• Journal of Digital Convergence
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• v.15 no.6
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• pp.189-196
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• 2017

This study investigates customer satisfaction with full service carriers (FSC) and low cost carriers (LCC) using social media sentiment evaluation. From 2008 to 2016, a total of 77,591 tweets about two FSC and six LCC were aggregated and classified as per airline choice factors. Sentiment evaluation was employed to assess customer satisfaction by three appraisers. The results showed that customer satisfaction with LCC was significantly higher (p<0.001) compared to FSC. Furthermore, overall customer satisfaction with both FSC and LCC has been facing a consistent downward trend since the last seven years. The results also highlighted low customer satisfaction with respect to booking and flight operation factors, and a steep decline in customer satisfaction across booking, onboard services, and marketing factors for FSC. The results of this study have practical implications for the airline industry, which can use this quantitative data to improve customer satisfaction with FSC and LCC.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.39 no.10
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• pp.963-970
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• 2015

Laminate structures are used in the automobile, aerospace, and display industries. The advantages of fiber metal laminates are well known. Fiber metal laminates are useful for reducing the weight and improving impact resistance . However, currently, the mechanical properties of fiber metal laminates are not derived. In this paper, we use thickness as a factor for comparing the properties of laminates of various thickness combinations. The properties fiber metal laminates are analyzed using design of experiments. In addition, the finite element method is used to analyze elastic and plastic strains of fiber metal laminates and aluminum plates. The final goal of this paper is to find a suitable finite element model of fiber metal laminates under bending.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.29 no.5
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• pp.389-395
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• 2016

In this paper, vibration characteristics in terms of the airfoil cross-sectional shape was examined by using the EDISON co-rotational plane beam-transient analysis. Co-Rotational plane beam analysis is appropriate for large rotation and small strain. Assuming aircraft wing as a cantilevered beam, natural frequencies of each airfoil cross-sectional shape were estimated using VABS program and fast Fourier transformation(FFT). VABS conducts finite element analysis on the cross-section including the detailed geometry and material distribution to estimate the beam sectional properties. Under the same airfoil geometric configuration and material selection, variation of material induced difference in the deflection and natural frequencies. It was observed that variation of the natural frequency was dependent on variation of the airfoil shape and material.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.22 no.5
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• pp.480-488
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• 2012

The aircrafts with high aspect ratio wings made by a composite material have been developed, which enable high energy efficiency and long-term flight by reducing air resistance and structural weight. However, they have difficulties in securing the aeroelastic stability such as the flutter because of their long and flexible wings. The flutter is unstable self-excited-vibration caused by interaction between the structural dynamics and the aerodynamics. It should be verified analytically prior to first flight test that the flutter does not happen in the range of flight mission. Normally, the finite element model is used for the flutter analysis. So it is important to construct the finite element model representing dynamic characteristics similar to those of a real aircraft. Accordingly, in this research, to acquire dynamic characteristics experimentally the modal test of the aircraft with high aspect ratio composite wings was conducted. And then the modal parameters from the finite element analysis(FEA) were compared with those from the modal test. To make analysis results closer to test results, the finite element model was updated by means of the sensitivity analysis on variables and the optimization. Finally, it was proved that the updated finite element model is reliable as compared with the results of the modal test.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.38 no.12
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• pp.1335-1343
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• 2014

Piezoelectric paint can be used to monitor vibrations or impacts occurring in large engineering structures such as ships and airplanes. This study investigated the impact detection characteristics of a piezoelectric paint sensor and possible errors in detecting impacts according to boundary conditions. The piezoelectric paint sensor used in this study was coated on an aluminum plate with four different electrode areas. After the occurrence of the poling process, the output voltages from the paint sensors were obtained when impact occurred in a certain sensor region. The experimental results revealed a large difference in magnitudes between the sensor signal in the impact region and those in the other regions, and this relation was maintained regardless of the changes in the boundary conditions.

• Composites Research
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• v.14 no.2
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• pp.1-7
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• 2001

The studies on the formulation and curing behaviors of Kevlar/Epoxy prepreg for NOSE CONE of aircraft were presented in this paper. Dielectrometer and differential scanning calorimeter were used in order to check the curing behaviors. This prepreg showed the lowest ionic viscosity around $120^{\circ}C$, and then the ionic viscosity was gradually increased up to $200^{\circ}C$. This indicated that the curing reaction of this prepreg started at $120^{\circ}C$ and the molecular weight was increased by the accelerated thermal cross-linking reaction. The loss factor and tan $\delta$ values were also measured and discussed. The loss factor behaviors of Kevlar/Epoxy prepreg, which is related to the fluidity of matrix, were fecund to be similar with that of ionic viscosity. The thermal reaction properties of this prepreg were also studied by differential scanning calorimeter.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.27 no.11
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• pp.1012-1018
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• 2016

We perform a electromagnetic analysis method for indirect effects of a high-conductive structure such as an aircraft exposed by lightning, by using the finite-difference time-domain(FDTD) method. The lightning waveform used to analyze indirect effects has low frequency spectrum and high-conductive materials such as aluminum and carbon fiber composite materials have very short skin depths, and thus, it requires large memory and long computation time using conventional three dimensional FDTD analysis method. We develop an efficient electromagnetic analysis method suitable for lightning and high-conductive structures. The developed analysis method is based on two dimensional FDTD and impedance network boundary condition(INBC) algorithms and we investigate the indirect effects on the structures exposed to lightning.

• Journal of Digital Convergence
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• v.9 no.3
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• pp.59-67
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• 2011

The World aerospace industry grows consistently with the development digital technology. We study the activation of the digital aerospace industry based on avionics system, with respect to demand, system and industrial structure in the gimpo area. The strategy is made for aerospace industry to be a growth driver and then we suggest some projects to carry out it. Those are lasting creation of aerospace demand, possession of core part material and competitive digital technology, construction infrastructure for activation of system operation, improvement of administrative assistance system and finally strengthening policy modulation between civil, company, army, academy, and government. Therefore, it is possible to develop into it focusing the MRO and the Helicopter, if we complement systems related in the field of administration and Industry.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.23 no.1
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• pp.9-15
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• 2010

In this paper, dynamic modeling of hull structure including surface-bonded piezoelectric composite actuator was developed and structural vibration control performance was evaluated. Cylindrical shell structure with end-caps was considered as a host structure which could be used as a simple model of fuselage of aircraft and underwater vehicles. An advanced piezoelectric composite, macro-fiber composite(MFC), which has been developed in NASA Langley Research Center was applied for the effective structural vibration control. MFC has great flexibility by using piezoceramic fiber sheet and enhanced piezoelectric effect for in-plane motion by utilizing interdigitated electrode. Governing Equations were derived from the finite element model and modal characteristics were investigated. Modal test was conducted to verify the finite element model. Optimal controller was designed and implemented for the evaluation of vibration control performance. Structural vibration was controlled effectively by applying proper control input to the piezoelectric actuators.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.1-9
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• 2013

In order to increase endurance flight efficiency of long endurance electric powered UAV with solar cell, the light weight airframe design techniques are important. In this paper, the design of the main wing of electric powered UAV manufactured using Mylar film and fiber reinforced composite was conducted in order to achieve weight reduction and structural integrity of the structure. The shape of spar and size were determined using beam theory analysis. The finite element analysis of the wing was performed under various load condition derived from flight environment of EAV-2H. Finally, the static strength test of the main wing was conducted to verify structural integrity. It was found that the developed main wing weigh less than 42% than the previous EAV-2 and the main wing passed static strength test under ultimate load.