• Korean Journal of Materials Research
• /
• v.10 no.5
• /
• pp.354-659
• /
• 2000

Applications of composite materials have been in progress noticeably in manufacturing areas of automotive, aircraft and in other industries, resulting in ensuing research activities. Carbon-epoxy, one of major composite materials, is investigated for its thermal characteristics. Upon treatments of the composite material with repeated heatings and coolings variations of its elastic constants are monitored to reveal the thermal nature of the composite material. In this study, generally, changes in elastic constants are observed to occur mostly during the first 10~20 thermal cycles. Values of G(sub)13 remain almost unchanged except a minor decrease. However in the observed small changes thermal shocks produce less effect than thermal fatigues. On the other hand, values of $E_1$show gradual increases with the num-ber of applied thermal cycles and temperatures. Meanwhile, values of $E_2$ and G(sub)23 decrease to a certain extent in the early stage during the applications of thermal cycling but are not appreciable affected by frequencies of thermal cy-cles. Also, thermal shocks are observed to induce different effects depending on treatment temperatures.

• Journal of Korea Port Economic Association
• /
• v.23 no.2
• /
• pp.25-40
• /
• 2007

The sea/air intermodal transport is a time-saving and cost-saving transport for cargo shipments. In reaction to a recent growth of high value-added products in China, the volume of sea/air intermodal transport in Korean airport has been increasing continuously. This paper treats the situation, the system, and the possibility of sea/air intermodal transport, which are emerging as an alternative to solve the logistics problem related to the increase of international air cargo demand in China. Also, several strategies are considered to develope Korea into intermodal transport hub including the value added logistics activity which will secure the demand of sea/air intermodal transport.

• Journal of Convergence for Information Technology
• /
• v.8 no.3
• /
• pp.107-114
• /
• 2018

Recently, as aviation industry has been activated, development of software related to composite materials has been demanded. Composite analysis requires specialized structural analysis and test evaluation. Therefore, it is necessary to use existing commercial software to analyze the composite structure, but existing commercial software only provides limited functions. Especially, since there is no specialized software for corner structure analysis of aerospace composites spa structure, much human resources and time are consumed in structural analysis. In order to solve this problem, we developed a GUI-based automation software based on user-friendly GUI that reflects the existing corner structure analysis procedure and provides multiple breakdown criteria. To verify the reliability of the structural analysis results of the developed software, it was confirmed that there is no problem in the structural analysis performance as a result of comparing with the existing analysis results.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.25 no.6
• /
• pp.74-86
• /
• 2021

The composite lattice structure is a structure that supports the required load with the minimum weight and thickness. Composite lattice structure is manufactured by the filament winding process using impregnating high-strength carbon fiber with an epoxy resin. Filament winding process can laminate and manufacture only structurally necessary parts, composite lattice structure can be applied to aircraft fuselages, satellite and launch vehicles, and guided weapons to maximize weight reduction. In this paper, the development and evaluation of the composite lattice structure corresponding to the entire process from design, analysis, fabrication, and evaluation of large-scale cylindrical and conical composites lattice structure were performed. To be applicable to actual projectiles and guided weapons, we developed a cylindrical lattice structure with a diameter of 2,600 mm and a length of 2,000 mm, and a conical lattice structure with an upper diameter of 1,300 mm, a lower diameter of 2,500 mm, and a length of 900 mm. The performance of the developed composite lattice structure was evaluated through a load test.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.30 no.4
• /
• pp.114-122
• /
• 2002

The integration of the landing gear system is a complex relationship between the many conflicting parameters of shock absorption, minimum stow area, complexity, weight and cost. Especially ground impact load and dynamic behaviors greatly influence design load of landing gear components as well as load carrying structural attachment. This study investigates ground impact load and dynamic behaviors of the T-50 landing gear system using ADAMS. Taking into account for various operational/environmental conditions, an analysis of shock absorbing characteristics at ground impact is performed with experience derived from a wide range of proprietary designs. Analytical results are presented for discussing the effects of aircraft horizontal and vertical speed, landing attitudes, shock absorbing efficiency. This analysis leads us to the conclusion that the proposed program is shown to be a better quantitative one that apply to a new development and troubleshooting of the landing gear system.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.40 no.11
• /
• pp.917-926
• /
• 2012

