Date of Award
Program or Major
Master of Science
Se Young Yoon
This continued research uses a hybrid dynamic algorithm to mathematically model the attitude dynamics of a ﬂexible spacecraft. While a full ﬁnite element model would be the most accurate model, it also would be a huge computational burden on MMS. This method is meant to be an accurate approximation while still being computationally reasonable for on-board, real-time calculations. The algorithm uses Euler’s Moment Equations to propagate the dynamics of the spacecraft hub while ﬁnite element analysis is used to calculate the ﬂexible boom displacements and update the systems mass moment of inertia tensor. This algorithm is iterative and the FEM runs a user-deﬁned number of times within each iteration. Experimental results show that the algorithm is reasonably accurate and can provide a viable approximation for ﬂexible, spin-stabilized spacecraft. Lastly, comparison of controller performance shows Sliding Mode Control to be the most expensive yet most robust control method for this application.
Hashem, Chris, "Modified Hybrid Modeling Technique for Flexible Spin-Stabilized Spacecraft Applied to NASA's Magnetospheric MultiScale (MMS) Mission TableSat Generation IC (TableSat IC)" (2016). Master's Theses and Capstones. 889.