2026-09-22T23:26:56Z https://www.ideals.illinois.edu/oai-pmh

oai:www.ideals.illinois.edu:2142/14683 2023-07-10 col_2142_5131 col_2142_14800 com_2142_5130 com_2142_14799 com_2142_234

Coverstone, Victoria L. Coverstone, Victoria L. Warner, John G. 2010-01-06T16:21:14Z 2010-01-06T16:21:14Z 2010-01-06T16:21:14Z 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. Item withdrawn by Mark Zulauf (zulauf@illinois.edu) on 2009-12-10T13:50:00Z Item was in collections: University of Illinois Theses & Dissertations (ID: 1) No. of bitstreams: 10 warner_john.pdf: 1485197 bytes, checksum: bf563309dcfe7b792807091d01e511f9 (MD5) thesisbib.bib: 6059 bytes, checksum: 7d650c1039d5020662575541808f758f (MD5) ADACS_architecture.tex: 26503 bytes, checksum: 62917df8cdbdd9db93ab5274cd88374b (MD5) attitude_theory.tex: 42794 bytes, checksum: cc9d3da30eb1bcd003b2b2c168b709a0 (MD5) attitude_theory_background.tex: 19425 bytes, checksum: 4dbe7f1f2654a1b39bfd0846a476cc71 (MD5) conclusions.tex: 3181 bytes, checksum: 3ba9e46fd8ec0829d3615115bf291947 (MD5) cubesat_overview.tex: 3104 bytes, checksum: 4e98e06b7739a42cfcf8a8eb5240d57c (MD5) simulation_results.tex: 16330 bytes, checksum: 24d41ccb38880b48c3c7951ef3fbf82d (MD5) introduction.tex: 2785 bytes, checksum: 7b0fc5fc99cb37eafcdfc6fc3fa1a8f3 (MD5) thesis_08.tex: 4271 bytes, checksum: 34f15c5d76aee9da0ff1bee5d1f1c48e (MD5) Made available in DSpace on 2010-01-06T16:21:14Z (GMT). No. of bitstreams: 11 warner_john.pdf: 1485197 bytes, checksum: bf563309dcfe7b792807091d01e511f9 (MD5) thesis_08.tex: 4271 bytes, checksum: 34f15c5d76aee9da0ff1bee5d1f1c48e (MD5) conclusions.tex: 3181 bytes, checksum: 3ba9e46fd8ec0829d3615115bf291947 (MD5) introduction.tex: 2785 bytes, checksum: 7b0fc5fc99cb37eafcdfc6fc3fa1a8f3 (MD5) simulation_results.tex: 16330 bytes, checksum: 24d41ccb38880b48c3c7951ef3fbf82d (MD5) cubesat_overview.tex: 3104 bytes, checksum: 4e98e06b7739a42cfcf8a8eb5240d57c (MD5) attitude_theory_background.tex: 19425 bytes, checksum: 4dbe7f1f2654a1b39bfd0846a476cc71 (MD5) attitude_theory.tex: 42794 bytes, checksum: cc9d3da30eb1bcd003b2b2c168b709a0 (MD5) ADACS_architecture.tex: 26503 bytes, checksum: 62917df8cdbdd9db93ab5274cd88374b (MD5) thesisbib.bib: 6059 bytes, checksum: 7d650c1039d5020662575541808f758f (MD5) license.txt: 4061 bytes, checksum: 57e88fe7e38a31b74f0dbeba8a11711b (MD5) http://hdl.handle.net/2142/14683 en Copyright 2009 John G. Warner Attitude Determination Control Kalman Filter Extended Kalman Filter Magnetometer Rate Gyro Sun Sensor Attitude Determination and Control of Nano-Satellites 2009-12 Aerospace Engineering 1615 Aerospace Engineering 4048 University of Illinois at Urbana-Champaign Thesis M.S. MS: Aerospace Engr -UIUC 10KS4048MS