Partial Stabilization of an Orbiting Satellite Model with a Flexible Attachment
Optimization and Control
2025-08-06 v2
Abstract
We consider a mathematical model of an orbiting satellite, comprising a rigid carrier body and a flexible boom, operating under the influence of gravity gradient torque. This model is represented by a nonlinear control system, which includes ordinary differential equations governing the carrier body's angular velocity and attitude quaternion, coupled with the Euler-Bernoulli equations that describe the vibration of the flexible component. We propose an explicit feedback design aimed at guaranteeing the partial stability of the closed-loop system in an appropriate Hilbert space.
Keywords
Cite
@article{arxiv.2311.09691,
title = {Partial Stabilization of an Orbiting Satellite Model with a Flexible Attachment},
author = {Julia Kalosha and Yevgeniia Yevgenieva and Alexander Zuyev},
journal= {arXiv preprint arXiv:2311.09691},
year = {2025}
}
Comments
This is a preprint version of the paper submitted to Journal of Mathematical Sciences (Series B)