| As the need for small satellite missions increases, the practice of launching multiple satellites from a single launch vehicle is also likely to increase. Small satellite missions are often flexible enough that there is a range of satisfactory orbit parameters. Since magnetic attitude control algorithms are typically tuned to a particular orbit, the performance of the control system is often adversely affected if the selected orbit is not particularly close to the orbit parameters for which the system was originally designed.; This thesis describes the attitude determination and control system of the TOROID satellite. The control system for this satellite is an expansion of a linear quadratic regulator routine using a magnetic-inclination-dependent gain scheduling technique that allows a single algorithm to be used effectively in a range of orbits. The inclusion of internal momentum bias is not necessary; but it does significantly improve the performance. The algorithms are set up such that the performance may be optimized for use on other satellites without making significant changes to the software. High fidelity Simulink simulations have been created for use in the development, analysis, and implementation of the attitude determination and control system. |
