Abstract
This paper analyses the impact of moment of inertia on a spinning spacecraft. Spacecraft moment of inertia distribution is represented in the form of product of inertia terms in system inertia matrix. The cross product of inertia (CPI) for the body axes in the transverse plane is used to control conic motion. The attitude controller controls the spin rate in the spin axis and the angular rate in the transverse axes as well besides orienting spin axis. Dynamic equations are derived with cross product of inertia and are tested with different attitude control modes to test its effect. The analysis is done with and without cross product of inertia with a range of initial conditions to determine the maximum time taken by the individual module and finally concluded with simulation results. Finally attitude information is displayed in Attitude Control System (ACS) control panel.
Published Version
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