Chapter 13
Study on Bearing Mechanism
of Composite Stiffened Panel
with Delamination Under Shear Load
Xue Bi, Peng Zou, and Xiangming Chen
Abstract As a typical thin wall structure, the composite stiffened panel not only has
the splendid properties of composite material, but also shows the excellent performance of the composite wall structure with low quality and high bearing capacity.
For the structure, the buckling and post-buckling failure of the panel and the effect
of damage on the performance of the stiffened panel will happen. Thus, in this paper,
the effect of damage on post-buckling bearing capacity of composite stiffened panels
under shear load is researched. Three finite element models are built, including no
damage shear model, delamination embedded shear model and shear after impact
model. The shear failure, effect of delamination and impact damage on panel bearing
strength is discussed. Furthermore, the effects of the size of delamination and position
of impact on structure performance are also researched. These researches provided
abundant theoretical supports for the experiment design and hopeful to be applied in
industry manufacturing.
Keywords Shear load · Delamination · Stiffened panel
13.1 Introduction
Due to the excellent specific strength, specific stiffness and fatigue resistance, carbon
fiber reinforced polymer (CFRP), is widely used in the aviation and aerospace industries. The composite stiffened panel, as a typical thin wall structure with low quality
and high bearing capacity, plays a significant role in aircraft design because of its
outstanding performance, such as fuselages, horizontal/vertical tail wings and wing.
For the research on typical failure modes of composite stiffened panel, more attention
should be paid to the buckling and post-buckling performance failure and damage
defect. The bearing capacity of composite stiffened panel under different loads have
been studied by many famous relevant institutions, such as COCOMAT [1] (Improved
X. Bi (B) · P. Zou · X. Chen
Full Scale Aircraft Structural Static/Fatigue Laboratory, AVIC Aircraft Strength Research
Institute of China, Xi’an 710065, China
e-mail: 441811017@qq.com
© The Author(s), under exclusive license to Springer Nature Switzerland AG 2021
J. Xu and K. M. Pandey (eds.), Mechanical Engineering and Materials,
Mechanisms and Machine Science 100,
https://doi.org/10.1007/978-3-030-68303-0_13
155
Study on Bearing Mechanism
of Composite Stiffened Panel
with Delamination Under Shear Load
Xue Bi, Peng Zou, and Xiangming Chen
Abstract As a typical thin wall structure, the composite stiffened panel not only has
the splendid properties of composite material, but also shows the excellent performance of the composite wall structure with low quality and high bearing capacity.
For the structure, the buckling and post-buckling failure of the panel and the effect
of damage on the performance of the stiffened panel will happen. Thus, in this paper,
the effect of damage on post-buckling bearing capacity of composite stiffened panels
under shear load is researched. Three finite element models are built, including no
damage shear model, delamination embedded shear model and shear after impact
model. The shear failure, effect of delamination and impact damage on panel bearing
strength is discussed. Furthermore, the effects of the size of delamination and position
of impact on structure performance are also researched. These researches provided
abundant theoretical supports for the experiment design and hopeful to be applied in
industry manufacturing.
Keywords Shear load · Delamination · Stiffened panel
13.1 Introduction
Due to the excellent specific strength, specific stiffness and fatigue resistance, carbon
fiber reinforced polymer (CFRP), is widely used in the aviation and aerospace industries. The composite stiffened panel, as a typical thin wall structure with low quality
and high bearing capacity, plays a significant role in aircraft design because of its
outstanding performance, such as fuselages, horizontal/vertical tail wings and wing.
For the research on typical failure modes of composite stiffened panel, more attention
should be paid to the buckling and post-buckling performance failure and damage
defect. The bearing capacity of composite stiffened panel under different loads have
been studied by many famous relevant institutions, such as COCOMAT [1] (Improved
X. Bi (B) · P. Zou · X. Chen
Full Scale Aircraft Structural Static/Fatigue Laboratory, AVIC Aircraft Strength Research
Institute of China, Xi’an 710065, China
e-mail: 441811017@qq.com
© The Author(s), under exclusive license to Springer Nature Switzerland AG 2021
J. Xu and K. M. Pandey (eds.), Mechanical Engineering and Materials,
Mechanisms and Machine Science 100,
https://doi.org/10.1007/978-3-030-68303-0_13
155