Crack Growth Prediction on Critical Component for Structure Life Extension of Royal Malaysian Air Force (RMAF) Sukhoi Su-30MKM
| Autor: | Alizarin Ali, Ashaari Shafie, Roslina Mohammad, Arvinthan Venugopal, Fuad Shah Koslan, Owi Eugene |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2021 |
| Předmět: |
Wing root
Wing Mining engineering. Metallurgy fatigue critical location Airworthiness Computer science business.industry Numerical analysis crack growth prediction structure life extension Metals and Alloys TN1-997 wing root Structural engineering Life extension Airframe Ultimate failure aircraft structural integrity program General Materials Science business Engineering analysis |
| Zdroj: | Metals Volume 11 Issue 9 Metals, Vol 11, Iss 1453, p 1453 (2021) |
| ISSN: | 2075-4701 |
| DOI: | 10.3390/met11091453 |
| Popis: | The critical aircraft structure, being the load-bearing members, is a vital component for any aircraft. The effect of fatigue loading, operating conditions, and environmental degradation has caused the structural integrity of the airframe to be assessed for its airworthiness requirement. Using the fatigue design concept of Safe Life, the RMAF adopts the Aircraft Structure Integrity Program (ASIP) to monitor the structural integrity of its critical components. RMAF has produced the task card using the engineering analysis concept on the aircraft’s critical structure. Various Computer-Aided Engineering (CAE) methods were used, and for this analysis, the Crack Growth Prediction method was used to determine the crack growth behavior and its ultimate failure point in case of any crack occurrences. Although there are six critical locations, the wing root is chosen since it has the highest possibility of fatigue failure. The analytical methods which were discussed are Crack Growth Analysis and Low Cycle Fatigue. For the numerical method, NX Nastran was used for the simulation of crack growth. The result from the crack growth analysis was validated with the numerical result. The conclusion is that, based on the fatigue life cycle, the wing root structure condition is not affected by severe damage, and its failure is approximately around 30 to 100 years for both the through hole and through side crack. Thus, its structural life can be extended. The research outcome will be on the extension of the structure life of the aircraft wing. |
| Databáze: | OpenAIRE |
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