Scholarlink

This paper considers the actuator installation optimization problem of the flexible appendage to control the vibration when rigid-flexible spacecraft is in large-range planar motion. Firstly, a novel dynamic model is obtained using Hamilton's principle containing more nonlinear terms. The vibration is decomposed with the Rayleigh–Ritz method. Based on the new model and Euler–Bernoulli beam theory, a new cost function is proposed to describe the energy cost of the vibration controller. In addition, Genetic Algorithm is used to optimize the installation positions. Eventually, the optimal installation of actuators is calculated with the optimization algorithm, and numerical simulations are presented to compare the control effect in different installation positions.

错误：搜索内容不能为空，请输入英文关键词
错误：关键词超出字数限制，请精简
高级检索

Actuator Layout Optimization for Active Vibration Control of Rigid-Flexible Spacecraft Using Genetic Algorithm

  • 会议论文

  • 发表日期：

    2026年

查看全文
  • Zeqiang Han,
  • Hongwei Xia,
  • Xudong Li,
  • Haoran Sun,
  • Zening Li,
  • Guangcheng Ma

摘要

This paper considers the actuator installation optimization problem of the flexible appendage to control the vibration when rigid-flexible spacecraft is in large-range planar motion. Firstly, a novel dynamic model is obtained using Hamilton's principle containing more nonlinear terms. The vibration is decomposed with the Rayleigh–Ritz method. Based on the new model and Euler–Bernoulli beam theory, a new cost function is proposed to describe the energy cost of the vibration controller. In addition, Genetic Algorithm is used to optimize the installation positions. Eventually, the optimal installation of actuators is calculated with the optimization algorithm, and numerical simulations are presented to compare the control effect in different installation positions.