Application of a Modified PI Control Algorithm for Separation Parameter Optimization in Micro/Nano-Satellites with Off-Center Mass Distributions

This study addresses the attitude control challenge inherent in the separation of satellites with eccentric configurations. We propose an automated optimization algorithm for adjusting separation parameters, utilizing cosimulation between ADAMS and MATLAB/Simulink. Simulation results demonstrate that the method effectively constrains the separation angular velocity and exhibits rapid convergence during optimization. In-orbit separation validation confirmed that the X/Y-axis angular velocities of all three satellites remained within the simulated prediction range. The Z -axis angular velocity slightly exceeded the prediction by approximately 1 %, yet all separation data complied with the <tex xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink">$\pm 7^{\circ} / \mathrm{s}$</tex> requirement specified in the launch technical specifications. These findings confirm the significant effectiveness of the proposed method for parameter adjustment in eccentric micro/nano-satellite separation, demonstrating substantially enhanced efficiency over traditional approaches. The methodology demonstrates considerable potential for engineering applications in multi-satellite separation parameter optimization.