Attitude Determination and Control of Nano-Satellites

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

Warner, John G. ; Coverstone, Victoria L. ; Coverstone ; Victoria L.

关键词: Attitude;    Determination;    Control;    Kalman Filter;    Extended Kalman Filter;    Magnetometer;    Rate Gyro;    Sun Sensor;   

Others  :  https://www.ideals.illinois.edu/bitstream/handle/2142/14683/warner_john.pdf?sequence=1&isAllowed=y

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来源: The Illinois Digital Environment for Access to Learning and Scholarship

【 摘 要 】

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