Session: 01-06-03: Impact, Fatigue, Damage and Fracture of Composite Structures 3
Paper Number: 162925
162925 - Modeling Compression After Impact of Hybrid Carbon Fiber Reinforced Laminate Using Enhanced Schapery Theory
Unidirectional (UD) laminae offer directional load-bearing capacity and high tailor-ability, while woven laminae provide in-plane damage tolerance, which is lacking in UD laminae. By combining both unidirectional and woven laminae layers, the resulting hybrid laminate exhibits significant resistance to delamination, impact damage, matrix cracking, and other forms of degradation. These exceptional properties make hybrid laminates highly suitable for aerospace structural applications. However, these structural components are prone to low-energy impacts, such as hail strikes, tool drops, and runway debris, which can lead to barely visible impact damage (BVID) and compromise compressive performance. Under compressive loading after impact, failure events such as the onset of buckling and delamination-induced instability can provide important insights into the material's performance. Accurately modeling and understanding the compression-after-impact (CAI) behavior is therefore essential for designing and developing reliable, damage-tolerant aerospace structures. However, due to its complexity, modeling CAI with high fidelity is challenging and computationally demanding. In this study, a CAI modeling framework is presented in which impact damage details are captured through a pre-CAI low-velocity impact (LVI) model. The damage details and nodal deformations from the LVI results are then transferred to the CAI model. Both the LVI and CAI models are validated against experimental results from LVI and CAI tests conducted on [45W/0W/0T/0W/45W]s hybrid laminates, where the woven layers are made of M21-285T2 and the UD tape layers are made of M21-UD194 materials. The LVI and CAI experiments were carried out following ASTM D7136 and ASTM D7137 standards, respectively. During LVI, the laminates were impacted using 30 J and 60 J impact energies, and CAI tests were performed at a 0.0127 mm/s loading rate. The woven layers in the hybrid laminate were homogenized and modeled as equivalent UD layers, with cohesive interactions between the woven and UD layers defined based on characterization experiments. The computational responses for both the LVI and CAI models were analyzed using Enhanced Schapery Theory, implemented in Abaqus as a VUMAT. Discrepancies between the experimental and computational results are presented and analyzed.
Presenting Author: Minhazur Rahman Arizona State University
Presenting Author Biography: Minhazur Rahman joined ASU in 2024 as a Postdoctoral Research Scholar in the School for Engineering of Matter, Transport and Energy (SEMTE). His research focuses on modeling and predicting damages in fiber reinforced composites, adhesive bonded composite laminates, surface and material characterizations of polymer composites, NDE of bonded composite laminates, NDE data driven failure prediction, composite manufacturing process simulation, etc.
He has a PhD in Mechanical Engineering from University of Texas at Arlington (UTA) working at Material State Awareness and Sustainability (MSAS) lab in UT Arlington Research Institute (UTARI). He received a Master of Science degree in Aerospace Engineering, jointly awarded by Nanyang Technological University (NTU) and Technical University of Munich (TUM). Where his research focused on improving upon carbon fiber preform techniques and modeling material behavior of carbon fiber preforms under compression, for resin transfer molding. Prior to that, he received his Bachelor of Science degree in Mechanical Engineering from Chittagong University of Engineering and Technology (CUET).
Modeling Compression After Impact of Hybrid Carbon Fiber Reinforced Laminate Using Enhanced Schapery Theory
Paper Type
Technical Presentation Only