University of Illinois Urbana-Champaign

Attitude Determination and Control of Nano-Satellites

Warner, John G.

Content Files
warner_john.pdf

Permalink

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

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
Date of Ingest
2010-01-06T16:21:14Z
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
Permalink
http://hdl.handle.net/2142/14683
Copyright and License Information
Copyright 2009 John G. Warner

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