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The hat-shaped stringer is commonly used in the fuselage panel of civil aircraft. The co-bonding and co-curing processes are used to manufacture the stringer compression coupons respectively, and the test is carried out to obtain the compression failure load. The engineering method and finite element method are used to calculate the failure load of coupons. The failure load obtained by engineering analysis method is conservative, and the maximum error is 31%. The maximum error of failure load obtained by finite element method is 9.7%. The result shows that both the engineering method and the finite element method can be used as the basis for calibrating the compression load capacity of the stringers in the civil aircraft design process.

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Study on Compression Load Capacity of Composite Hat-Shaped Stringers in Civil Aircraft

  • 会议论文

  • 发表日期：

    2026年

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  • Shiwei Liu,
  • Lin Chen,
  • Mingde Chang

摘要

The hat-shaped stringer is commonly used in the fuselage panel of civil aircraft. The co-bonding and co-curing processes are used to manufacture the stringer compression coupons respectively, and the test is carried out to obtain the compression failure load. The engineering method and finite element method are used to calculate the failure load of coupons. The failure load obtained by engineering analysis method is conservative, and the maximum error is 31%. The maximum error of failure load obtained by finite element method is 9.7%. The result shows that both the engineering method and the finite element method can be used as the basis for calibrating the compression load capacity of the stringers in the civil aircraft design process.