Non-destructive testing to identify different failures in composite laminates
Conventional non-destructive testing of carbon composite components in aircrafts are highly time consuming, being overly reliant on excessive inspection to detect barely visible internal damages. Processes like the ultrasonic phased array testing requires significant time to complete inspection the...
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| Format: | Final Year Project (FYP) |
| Language: | English |
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Nanyang Technological University
2021
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| Online Access: | https://hdl.handle.net/10356/149452 |
| _version_ | 1811683762728075264 |
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| author | Toh, Zheng Jie |
| author2 | Sridhar Idapalapati |
| author_facet | Sridhar Idapalapati Toh, Zheng Jie |
| author_sort | Toh, Zheng Jie |
| collection | NTU |
| description | Conventional non-destructive testing of carbon composite components in aircrafts are highly time consuming, being overly reliant on excessive inspection to detect barely visible internal damages. Processes like the ultrasonic phased array testing requires significant time to complete inspection the components of an aircraft. Furthermore, the nature of the material allows for barely visible impact damages (BVID) to occur. BVID are a form of impact damage that provide minimal surface damage while hiding significant internal damages. These issues however can be resolved through the implementation of structural health monitoring systems. These monitoring systems are active systems, having the potential to constantly detect external forces and impacts via sensors within the structures of components during flight and ground operations. This study aims to distinguish and correlate the signal emissions of piezo ceramic sensors upon experiencing BVID. Energy required to fabricate BVID on carbon composite laminates were first determined through the use of quasi-static indentation and ultrasonic immersion tank testing. Subsequently, pristine and sensor embedded carbon composite laminates were then impacted via a low velocity impact test to induce BVID for further analysis. Development of the relationship between the sensor signal patterns to the degree of damage will be of beneficial use for further research of structural health monitoring in the aviation industry. |
| first_indexed | 2024-10-01T04:17:53Z |
| format | Final Year Project (FYP) |
| id | ntu-10356/149452 |
| institution | Nanyang Technological University |
| language | English |
| last_indexed | 2024-10-01T04:17:53Z |
| publishDate | 2021 |
| publisher | Nanyang Technological University |
| record_format | dspace |
| spelling | ntu-10356/1494522021-05-19T02:44:15Z Non-destructive testing to identify different failures in composite laminates Toh, Zheng Jie Sridhar Idapalapati School of Mechanical and Aerospace Engineering MSridhar@ntu.edu.sg Engineering::Materials::Composite materials Engineering::Mechanical engineering Conventional non-destructive testing of carbon composite components in aircrafts are highly time consuming, being overly reliant on excessive inspection to detect barely visible internal damages. Processes like the ultrasonic phased array testing requires significant time to complete inspection the components of an aircraft. Furthermore, the nature of the material allows for barely visible impact damages (BVID) to occur. BVID are a form of impact damage that provide minimal surface damage while hiding significant internal damages. These issues however can be resolved through the implementation of structural health monitoring systems. These monitoring systems are active systems, having the potential to constantly detect external forces and impacts via sensors within the structures of components during flight and ground operations. This study aims to distinguish and correlate the signal emissions of piezo ceramic sensors upon experiencing BVID. Energy required to fabricate BVID on carbon composite laminates were first determined through the use of quasi-static indentation and ultrasonic immersion tank testing. Subsequently, pristine and sensor embedded carbon composite laminates were then impacted via a low velocity impact test to induce BVID for further analysis. Development of the relationship between the sensor signal patterns to the degree of damage will be of beneficial use for further research of structural health monitoring in the aviation industry. Bachelor of Engineering (Mechanical Engineering) 2021-05-19T02:44:14Z 2021-05-19T02:44:14Z 2021 Final Year Project (FYP) Toh, Z. J. (2021). Non-destructive testing to identify different failures in composite laminates. Final Year Project (FYP), Nanyang Technological University, Singapore. https://hdl.handle.net/10356/149452 https://hdl.handle.net/10356/149452 en application/pdf Nanyang Technological University |
| spellingShingle | Engineering::Materials::Composite materials Engineering::Mechanical engineering Toh, Zheng Jie Non-destructive testing to identify different failures in composite laminates |
| title | Non-destructive testing to identify different failures in composite laminates |
| title_full | Non-destructive testing to identify different failures in composite laminates |
| title_fullStr | Non-destructive testing to identify different failures in composite laminates |
| title_full_unstemmed | Non-destructive testing to identify different failures in composite laminates |
| title_short | Non-destructive testing to identify different failures in composite laminates |
| title_sort | non destructive testing to identify different failures in composite laminates |
| topic | Engineering::Materials::Composite materials Engineering::Mechanical engineering |
| url | https://hdl.handle.net/10356/149452 |
| work_keys_str_mv | AT tohzhengjie nondestructivetestingtoidentifydifferentfailuresincompositelaminates |