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Rigid Body Satellite Time-Optimal Attitude Control Using Inversion

Author:
Basu, Kaushik
Published:
[University Park, Pennsylvania] : Pennsylvania State University, 2018.
Physical Description:
1 electronic document
Additional Creators:
Melton, Robert G.
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Open Access.
Summary:
Spacecraft missions with requirements for tighter tolerances and that take advantage of improvingcomputational technology, and having more stringent control requirements, including time optimalsolutions are required.An inverse-dynamics method is used in conjunction with a particle swarm algorithm to findnear-minimum time reorientation maneuvers in the presence of path constraints. The methodemploys a quaternion formulation of the kinematics, using B-splines to represent the quaternions.The inverse particle swarm optimization provides a method to determine an initial starting point fora more accurate algorithm that uses a gradient-based method. The inverse method provides certainadvantages in this problem over other methods such as enforcement of boundary conditions and theincrease of computational efficiency by avoiding the use of numerical integrators.Once the technique is established, parallelization of the algorithm demonstrates the potential forflight hardware to be implemented that will aid in performing near real-time solutions. In total thesuperior terminating kinematic results and speed up of computing time from hours to just severalseconds will allow the implementation using space hardened Graphic Processor Units and FieldProgrammable Gate Arrays to perform autonomous guidance and navigation.
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Dissertation Note:
Ph.D. Pennsylvania State University 2018.
Reproduction Note:
Microfilm (positive). 1 reel ; 35 mm. (University Microfilms 28406810)
Technical Details:
The full text of the dissertation is available as an Adobe Acrobat .pdf file ; Adobe Acrobat Reader required to view the file.
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