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Acta Aeronautica et Astronautica Sinica ›› 2023, Vol. 44 ›› Issue (20): 228498-228498.doi: 10.7527/S1000-6893.2023.28498

• Solid Mechanics and Vehicle Conceptual Design • Previous Articles    

Effect of low-velocity impact damage on compressive properties of composite stiffened panels

Junchao YANG1, Xueming WANG2, Xiangming CHEN1(), Peng ZOU1, Zhe WANG1   

  1. 1.National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an  710065,China
    2.China Special Vehicle Research Institute,Jingmen  448035,China
  • Received:2023-01-12 Revised:2023-02-20 Accepted:2023-03-21 Online:2023-03-23 Published:2023-03-21
  • Contact: Xiangming CHEN E-mail:asrichenxm@avic.com
  • Supported by:
    National Key R&D Program of China(2019YFA0706800);Civil Aircraft Scientific Research Project(MJZ5-3N21)

Abstract:

Compression tests were carried out on intact and low-velocity impact damage composite stiffened panels. The post-buckling behaviors of stiffened panels were measured in real time using Digital Image Correlation (DIC) and electrical measurement methods respectively. The test results show that the impact damage has no significant impact on the buckling load and buckling mode, but has a greater impact on the failure load and failure mode. Compared with the intact stiffened panel, the skin fiber damage of the stiffened panel with impact damage extends along the transverse direction, leading to the early failure of the structure, with a strength reduction of 30%. Subsequently, the impact damage was equivalent simplified by the softening inclusion method, and the progressive damage finite element analysis model of composite stiffened panel was established based on the improved Tsai-Wu criterion and the secondary stress criterion. The post-buckling failure processes of intact and impact damaged stiffened panels were simulated respectively. Compared with the test results, the predicted buckling load error is less than 1%, and the failure load error is less than 6%. The buckling mode, failure process and failure mode are consistent with the test results. Finally, based on the finite element analysis method, the effects of impact damage location on the compression performance of stiffened panels were discussed. The impact damage location has a small impact on the buckling load and buckling mode, but a large impact on the failure load and failure mode, especially when the impact damage is located in the wave valley of the bottom skin of the stiffener cap, the strength reduction is the most significant.

Key words: composite stiffened panels, low-velocity impact damage, digital image correlation, compression, post-buckling

CLC Number: