Abstract
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.
Highlights
The Sukhoi Su-30MKM is a Royal Malaysian Air Force (RMAF) super maneuverabilityMulti-Role Fighter Aircraft
The primary purpose of this paper is to describe the work carried out on the Su-30MKM Preventive and Restoration (PRW) project based on a Computer-Aided Engineering (CAE) analysis and fatigue analysis
The method in this paper proposed that breaking down the complex component of Computer-Aided Design (CAD) Modeling into a simplified model
Summary
The Sukhoi Su-30MKM is a Royal Malaysian Air Force (RMAF) super maneuverabilityMulti-Role Fighter Aircraft. Current management approaches rely on various combinations of inspection and early retirement to keep the structure safe. Structural optimization and the use of high-strength materials have increased the number of parts or regions that are highly stressed, which are, intrinsically intolerant of fatigue damage. Arising from these changes, one factor, more than any other, has attracted the attention of the fatigue research community over the years–the sensitivity of fatigue life to small cracks, and, to the surface condition and processing [2]
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