Improvement of Progressive Damage Model to Predicting Crashworthy Composite Corrugated Plate
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Improvement of Progressive Damage Model to Predicting Crashworthy Composite Corrugated Plate Yiru Ren 1,2 & Hongyong Jiang 1,2 & Wenyuan Ji 1,2 & Hanyu Zhang 1,2 & Jinwu Xiang 3 & Fuh-Gwo Yuan 1,2,4
Received: 11 April 2017 / Accepted: 28 April 2017 # Springer Science+Business Media Dordrecht 2017
Abstract To predict the crashworthy composite corrugated plate, different single and stacked shell models are evaluated and compared, and a stacked shell progressive damage model combined with continuum damage mechanics is proposed and investigated. To simulate and predict the failure behavior, both of the intra- and inter- laminar failure behavior are considered. The tiebreak contact method, 1D spot weld element and cohesive element are adopted in stacked shell model, and a surface-based cohesive behavior is used to capture delamination in the proposed model. The impact load and failure behavior of purposed and conventional progressive damage models are demonstrated. Results show that the single shell could simulate the impact load curve without the delamination simulation ability. The general stacked shell model could simulate the interlaminar failure behavior. The improved stacked shell model with continuum damage mechanics and cohesive element not only agree well with the impact load, but also capture the fiber, matrix debonding, and interlaminar failure of composite structure. Keywords Crashworthiness . Composite corrugated plate . Damage . Failure behavior . Delamination
* Yiru Ren [email protected]
1
State Key Laboratory of Advanced Design and Manufacturing for Vehicle Body, Hunan University, Changsha, Hunan 410082, China
2
College of Mechanical and Vehicle Engineering, Hunan University, No.1 Lushan South Rd, Yuelu Dist, Changsha 410082, China
3
School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China
4
Department of Mechanical and Aerospace Engineering, North Carolina State University, Raleigh, NC 27695, USA
Appl Compos Mater
1 Introduction In order to guarantee the safety of occupant during the emergency landing, the crashworthiness analysis and design of aircraft has been conducted for decades [1–3]. With the development of advanced composite material, it has been given much more attention for the application of aerospace engineering [4, 5]. Different from the conventional metal aircraft, the impact dynamic performance and crashworthiness prediction meet great challenging for the complicated failure behavior [6–11]. To reveal the failure mechanism of composite structures, all kinds of composite energy absorber has been investigated. To enhance the crashworthiness of aircraft, many failure mechanism and models for composite structures are proposed and investigated. Yang investigates the effect of fibre cross-section shape on the mechanical properties of unidirectional fibre reinforced composites, and the optimal cross-section shape of the reinforcing fibre is suggested [12]. The microscopic failure mechanisms of cross-ply laminate is studied based on microscopic model,
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