應用於輕航機機翼之碳纖維複合材料層板修補強度與模擬分析比較之研究

Study on Repair Strength and Simulation Analysis of Carbon-Fiber Composite Laminates for Light Aircraft Wings

林暘倫(Yang-Lun Lin)

指導教授 ： 洪健君

淡江大學/工學院/航空太空工程學系碩士班/碩士(2021年)

https://doi.org/10.6846/TKU.2021.00318

摘要

複合材料近年來在航空界運用的比例越來越多，因為質量輕及抗腐蝕性佳等特性，已經逐漸取代過去常見金屬材料。本論文的研究目的是將碳纖維複合材料運用於輕航機機翼上，根據機翼損壞位置並透過修補過後的結構強度分析是否與完整碳纖維層板相同；本研究首先以碳纖維標準試板12K(TC-35R)，利用真空加壓成型法，製作出3片共8層碳纖維層板，大小設定在250mm 250mm，方向為[0/90/45/-45]s。3片碳纖維層板分別為完整無破損的碳纖維層板、破壞過後的碳纖維層板以及破壞過後運用真空熱壓成型法(Vacuum Forming)進行修補的碳纖維層板；本研究將3片碳纖維層板進行強度測試，以確認修補過後的碳纖維是否和完整無破損的碳纖維層板承受相同強度壓力測試。為確保研究的穩定性、一致性及可靠度，透過非破壞性超音波檢測是否有修補正確，也能清楚地得知脫層以及裂縫位置，再運用有限元素套裝軟Abaqus模擬加壓並分析完整碳纖維層板的應力與結構強度，最後將模擬結果與分析結果兩者進行比較，分析誤差是在合理的範圍內。
本研究透過以上的實驗與分析，將碳纖維複合材料層板運用在輕型運動飛機襟翼上，透過有限元素套裝軟體Abaqus模擬，分析出最大應力以及最大變形量都是在合理範圍內，因此能夠驗證本研究碳纖維複合材料層板可以運用在輕航機機翼上下蒙皮，希望未來能夠應用更大量碳纖維複合材料在輕航機結構等相關領域。

關鍵字

碳纖維 ； 複合材料層板 ； 超音波檢測 ； 輕航機

並列摘要

In recent years, composite materials have been used more and more in the aerospace industry. Because of light weight and good corrosion resistant, composite materials have gradually replaced the common metal materials in the past. The purpose of this research is to apply the carbon fiber composite material to the wing of light aircraft. According to the strength of the repaired structure at the location of the wing damage, this research analyzed whether it is the same as the complete carbon fiber laminates. In this research, 3 pieces of 8-layer carbon fiber laminates were made by Vacuum Forming with carbon fiber 12K (TC-35R) with size set at 250mm 250mm and direction of [0/90/45/-45]s. The carbon fiber laminates are the complete carbon fiber laminates, the damaged carbon fiber laminates and the carbon fiber laminates repaired by Vacuum Forming after the damage. The carbon fiber laminates were strength tested to confirm whether the repaired carbon fiber was the same strength pressure test as the intact carbon fiber laminates.
In order to ensure the stability, consistency and reliability of this research, the non-destructive inspection, ultrasonic testing (UT), was used to determine whether the repair was correct and to clearly identify the delamination and crack locations. The stress and structural strength of the complete carbon fiber laminates were simulated and analyzed by Abaqus, and the simulation results were compared with the experimental analysis results. The error of analytical result is within a reasonable range.
In this research, through the above experiments and analysis, the carbon fiber composite laminates could be applied to the flaps of light sport aircraft, and the maximum stress and maximum deformation were found to be within a reasonable range through the FEA (Finite Element Analysis) Abaqus simulation. In the future, this research hopes to apply more carbon fiber composite materials in light aircraft structures and other related fields.

並列關鍵字

Carbon-Fiber ； Composite Laminate ； Ultrasonic Testing ； Light Aircraft

參考文獻

[1] 孫雨辰，季佳佳，馮蘊雯，“航空複合材料結構修理進展研究”，新視點，17期，頁58-61，2013。

[2] 蘇添財，“碳纖維的發展”，科學發展月刊，137期，頁50-53，1981。

[3] http://www.unioncarbide.com/, Union Carbide Corporation website. Accessed on: 21/12/2020.

[4] Nakamura, O., Ohana, T., Tazawa, M., Yokota, S., Shinoda, W., Nakamura, O.,and Itoh, J., “Study on the PAN Carbon-Fiber Innovation for Modeling a Successful R&D Management,” An Excited-Oscillation Management Model, Vol. 2, No. 2, pp. 154-164, 2011.

[5] 大谷杉郎、大谷朝男，碳纖維材料入門，復漢出版社，頁 26-52，2000。