Optimization of Structural Configurations of Spacecraft for Efficient Attitude Change Utilizing Non-holonomic Features

DOI

Description

<p>Spacecraft with movable parts can change their attitude through utilizing non-holonomic features generated by their motion. This can be used as an alternative attitude control method when their equipped attitude control devices no longer generate control torque. No propellant is required in this method, so it has attracted attention as a control method to extend the life of spacecraft. This paper discusses the optimization of the structural configurations to increase the efficiency of the non-holonomic features when attitude control devices are malfunctioned. The optimization problem is difficult due to several reasons: non-holonomic attitude change can be evaluated from numerical integration along trajectories in joint space, spacecraft might have many movable parts as well as structural design parameters, and so on. In this paper, the optimization problem is solved as iterative optimizations in the subspace consisting of the extracted parameters rather than considering all parameters simultaneously. The numerical results show that structural optimization can make the attitude change much more significant.</p>

Journal

Keywords

Details 詳細情報について

  • CRID
    1390020076787091840
  • DOI
    10.57350/jesa.169
  • ISSN
    27581802
  • Text Lang
    en
  • Data Source
    • JaLC
  • Abstract License Flag
    Allowed

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