Space Environment Modelling and Torque-Optimal Guidance for CubeSat Applications
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CubeSats and nano-satellites provide flexible low-cost platforms for the academic and scientific communities to conduct cutting-edge research in the harsh environment of space. The mission life of nano-satellites is often limited by the attitude actuators, and it is therefore beneficial to reduce torque and angular momentum usage during reorientation maneuvers. In this capacity, a computationally lightweight torque-optimal guidance algorithm was formulated, solved using pseudospectral methods, and validated in a MATLAB-Simulink environment. A low-computation atmospheric density model, developed in support of this research, was extensively validated via performance assessment of passive CubeSat aerostabilization. Results indicate that this torque-optimal guidance algorithm demonstrates substantial improvements in performance and pointing accuracy over an Eigenaxis controller for similar maneuvers, with low to moderate computational overhead. In doing so, it presents a significant advancement towards the development of intelligent GN&C systems for small satellites.
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Copyright © 2015 the author(s). Theses may be used for non-commercial research, educational, or related academic purposes only. Such uses include personal study, research, scholarship, and teaching. Theses may only be shared by linking to Carleton University Institutional Repository and no part may be used without proper attribution to the author. No part may be used for commercial purposes directly or indirectly via a for-profit platform; no adaptation or derivative works are permitted without consent from the copyright owner.
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- 2015
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