Satellite Attitude Determination with Attitude Sensors and Gyros using Steady-state Kalman Filter
نویسندگان
چکیده
Attitude determination, along with attitude control, is critical to functioning of every space mission. Here, we investigate the application of a steady-state Kalman Filter for attitude determination using attitude sensors (sun sensor and horizon sensors) and rate integrating gyros. The three-axis steady-state Kalman Filter formulation, adopted from literature, offers obvious computational advantages for on-board implementation on spacecrafts. Thus, closed loop simulation, involving the attitude determination formulation, true attitude dynamics and attitude control, for a satellite are developed in MATLABSimulink. Based on the simulation, performance of the filter for an Earth-pointing Low Earth Orbit satellite is presented, in order to examine the applicability of the steady-state Kalman Filter for satellite attitude determination.
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