Precise position determination and control is necessary to
accomplish proposed satellite formation flying missions of ground
movement target indication and synthetic aperture radar. This
thesis combines the estimation and control techniques of past AFIT
theses with various time-varying and time-invariant LQG control
methods. Linear time-invariant control is ideal for on-board
satellite estimation and control applications, freeing-up the
satellite's limited computational capacity. Using a dynamics frame
transformation from the nodal frame to an orbital frame, a higher
fidelity, time-periodic model produced nearly identical results for
either time-varying or time-invariant control for many scenarios.
Scenarios included initial perturbations in the radial, in-track,
and cross-track directions as well as increased magnitude
perturbations; step size increase from 0.2 seconds to 2 seconds;
and increased and reduced measurement noise level scenarios versus
the standard absolute GPS receiver noise level. Results obtained
indicate the ability to control within the error range of the
measurements (centimeter-level and better) using realistic noise
and dynamics perturbations.
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