Abstract
The calibration mode of a gimballess inertial attitude control system (GIACS) based on electrostatic gyros (ESGs) is considered upon activation of the system on board an orbiting space vehicle, with implementation of the algorithm for solving problems of angular position correction and refined drift model coefficient (DMC) calibration of electrostatic gyros, based on data from a space vehicle astrosighting device (ASD). The ESG-based GIACS was tested on a ground test bench. The results from solving the problem by processing the test data are presented.
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