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<p>High-energy wide-area blunt impact (HEWABI) can cause severe internal damage to the composite aircraft structures, which is almost invisible from the fuselage exterior, posing a significant threat to the safety of aircraft operations. The bending and compression tests on composite shear tie specimens were carried out and the corresponding finite element analysis (FEA) models were established; their effectiveness was verified. A rubber impact model for composite fuselage barrel was developed to investigate the structural response, damage, and failure sequence at various impact locations. The results indicated that damage occurred sequentially at shear ties, frames, and stringers at various impact locations, whereas the skin remained almost intact. Besides, the fuselage exhibited higher structural stiffness and greater impact resistance when the impact was located between stringers, while the shear ties failed completely under high-energy impacts. Conversely, the fuselage exhibited lower structural stiffness and reduced impact resistance when the impact was located at the stringer, while widespread damages occurred at high-energy impact.</p>

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Study on the Damage of Composite Fuselage Barrel Under Wide-Area Blunt Impact

  • 期刊论文

  • 发表日期：

    2025年11月8日

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  • Jun Zou,
  • Yulong Jia,
  • Jizhen Wang,
  • Yazhou Guo,
  • Yiqun Wang,
  • Zhenyu Feng

摘要

High-energy wide-area blunt impact (HEWABI) can cause severe internal damage to the composite aircraft structures, which is almost invisible from the fuselage exterior, posing a significant threat to the safety of aircraft operations. The bending and compression tests on composite shear tie specimens were carried out and the corresponding finite element analysis (FEA) models were established; their effectiveness was verified. A rubber impact model for composite fuselage barrel was developed to investigate the structural response, damage, and failure sequence at various impact locations. The results indicated that damage occurred sequentially at shear ties, frames, and stringers at various impact locations, whereas the skin remained almost intact. Besides, the fuselage exhibited higher structural stiffness and greater impact resistance when the impact was located between stringers, while the shear ties failed completely under high-energy impacts. Conversely, the fuselage exhibited lower structural stiffness and reduced impact resistance when the impact was located at the stringer, while widespread damages occurred at high-energy impact.