| Summary: | 碩士 === 國立成功大學 === 電機工程研究所 === 83 === The purpose of this research is to develop a navigation
simulation system for low Earth-orbiting satellites which are
the main point of indigenous satellite development. Such a
system provides a tool for the attitude determination and
navigation sensors analysis in the computer simulation
environment. This satellite navigation system is established by
the following steps: (1) A simulation of the dynamics of the
low Earth-orbiting satellite, including the satellite orbital
motion and attitude dynamics subject to the environmental
perturbations, is build. (2) Mathematical models of the
navigation sensors that provides performance and cost tradeoffs
are selected and setup. (3) A state estimator for attitude
determination is designed. (4) Attitude determination
algorithms based upon the navigation sensors outputs and the
estimator are realized. Finally, an analysis for the attitude
estimation of a spin-stabilized low Earth-orbiting satellite
using the GPS observables is conducted.
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