Evaluation of the Bolted Metallic Repair on Damaged Stiffened Composite Panel
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TECHNICAL ARTICLE—PEER-REVIEWED
Evaluation of the Bolted Metallic Repair on Damaged Stiffened Composite Panel Xiangming Chen . Jiong Zhang . Yanan Chai . Xiufeng Tang
Submitted: 25 June 2020 / in revised form: 26 September 2020 / Accepted: 1 November 2020 Ó ASM International 2020
Abstract The compression behavior of a damaged Isection stiffened panel repaired by the bolted metal patch method is studied experimentally and numerically by the finite element method in this paper. In the finite element model, the bolt was simulated by a combination of beam elements coupled to rigid contact surfaces, the coupling failure criterion and a new delamination criterion were used to analyze the failure of composite laminates and bonding interfaces, respectively. The repairing effects of the mechanical fastening method are compared with the panels with damage. The results show that the load-carrying capacity of the repaired panel increases significantly compared with the panel with damage. The experimental results validate the proposed finite element model. Finally, an improved repair configuration is proposed based on the finite element simulation. This shows that the presented repair is useful and effective to repair the damaged composite structures. X. Chen (&) School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China e-mail: [email protected] J. Zhang (&) School of Civil Engineering and Architecture, Wuyi University, Jiangmen 529020, China e-mail: [email protected] Y. Chai Aircraft Strength Research Institute of China, Xi’an 710065, China e-mail: [email protected] X. Tang School of Applied Physics and Materials, Wuyi University, Jiangmen 529020, China e-mail: [email protected]
Keywords Stiffened composite panel Repair Mechanical fastening method
Introduction Carbon fiber-reinforced composite materials are playing an increasingly important part in aircraft structures due to their well design, high strength and stiffness [1–3]. Thinwalled composite stiffened panels have been widely used in aircraft structures for the excellent load-carrying capacity [4–6]. However, the composite structures such as wings or fuselages are susceptible to damage from incidents such as collision by fragments from a failed engine. In this case, the damage can cause severe reductions in strength, stiffness, load-carrying capability, and flight maneuvers are limited. It is important content to consider the safety requirements of wing and fuselage structure in the relevant design specifications and airworthiness regulations to ensure the safe return of the aircraft under the threat of damage. When such damage occurs, it must be ensured that the aircraft structure can bear the get home loads, and reliable permanent repair should be carried out in time. Many researchers have studied the mechanical properties of stiffened composite panel with damage and tried to find out the damage progression and residual strength of the damaged panels in recent years [7–14]. On the other hand, repair methods for damage must be dev
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