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[ subject:"Aerospace engineering." ]
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Experimental and Numerical Investiga...
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Thorsson, Solver I.
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Experimental and Numerical Investigation of Fiber Reinforced Laminated Composites Subject to Low-Velocity Impact.
紀錄類型:
書目-電子資源 : Monograph/item
正題名/作者:
Experimental and Numerical Investigation of Fiber Reinforced Laminated Composites Subject to Low-Velocity Impact./
作者:
Thorsson, Solver I.
出版者:
Ann Arbor : ProQuest Dissertations & Theses, : 2017,
面頁冊數:
263 p.
附註:
Source: Dissertation Abstracts International, Volume: 78-11(E), Section: B.
Contained By:
Dissertation Abstracts International78-11B(E).
標題:
Aerospace engineering. -
電子資源:
http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=10612202
ISBN:
9781369903355
Experimental and Numerical Investigation of Fiber Reinforced Laminated Composites Subject to Low-Velocity Impact.
Thorsson, Solver I.
Experimental and Numerical Investigation of Fiber Reinforced Laminated Composites Subject to Low-Velocity Impact.
- Ann Arbor : ProQuest Dissertations & Theses, 2017 - 263 p.
Source: Dissertation Abstracts International, Volume: 78-11(E), Section: B.
Thesis (Ph.D.)--University of Michigan, 2017.
Foreign object impact on composite materials continues to be an active field due to its importance in the design of load bearing composite aerostructures. The problem has been studied by many through the decades. Extensive experimental studies have been performed to characterize the impact damage and failure mechanisms. Leaders in aerospace industry are pushing for reliable, robust and efficient computational methods for predicting impact response of composite structures. Experimental and numerical investigations on the impact response of fiber reinforced polymer matrix composite (FRPC) laminates are presented. A detailed face-on and edge-on impact experimental study is presented. A novel method for conducting coupon-level edge-on impact experiments is introduced. The research is focused on impact energy levels that are in the vicinity of the barely visible impact damage (BVID) limit of the material system. A detailed post-impact damage study is presented where non-destructive inspection (NDI) methods such as ultrasound scanning and computed tomography (CT) are used. Detailed fractography studies are presented for further investigation of the through-the-thickness damage due to the impact event. Following the impact study, specimens are subjected to compression after impact (CAI) to establish the effect of BVID on the compressive strength after impact (CSAI). A modified combined loading compression (CLC) test method is proposed for compression testing following an edge-on impact. Experimental work on the rate sensitivity of the mode I and mode II inter-laminar fracture toughness is also investigated. An improved wedge-insert fracture (WIF) method for conducting mode I inter-laminar fracture at elevated loading rates is introduced. Based on the experimental results, a computational modeling approach for capturing face-on impact and CAI is developed. The model is then extended to edge-on impact and CAI. Enhanced Schapery Theory (EST) is utilized for modeling the full field damage and failure present in a unidirectional (UD) lamina within a laminate. Schapery Theory (ST) is a thermodynamically based work potential material model which captures the pre-peak softening due to matrix micro-cracking such as hackling, micro fissures, etc. The Crack Band (CB) method is utilized to capture macroscopic matrix and fiber failure modes such as ply splitting and fiber rupture. Discrete Cohesive Zone Method (DCZM) elements are implemented for capturing inter-laminar delaminations, using discrete nodal traction-separation governed interactions. The model is verified against the impact experimental results and the associated CAI procedures. The model results are in good agreement with experimental findings. The model proved capable of predicting the representative experimental failure modes.
ISBN: 9781369903355Subjects--Topical Terms:
1002622
Aerospace engineering.
Experimental and Numerical Investigation of Fiber Reinforced Laminated Composites Subject to Low-Velocity Impact.
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Foreign object impact on composite materials continues to be an active field due to its importance in the design of load bearing composite aerostructures. The problem has been studied by many through the decades. Extensive experimental studies have been performed to characterize the impact damage and failure mechanisms. Leaders in aerospace industry are pushing for reliable, robust and efficient computational methods for predicting impact response of composite structures. Experimental and numerical investigations on the impact response of fiber reinforced polymer matrix composite (FRPC) laminates are presented. A detailed face-on and edge-on impact experimental study is presented. A novel method for conducting coupon-level edge-on impact experiments is introduced. The research is focused on impact energy levels that are in the vicinity of the barely visible impact damage (BVID) limit of the material system. A detailed post-impact damage study is presented where non-destructive inspection (NDI) methods such as ultrasound scanning and computed tomography (CT) are used. Detailed fractography studies are presented for further investigation of the through-the-thickness damage due to the impact event. Following the impact study, specimens are subjected to compression after impact (CAI) to establish the effect of BVID on the compressive strength after impact (CSAI). A modified combined loading compression (CLC) test method is proposed for compression testing following an edge-on impact. Experimental work on the rate sensitivity of the mode I and mode II inter-laminar fracture toughness is also investigated. An improved wedge-insert fracture (WIF) method for conducting mode I inter-laminar fracture at elevated loading rates is introduced. Based on the experimental results, a computational modeling approach for capturing face-on impact and CAI is developed. The model is then extended to edge-on impact and CAI. Enhanced Schapery Theory (EST) is utilized for modeling the full field damage and failure present in a unidirectional (UD) lamina within a laminate. Schapery Theory (ST) is a thermodynamically based work potential material model which captures the pre-peak softening due to matrix micro-cracking such as hackling, micro fissures, etc. The Crack Band (CB) method is utilized to capture macroscopic matrix and fiber failure modes such as ply splitting and fiber rupture. Discrete Cohesive Zone Method (DCZM) elements are implemented for capturing inter-laminar delaminations, using discrete nodal traction-separation governed interactions. The model is verified against the impact experimental results and the associated CAI procedures. The model results are in good agreement with experimental findings. The model proved capable of predicting the representative experimental failure modes.
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