Attitude Determination and Control of Nano-Satellites

Warner, John G.

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https://hdl.handle.net/2142/14683 Copy

Description

Title

Attitude Determination and Control of Nano-Satellites

Author(s)

Warner, John G.

Issue Date

2010-01-06T16:21:14Z

Director of Research (if dissertation) or Advisor (if thesis)

Coverstone, Victoria L.

Doctoral Committee Chair(s)

Coverstone, Victoria L.

Department of Study

Aerospace Engineering

Discipline

Aerospace Engineering

Degree Granting Institution

University of Illinois at Urbana-Champaign

Degree Name

M.S.

Degree Level

Thesis

Keyword(s)

• Attitude
• Determination
• Control
• Kalman Filter
• Extended Kalman Filter
• Magnetometer
• Rate Gyro
• Sun Sensor

Abstract

The University of Illinois's IlliniSat2 satellite bus is unique in that it is among only a few nano-satellites that implements three-axis, onboard attitude determination and control. Though this is an ambitious goal, it will allow for a wide range of scientific missions to be accomplished on this bus. To complete the system, an accurate attitude determination system needs to be developed. Several methods for determining the attitude state as well as mitigating system noise are explored. In particular, an extended Kalman lter is developed to obtain accurate angular rate information from noisy rate measurements. These rate measurements may be provided by either rate gyros or by successive vector measurements. A linear Kalman lter is developed to obtain an accurate attitude estimate. The attitude may be measured with two vector measurements via the TRIAD algorithm, while sensor noise may be rejected via the lter. Using these techniques the requirements for an e ective attitude determination and control system are met.

Graduation Semester

2009-12

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http://hdl.handle.net/2142/14683

Copyright and License Information

Copyright 2009 John G. Warner

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