• Journal of Aerospace System Engineering
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• v.17 no.6
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• pp.144-148
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• 2023

Aircraft battery is the core equipment of an aircraft that supplies engine starting power and emergency power, and it must be charged to ensure sufficient capacity at all times and maintain high reliability to ensure stable power supply. The battery of the T-50 series aircraft is designed to enable the engine to start up to two times in temperatures as low as -18℃ and above. However, intermittent failures in engine starting have been observed during winter. In this paper, we analyze the failure phenomena occurring during low-temperature charging of the battery and improve the charging algorithm based on the analysis and test. Additionally, the results of start simulation tests show that the battery charging defects at low temperatures are resolved, and an improvement in the charging performance is confirmed; thus, validating the effectiveness of the new algorithm.

• Journal of Aerospace System Engineering
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• v.17 no.6
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• pp.108-117
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• 2023

Thus far, a mission software component of the KT-1 military fixed-wing aircraft for overseas export has been developed through international joint development with foreign companies. The reliability of the software component could be certified by complying with the development environment and procedures of foreign companies based on DO-178B. However, recently, DO-178C certification is required for overseas exports, and reliability tests to comply with the weapon system software development guidelines are required for domestic military forces. In this paper, we describe the problems in obtaining domestic airworthiness certification in the international joint development of a previously developed KT-1 export-typed aircraft system integration project. To this end, we find a solution to comply with both DO-178C and the Weapon System Software Development and Management Manual and provide the optimal software reliability test method.

• Journal of Aerospace System Engineering
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• v.17 no.6
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• pp.118-126
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• 2023

Most of the aerospace industries establish the SAE AS9100 Quality Management System, and acquire commercial certification by the 3rd party. Nevertheless, they repeatably have to cope with similar quality system evaluation by the airworthiness authority for the production certificate, parts manufacturer approval, and technical standard order authorization in accordance with the applicable regulations. The current quality system evaluation criteria of the airworthiness authority could be recommended for reforms in order to reduce duplication and correspond to the industrial development and environmental changes. In this paper, we propose measures to reform the authority's evaluation criteria through comparative analysis among the IAQG SAE AS9100, the FAA quality system codes, and the MOLIT ACSEP requirements.

• Journal of Advanced Navigation Technology
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• v.21 no.6
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• pp.561-571
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• 2017

Radio navigation systems are already used as important national infrastructures in various fields such as air traffic, land transportation, geodetic survey, broadcasting communication and national defense, and are used in various industries. Since these systems are fusion of various technologies, it takes much time and cost in the development stage. In the early stages of development of the system, developed countries are establishing a national mid-term plan that meets international compatibility and standards. Korea did not develop the system due to the lack of national mid- and long-term plan, and it is not contributing effectively to industries. This paper analyzes the technical principles and technology trend of radio navigation system in the aviation sector to establish mid - and long - term plan. Based on the analyzed technology trends, the future prospect of technological development of the domestic navigation system and the development of related industries will be presented.

• Composites Research
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• v.28 no.4
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• pp.212-218
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• 2015

A large composite spar was manufactured using an automatic fiber placement (AFP) machine. To verify its structural performance, the weakest part of the structure, which is called 'corner radius', was tested under bending and examined by finite element analysis. Since the application of AFP machine to composite structure fabrication is still in early stage in Korea, this paper presents the summary of whole process for manufacturing composite spar using AFP machine from mandrel design and analysis to verification test. The deflection and stress by mandrel weight and AFP machine force, thermal deformation and natural frequency were all examined for mandrel design. The target structure was composite C-spar and cured in an autoclave. Test results were compared with nonlinear finite element analysis results to show that the structure has the strength close to the theoretical value. It was confirmed that the corner radius of the spar manufactured by AFP process showed deviation less than 20% compared with first ply failure strength. The results indicate that the AFP technology could be used for large scale composite structure production in the near future.