The analysis of aerodynamic characteristics for aircraft propellers is studied to develop high efficiency composite propellers. It is to verify the accuracy and reliability of predicting the efficiency characteristics of aircraft propellers by applying nonlinear numerical analysis. The numerical simulation method incorporated the CFD code, which is based on RANS (Reynolds Averaged Navier-Stocks) equation. The study includes a comparative analysis between the numerical simulation results and the wind tunnel test results of the full-scale aircraft propeller. The comparison shows that thrust and power coefficients of the propeller calculated by nonlinear numerical analysis are higher than those based on the results generated from the wind tunnel test. The efficiency of the propeller calculated by numerical analysis matches closely to the efficiency based on the wind tunnel test results. The verification results are analyzed, then, will be used in optimizing the design and manufacture of the subject aircraft propeller studied.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.5
• /
• pp.110-116
• /
• 2003

With the growth of aircraft performance and needs for light aircraft, the problems associated with hail impacts on aircraft during flights and grounding become and important issue. These hail encounters can cause severe damages to aircraft and result in major concerns in safety and cost. Since nearly all external components of the commercial and military aircraft-in particular, the nose section and the leading edge of the wing and tail-are subject to damages, much effort has been put into understanding of this problem. However, most of the previous studies have focused on the composite components and few results have been reported for the metallic components. In this paper, we study the ice impacts on the aluminum component with the finite element analysis method utilizing commercial non-linear dynamics solver LS-DYNA. The results are compared with the experimental data and a simple measure of the ice impact effects is proposed.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.34 no.1
• /
• pp.65-73
• /
• 2006

The high temperature occurs due to the combustion gas from engine in unmanned aerial vehicles (UAV). The high temperature may cause serious damages in UAV structure. The Functionally Graded Material (FGM) is chosen as a candidate material of the engine duct structure. A functionally graded material (FGM) is a two- component mixture composed by compositional gradient materials from one material to the other. In contrast, traditional composite materials are homogeneous mixtures, and involve compositions between the desirable properties of the component materials. Since significant proportions of an FGM contain the pure form of each material, the need for compromise is eliminated. The properties of both components can be fully utilized. Thermal stress analysis of FGM layers (20, 40, 60, 80 and 100) is performed in this paper. In addition, the creep behavior of FGM applied in duct structure of an engine is analyzed for better understanding of FGM characteristics.

• Composites Research
• /
• v.35 no.2
• /
• pp.106-114
• /
• 2022

Carbon fiber-reinforced plastic, well known high specific strength and high specific stiffness, have been widely used in the aircraft industry. Mostly the CFRP structure is fabricated by lamination of carbon fiber or carbon prepreg, which has major disadvantage called delamination. Delamination is usually produced due to absence of the through-thickness direction fiber. In this study, three-dimensional carbon preform woven in three directions is used for fabrication of aircraft wing unit structure, a part of repeated structure in aircraft wing. The unit structure include skin, stringer and rib were prepared by resin transfer molding method. After, the 3D structure was compared with laminate structure through compression test. The results show that 3D structure is not only effective to prevent delamination but improved the mechanical strength. Therefore, the 3d preform structure is expected to be used in various fields requiring delamination prevention, especially in the aircraft industry.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.48 no.8
• /
• pp.555-563
• /
• 2020

Foward-swept wings are known to possess superior aerodynamic performance compared to the conventional straight wings. However major concerns regarding forward-swept wings include divergence at lower airspeeds which require careful consideration at the design stage. As an endeavor to overcome such drawbacks, aeroelastic tailoring is attempted. In order to find an optimal ply sequence, recursive aeroelastic analyses is conducted and one-dimensional beam analysis coupled with simple aerodynamics is used for the improved computational efficiency and modelling convenience. The analysis used in this paper, DYMORE and analytic formula, both use one-dimensional beam model for the structure. Cross-sectional analysis for multi-cell NACA0015 airfoil section is conducted using VABS and oblique function is used for the sweep angle. Throughout the present aeroelastic tailoring, the maximum divergence speed of 290.2m/s is achieved which is increased by approximately 43% than that for the conventional ply configuration.