Analysis of the orbit lowering and attitude control performance of a magnetic coil-augmented gossamer sail

Abstract

This thesis introduces the analysis of a novel device which, capitalizing on recent advances in gossamer solar sail technology, offers the possibility of propellantless satellite deorbiting and attitude control. By taking advantage of aerodynamic drag effects, a lightweight sail can rapidly deorbit a satellite. At the same time, the sail provides an ideal substrate for a large area magnetic torque coil for attitude control. Through the use of orbit propagation software, the performance of an implementation of this "MagSail" on a Low Earth Orbit (LEO) small satellite is simulated. The analysis is set forth in three parts. First the orbit decay profile of the satellite under the effects of atmospheric drag is presented. The results are interpreted for various initial orbits. Next, the actual torque generation of the MagSail is analyzed. Emphasis is placed on how various design parameters change the magnetic moment of the sail. Finally, a six degree of freedom simulation, combining both orbit propagation and PD attitude control demonstrates a possible implementation of the sail's attitude control capabilities. The work presented in this thesis provides an in-depth look at the deorbiting performance of large-area, low-mass LEO satellites. This research provides a theoretical framework for the development of compact, cost-effective propellantless propulsion and space debris mitigation systems.

Notes

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Thesis Completion

2009

Semester

Summer

Advisor

Ham, Chan

Degree

Bachelor of Science (B.S.)

College

College of Engineering and Computer Science

Degree Program

Aerospace Engineering

Subjects

Dissertations, Academic -- Engineering and Computer Science;Engineering and Computer Science -- Dissertations, Academic

Format

Print

Identifier

DP0022365

Language

English

Access Status

Open Access

Length of Campus-only Access

None

Document Type

Honors in the Major Thesis

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