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This paper presents a sequential thermal-mechanical coupling equivalent evaluation methodology for multiscale aircraft rudder wings fabricated using additive manufacturing (AM). The AM rudder wings incorporate periodic honeycomb sandwich or lattice structures for enhanced mass centroid adjustment, load distribution, and thermal insulation. Due to the complexity of lattice structures, traditional performance simulations are computationally intensive. The proposed method involves replacing the periodic microstructure with an equivalent homogenized model using the energy-based homogenization to ascertain equivalent mechanical properties and thermal conductivity. This simplifies the multiscale problem into a single-scale calculation, reducing computational complexity while maintaining accuracy. The results clearly showcase the precision of the method, highlighting a 56% discrepancy in deformation distributions between equivalent and hollow rudder wings. This methodology provides a concise and adaptable framework for the comprehensive evaluation of aircraft rudder wings featuring periodic lattice structures.

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Thermal-Mechanical Coupling Evaluation for Aircraft Rudder Wing with Periodic Lattice Structures

  • 会议论文

  • 发表日期：

    2026年

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  • Shaoying Li,
  • Guangzhi Nan,
  • Yingchao Ma,
  • Chi Zhang,
  • Bin Sun,
  • Wen Zhu,
  • Yongli Zhang

摘要

This paper presents a sequential thermal-mechanical coupling equivalent evaluation methodology for multiscale aircraft rudder wings fabricated using additive manufacturing (AM). The AM rudder wings incorporate periodic honeycomb sandwich or lattice structures for enhanced mass centroid adjustment, load distribution, and thermal insulation. Due to the complexity of lattice structures, traditional performance simulations are computationally intensive. The proposed method involves replacing the periodic microstructure with an equivalent homogenized model using the energy-based homogenization to ascertain equivalent mechanical properties and thermal conductivity. This simplifies the multiscale problem into a single-scale calculation, reducing computational complexity while maintaining accuracy. The results clearly showcase the precision of the method, highlighting a 56% discrepancy in deformation distributions between equivalent and hollow rudder wings. This methodology provides a concise and adaptable framework for the comprehensive evaluation of aircraft rudder wings featuring periodic lattice structures.