• Journal of Advanced Marine Engineering and Technology
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• v.37 no.5
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• pp.477-483
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• 2013

The widlass base frame which is currently used is designed by lots of volume and costs so as to obtain high rigidity in spite of the greatly external load. The purpose of this research is to draw conceptual design of optimal design which can satisfy high rigidity existing windlass base frame has and lessening the body at the same time. Therefore, it progressed conceptual design by applying Topology optimization and Size optimization based on the finite-element analysis for the early model and indicated the result by comparing the early model with optimized model. As the result of Topology optimization, its stress was increased by about 6MPa and weight was decreased by about 560kg in comparison with the early model. In addition, in case of Size optimization, its stress was increased by about 7MPa and weight was decreased by about 1,560kg in comparison with the early model.

• Journal of Advanced Navigation Technology
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• v.22 no.4
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• pp.279-287
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• 2018

Flight tests for aircraft development and certification have higher air accidents risk than other aerospace industries. Accordingly risk identification necessary for risk management in the safety management system is a very important factor in preventing similar air accidents during flight tests. But internationally issued accident statistics are usually confined to commercial transport aircraft and they do not reflect characteristics of flight tests, also databases to hazards identification during flight tests are not established or available in Republic of Korea. Therefore, we identified flight test procedures and traced the major causes of aviation accidents based on the statistics and preventive materials for risk management which were issued by international organizations and advanced countries of aviation. A total of 312 final reports classified as flight test among air accident/incident database held by U.S. NTSB were researched and about 200 flight test hazard were identified. The results of this study will be used as basic data for establishing the safety management system of the national comprehensive flight performance test site.

• The Journal of the Acoustical Society of Korea
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• v.17 no.2E
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• pp.53-58
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• 1998

In this paper, we study the response of several anisotropic systems to buried transient line loads. The problem is mathematically formulated based on the equations of motion in the constitutive relations. The load is in form of a normal stress acting with arbitrary axis on the plane of monoclinic symmetry. Plane wave equation is coupled with vertical shear wave, longitudinal wave and horizontal shear wave. We first considered the equation of motion in reference coordinate system, where the line load is coincident with symmetry axis of the orthotrioic material. Then the equation of motion is transformed with respect to general coordiante system with azimuthal angle by using transformation tensor. The load is first described as a body force in the equations of the motion for the infinite media and then it is mathematically characterized. Subsequently the results for semi-infinite spaces is also obtained by using superposition of the infinite medium solution together with a scattered solution from the free surface. Consequently explicit solutions for the displacements are obtained by using Cargniard-DeHoop contour. Numerical results which are drawn from concrete examples of orthotropic material belonging to monoclinic symmetry are demonstrated.

• Structural Engineering and Mechanics
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• v.65 no.5
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• pp.513-521
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• 2018

In this paper, the resonance response of spar-type floating platform in coupled heave and pitch motion is investigated using a CPU time-effective numerical method. A coupled nonlinear 2-DOF equation of motion is derived based on the potential wave theory and the rigid-body hydrodynamics. The transient responses are solved by the fourth-order Runge-Kutta (RK4) method and transformed to the frequency responses by the digital Fourier transform (DFT), and the first-order approximation of heave response is analytically derived. Through the numerical experiments, the theoretical derivation and the numerical formulation are verified from the comparison with the commercial software AQWA. And, the frequencies of resonance arising from the nonlinear coupling between heave and pitch motions are investigated and justified from the comparison with the analytically derived first-order approximation of heave response.

• Journal of Welding and Joining
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• v.35 no.1
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• pp.49-54
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• 2017

In this study, the volumetric heat source in electron beam welding (EBW) is modeled through finite element method taking advantage of ABAQUS software package. Since this welding method is being applied in plates with different thicknesses and also considering that residual stresses reduce the strength of these weldments, the effect of thickness in the distribution and magnitude of residual stresses after welding is studied. Regarding the vast application of Inconel 706 super-alloy in aerospace industries, this material was selected in the current research. In order to validate the finite element model, the obtained results were compared to those of other researchers in this area, and good agreement was observed. The simulation results revealed that increase in the plate thickness leads to increase in the residual stresses. In addition heat treatment in the base metal (before welding) increases the residual stresses significantly.