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<p>We consider a mathematical model of an orbital satellite formed by a perfectly rigid carrier body and a flexible boom operating under the influence of the orbital moment of the gravity gradient. The model is represented by a nonlinear control system including ordinary differential equations governing the angular velocity of the carrier body and the attitude quaternion coupled with the Euler–Bernoulli equations used to describe the vibration of the flexible component. We propose an explicit feedback design aimed at guaranteeing partial stability of the closed-loop system in a proper Hilbert space.</p>

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PARTIAL STABILIZATION OF AN ORBITAL SATELLITE MODEL WITH FLEXIBLE ATTACHMENT

  • 期刊论文

  • 发表日期：

    2025年7月1日

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  • Julia Kalosha,
  • Yevgeniia Yevgenieva,
  • Alexander Zuyev

摘要

We consider a mathematical model of an orbital satellite formed by a perfectly rigid carrier body and a flexible boom operating under the influence of the orbital moment of the gravity gradient. The model is represented by a nonlinear control system including ordinary differential equations governing the angular velocity of the carrier body and the attitude quaternion coupled with the Euler–Bernoulli equations used to describe the vibration of the flexible component. We propose an explicit feedback design aimed at guaranteeing partial stability of the closed-loop system in a proper Hilbert space.