion, which may lead to premature loss of mission. Building from free molecular pressure and shear equations for flat plates, an aerodynamic solver is designed to analyze the aerodynamic forces and moments on a 3U CubeSat with center of gravity offset, orbiting at altitudes from 80 to 200 km. The motion of this CubeSat is then simulated for a variety of initial conditions, both with and without active control, to determine its behavior. Inferences are made as to design rules that will lead to more stable small satellites.

Name thesis:degree_name

M.S.

Level thesis:degree_level

Thesis

Discipline thesis:degree_discipline

Aerospace Engineering

Grantor

University of Illinois at Urbana-Champaign

Year dc:date

2018

Author dc:creator

• Williams, James Warren

Contributors dc:contributor

• Putnam, Zachary R.

• Stability CubeSat SmallSat Rarefied High Speed

Statement dc:rights

• Copyright 2018 James Williams

Language dc:language

en

Handle dc:identifier

http://hdl.handle.net/2142/101103

OAI identifier oai:identifier

oai:www.ideals.illinois.edu:2142/101103