Partial Stabilization of an Orbiting Satellite Model with a Flexible Attachment
arXiv:2311.09691 · doi:10.1007/s10958-025-07875-1
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.
This is a preprint version of the paper submitted to Journal of Mathematical Sciences (Series B)