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Formulation of Torque-Optimal Guidance Trajectories for a CubeSat with Degraded Reaction Wheels
2016
AIAA Guidance, Navigation, and Control Conference
unpublished
This paper presents the theory and design of a torque-optimal guidance algorithm for CubeSat applications. CubeSats and nano-satellites provide mission-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 may be limited by the attitude actuators, and it is therefore beneficial to reduce torque and angular momentum usage during reorientation maneuvers. The algorithm focuses
doi:10.2514/6.2016-0088
fatcat:5bzwp3n2qnbtzeenpsy72bvgz4