Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing
The evaluation of the reliability and the lifetime of aerospace components has become an important segment of the design stage. The aeronautical components are subjected to complex, rigorous tests and have a long test life. The main goal in the field of aviation is to have components with high relia...
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| Format: | Article |
| Language: | English |
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MDPI AG
2020-05-01
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| Series: | Materials |
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| Online Access: | https://www.mdpi.com/1996-1944/13/10/2310 |
| _version_ | 1797567714144813056 |
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| author | Sebastian Marian Zaharia Mihai Alin Pop Răzvan Udroiu |
| author_facet | Sebastian Marian Zaharia Mihai Alin Pop Răzvan Udroiu |
| author_sort | Sebastian Marian Zaharia |
| collection | DOAJ |
| description | The evaluation of the reliability and the lifetime of aerospace components has become an important segment of the design stage. The aeronautical components are subjected to complex, rigorous tests and have a long test life. The main goal in the field of aviation is to have components with high reliability and quality and to meet the mandatory requirements and regulations. The spars are stiffening components positioned along the wing and which take up most of the load and are tested for fatigue over a long period of time. The spar which was analysed in this study has a sandwich structure with GFRP (glass fiber reinforced plastic) skin and foam core. In this paper, the performances in the static and dynamic conditions of the GFRP-foam sandwich structures cut out of the composite spar of a glider were analysed. Additionally, using accelerated techniques based on the three-point fatigue bending test, the main reliability indicators of the GFRP-foam sandwich structures were determined. Using the statistical processing of the experimental data and the Inverse Power Law–Weibull acceleration model, the mean number of cycles to failure, in normal testing conditions of the GFRP-foam specimens was determined, with a value of 102,814. Using the accelerated testing techniques of the GFRP-foam sandwich structures an important decrease of the test time (8.43 times) was obtained. |
| first_indexed | 2024-03-10T19:46:24Z |
| format | Article |
| id | doaj.art-20b6d97a3ea04b04a79ee8bb81ac7453 |
| institution | Directory Open Access Journal |
| issn | 1996-1944 |
| language | English |
| last_indexed | 2024-03-10T19:46:24Z |
| publishDate | 2020-05-01 |
| publisher | MDPI AG |
| record_format | Article |
| series | Materials |
| spelling | doaj.art-20b6d97a3ea04b04a79ee8bb81ac74532023-11-20T00:46:37ZengMDPI AGMaterials1996-19442020-05-011310231010.3390/ma13102310Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life TestingSebastian Marian Zaharia0Mihai Alin Pop1Răzvan Udroiu2Manufacturing Engineering Department, Transilvania University of Brasov, Eroilor 29 Str, 500036 Brasov, RomaniaMaterials Science Department, Transilvania University of Brasov, Eroilor 29 Str, 500036 Brasov, RomaniaManufacturing Engineering Department, Transilvania University of Brasov, Eroilor 29 Str, 500036 Brasov, RomaniaThe evaluation of the reliability and the lifetime of aerospace components has become an important segment of the design stage. The aeronautical components are subjected to complex, rigorous tests and have a long test life. The main goal in the field of aviation is to have components with high reliability and quality and to meet the mandatory requirements and regulations. The spars are stiffening components positioned along the wing and which take up most of the load and are tested for fatigue over a long period of time. The spar which was analysed in this study has a sandwich structure with GFRP (glass fiber reinforced plastic) skin and foam core. In this paper, the performances in the static and dynamic conditions of the GFRP-foam sandwich structures cut out of the composite spar of a glider were analysed. Additionally, using accelerated techniques based on the three-point fatigue bending test, the main reliability indicators of the GFRP-foam sandwich structures were determined. Using the statistical processing of the experimental data and the Inverse Power Law–Weibull acceleration model, the mean number of cycles to failure, in normal testing conditions of the GFRP-foam specimens was determined, with a value of 102,814. Using the accelerated testing techniques of the GFRP-foam sandwich structures an important decrease of the test time (8.43 times) was obtained.https://www.mdpi.com/1996-1944/13/10/2310composite sparaccelerated fatigue life testingreliabilitylifetimeglider |
| spellingShingle | Sebastian Marian Zaharia Mihai Alin Pop Răzvan Udroiu Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing Materials composite spar accelerated fatigue life testing reliability lifetime glider |
| title | Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing |
| title_full | Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing |
| title_fullStr | Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing |
| title_full_unstemmed | Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing |
| title_short | Reliability and Lifetime Assessment of Glider Wing’s Composite Spar through Accelerated Fatigue Life Testing |
| title_sort | reliability and lifetime assessment of glider wing s composite spar through accelerated fatigue life testing |
| topic | composite spar accelerated fatigue life testing reliability lifetime glider |
| url | https://www.mdpi.com/1996-1944/13/10/2310 |
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