Inspection Interval Optimization for Aircraft Composite Tail Wing Structure Using Numerical-Analysis-Based Approach

Recently, there has been a tremendous increase in the use of fiber-reinforced composite (FRCP) in the aviation and aerospace industries due to its superior properties of high strength, stiffness, and low weight. The most important feature of implementing composite materials in aviation is their beha...

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Published inMathematics (Basel) Vol. 10; no. 20; p. 3836
Main Authors Khalid, Salman, Kim, Hee-Seong, Kim, Heung Soo, Choi, Joo-Ho
Format Journal Article
LanguageEnglish
Published Basel MDPI AG 01.10.2022
Subjects
Aerospace industry
Aircraft industry
aircraft tail wing structure
Airplanes
Aviation
Composite materials
Composite structures
Damage assessment
Deformations (Mechanics)
delamination
Design of experiments
Dynamic loads
Fatigue failure
Fiber composites
fiber-reinforced composites
Fibrous composites
finite element analysis
Finite element method
Flight time
Inspection
inspection interval
Maintenance costs
Mathematical models
Mechanical properties
Monte Carlo simulation
Optimization
Process parameters
Response surface methodology
Risk assessment
Stiffness
Wings
South Korea
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Summary:Recently, there has been a tremendous increase in the use of fiber-reinforced composite (FRCP) in the aviation and aerospace industries due to its superior properties of high strength, stiffness, and low weight. The most important feature of implementing composite materials in aviation is their behavior under dynamic loads and resistance to fatigue. To predict the life of composite structures and optimize the inspection interval, it is essential to predict the damage behavior of composites. In this study, a model of fatigue delamination damage of composite specimens was first constructed using a finite element analysis (FEA)-based approach. The FEA modeling was verified through comparison with experimental specimen data, and the verified FEA model was applied to the composite material aircraft tail wing structure. In this case, a Monte Carlo simulation (MCS) was performed by building a response surface model while considering the uncertainty of the mechanical parameters. Through this process, the risk as a function of flight time could be quantitatively evaluated, and the inspection interval was optimized by selecting the combination with the lowest number of repeated inspections that met the permitted risk criteria.
ISSN:2227-7390
2227-7390
DOI:10.3390/math10203836