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Purpose <p>Owing to the limitations of rocket carrying capacity and envelope, it is necessary to develop a space integral tension structure with a high absorption ratio and a new structure with adjustable functions to meet the functional requirements of a deployable space structure. The dynamic analysis of the space integral tension structure is challenging in orbit design, attitude adjustment and vibration control of the practical spatial structure, which inspired us to investigate the nonlinear dynamics in the present work.</p> Method <p>First, a simplified coupling nonlinear dynamic model for a space integral tension structure is proposed, in which the nonsmooth stiffness coefficient of the torsional spring is assumed to describe the fold/unfolded state. Based on the Hamiltonian leastaction principle, coupling dynamic equations were deduced for the space deployable model. Then, aiming at the non-smooth dynamics involved in space deployable rigid-flexible coupling damping structures, an innovative complex structure-preserving analysis method is proposed to solve nonlinear coupling dynamic equations, including ordinary differential equations (ODEs) and partial differential equation (PDE). The method is constructed as a bidirectional transmission algorithm between a symplectic Runge-Kutta scheme for ODEs and a generalized multi-symplectic scheme for PDE. The development of a structured analysis method is proposed to address non-smooth dynamic issues in rigid-flexible deployable structures, simulating their deployment/locking/folding dynamics.</p> Results and Conclusions <p>The numerical results show that, owing to the presence of damping, the system energy exhibits a decreasing trend during the folding and unfolding processes, accompanied by a continuous periodic conversion between the kinetic energy and strain energy of the system. Additionally, the system exhibited a fluttering phenomenon. The complex structure-preserving iteration method proposed in this paper provides a new way to investigate the nonlinear coupling dynamics of deployable space structures, which serves as a reference for optimizing the design and control strategies of rigid-flexible deployable structures.</p>

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Unfolding Dynamic Behaviors of an Element for Space Integral Tension Structure

  • 期刊论文

  • 发表日期：

    2025年4月10日

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  • Mengbo Xu,
  • Kaiyu Du,
  • Xiaochuan Qian,
  • Zhengqi Han,
  • Zichen Deng

摘要

Purpose

Owing to the limitations of rocket carrying capacity and envelope, it is necessary to develop a space integral tension structure with a high absorption ratio and a new structure with adjustable functions to meet the functional requirements of a deployable space structure. The dynamic analysis of the space integral tension structure is challenging in orbit design, attitude adjustment and vibration control of the practical spatial structure, which inspired us to investigate the nonlinear dynamics in the present work.

Method

First, a simplified coupling nonlinear dynamic model for a space integral tension structure is proposed, in which the nonsmooth stiffness coefficient of the torsional spring is assumed to describe the fold/unfolded state. Based on the Hamiltonian leastaction principle, coupling dynamic equations were deduced for the space deployable model. Then, aiming at the non-smooth dynamics involved in space deployable rigid-flexible coupling damping structures, an innovative complex structure-preserving analysis method is proposed to solve nonlinear coupling dynamic equations, including ordinary differential equations (ODEs) and partial differential equation (PDE). The method is constructed as a bidirectional transmission algorithm between a symplectic Runge-Kutta scheme for ODEs and a generalized multi-symplectic scheme for PDE. The development of a structured analysis method is proposed to address non-smooth dynamic issues in rigid-flexible deployable structures, simulating their deployment/locking/folding dynamics.

Results and Conclusions

The numerical results show that, owing to the presence of damping, the system energy exhibits a decreasing trend during the folding and unfolding processes, accompanied by a continuous periodic conversion between the kinetic energy and strain energy of the system. Additionally, the system exhibited a fluttering phenomenon. The complex structure-preserving iteration method proposed in this paper provides a new way to investigate the nonlinear coupling dynamics of deployable space structures, which serves as a reference for optimizing the design and control strategies of rigid-flexible deployable structures.