Low-velocity impact (LVI) on composites may cause Barely Visible Impact Damage (BVID), which is one of the most common damage types and may result in a decrease in strength of the composite. The objectives of this research were (a) to identify the characteristics of a carbon/epoxy composite plate after low-velocity impact, (b) to create a validated model to simulate the impact process and progressive failure, and (c) to perform sizing and shape optimization of the laminate for improving the damage resistance of the plate. As a part of this thesis, composite plates were fabricated using carbon fiber reinforced polymer (CFRP) prepreg. The LVI testing was performed on the samples with different impactors and different impact energy levels. The X-Ray Micro-tomography technique helped to reveal the internal fiber damage and matrix damage of the impacted plate. Numerical models with nonlinear dynamic responses were developed in ABAQUS, which validated the LVI experiments. Further, the modified model was created in MSC. PATRAN/NASTRAN to optimize the ply thickness, ply orientation, and dimensional properties of the plate to minimize the weight while abiding by the structural response constraints. Moreover, the possibility of the OpenMDAO framework in nonlinear dynamic analysis and size optimization was explored.
","abstract_html":"<p>Low-velocity impact (LVI) on composites may cause Barely Visible Impact Damage (BVID), which is one of the most common damage types and may result in a decrease in strength of the composite. The objectives of this research were (a) to identify the characteristics of a carbon/epoxy composite plate after low-velocity impact, (b) to create a validated model to simulate the impact process and progressive failure, and (c) to perform sizing and shape optimization of the laminate for improving the damage resistance of the plate. As a part of this thesis, composite plates were fabricated using carbon fiber reinforced polymer (CFRP) prepreg. The LVI testing was performed on the samples with different impactors and different impact energy levels. The X-Ray Micro-tomography technique helped to reveal the internal fiber damage and matrix damage of the impacted plate. Numerical models with nonlinear dynamic responses were developed in ABAQUS, which validated the LVI experiments. Further, the modified model was created in MSC. PATRAN/NASTRAN to optimize the ply thickness, ply orientation, and dimensional properties of the plate to minimize the weight while abiding by the structural response constraints. Moreover, the possibility of the OpenMDAO framework in nonlinear dynamic analysis and size optimization was explored.</p>","abstract_has_math":false,"creators":["He, Zhennan"],"institution":null,"degree_name":"Master of Science in Aerospace Engineering","degree_level":"Thesis - Open Access","degree_discipline":"Aerospace Engineering","degree_department":null,"school":null,"contributors":[],"advisors":[],"committee_chairs":[],"committee_members":[],"year":2020,"date_issued":"2020-12-01T08:00:00Z","date_published":"2020-12-01T08:00:00Z","updated_at":"2026-07-27T19:25:29Z","subjects":["impact testing","composites","CFRP","carbon composites","Aerospace Engineering","Structures and Materials"],"languages":[],"rights":[],"rights_urls":[],"identifier_entries":[]},"links":{"outbound_url":"https://commons.erau.edu/edt/555","outbound_label":"Repository record","outbound_source":"dc:identifier"},"metadata_groups":[{"id":"people","label":"People","entries":[{"key":"dc:creator","label":"Author","values":["He, Zhennan"]}]},{"id":"academic_context","label":"Academic Context","entries":[{"key":"thesis:degree_discipline","label":"Discipline","values":["Aerospace Engineering"]},{"key":"thesis:degree_level","label":"Degree Level","values":["Thesis - Open Access"]},{"key":"thesis:degree_name","label":"Degree Name","values":["Master of Science in Aerospace Engineering"]}]},{"id":"subjects_keywords","label":"Subjects and Keywords","entries":[{"key":"dc:subject","label":"Dc Subject","values":["impact testing","composites","CFRP","carbon composites","Aerospace Engineering","Structures and Materials"]}]},{"id":"identifiers","label":"Identifiers","entries":[{"key":"dc:identifier","label":"Identifier","values":["https://commons.erau.edu/edt/555"]}]},{"id":"additional","label":"Additional Metadata","entries":[{"key":"dc:description.abstract","label":"Abstract","values":["Low-velocity impact (LVI) on composites may cause Barely Visible Impact Damage (BVID), which is one of the most common damage types and may result in a decrease in strength of the composite. The objectives of this research were (a) to identify the characteristics of a carbon/epoxy composite plate after low-velocity impact, (b) to create a validated model to simulate the impact process and progressive failure, and (c) to perform sizing and shape optimization of the laminate for improving the damage resistance of the plate. As a part of this thesis, composite plates were fabricated using carbon fiber reinforced polymer (CFRP) prepreg. The LVI testing was performed on the samples with different impactors and different impact energy levels. The X-Ray Micro-tomography technique helped to reveal the internal fiber damage and matrix damage of the impacted plate. Numerical models with nonlinear dynamic responses were developed in ABAQUS, which validated the LVI experiments. Further, the modified model was created in MSC. PATRAN/NASTRAN to optimize the ply thickness, ply orientation, and dimensional properties of the plate to minimize the weight while abiding by the structural response constraints. Moreover, the possibility of the OpenMDAO framework in nonlinear dynamic analysis and size optimization was explored.
"]},{"key":"dc:title","label":"Title","values":["Analysis of After Impact Characteristics and Structural Optimization of CFRP Composite Plate"]}]}],"canonical_facts":{"dc:creator":["He, Zhennan"],"dc:description.abstract":["Low-velocity impact (LVI) on composites may cause Barely Visible Impact Damage (BVID), which is one of the most common damage types and may result in a decrease in strength of the composite. The objectives of this research were (a) to identify the characteristics of a carbon/epoxy composite plate after low-velocity impact, (b) to create a validated model to simulate the impact process and progressive failure, and (c) to perform sizing and shape optimization of the laminate for improving the damage resistance of the plate. As a part of this thesis, composite plates were fabricated using carbon fiber reinforced polymer (CFRP) prepreg. The LVI testing was performed on the samples with different impactors and different impact energy levels. The X-Ray Micro-tomography technique helped to reveal the internal fiber damage and matrix damage of the impacted plate. Numerical models with nonlinear dynamic responses were developed in ABAQUS, which validated the LVI experiments. Further, the modified model was created in MSC. PATRAN/NASTRAN to optimize the ply thickness, ply orientation, and dimensional properties of the plate to minimize the weight while abiding by the structural response constraints. Moreover, the possibility of the OpenMDAO framework in nonlinear dynamic analysis and size optimization was explored.
"],"dc:identifier":["https://commons.erau.edu/edt/555"],"dc:subject":["impact testing","composites","CFRP","carbon composites","Aerospace Engineering","Structures and Materials"],"dc:title":["Analysis of After Impact Characteristics and Structural Optimization of CFRP Composite Plate"],"thesis:degree_discipline":["Aerospace Engineering"],"thesis:degree_level":["Thesis - Open Access"],"thesis:degree_name":["Master of Science in Aerospace Engineering"]},"updated_at":"2026-07-27T19:25:29Z"}