• Journal of the Korea Society of Computer and Information
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• v.23 no.7
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• pp.57-62
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• 2018

In this paper, we propose an improved algorithm for rendering method to guarantee frame rates based on HMD (Head Mounted Display) motion in an avionics simulator. One of important issues in HMD simulators is to guarantee frame rates despite fast motion of HMD which is more rapid than the aircraft's moving speed to maintain a quality of images. Therefore, we propose an algorithm considering the moving speed of a pilot's head: Improved Speed-Based LOD (Level-Of-Detail) Control (ISBLC). In the proposed algorithm, frame rates are improved by changing dynamic LOD which determines details of objects for rendering images. Throughout the experiments, we show the average frame rates are achieved up to 60 and minimum frame rates are guaranteed up to 40. The proposed algorithms will be used HMD simulation in avionics simulators.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.30 no.1
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• pp.65-74
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• 2002

Composite materials are used for main structural components of aircraft fuselage such as skin, stringer and frame to reduce weight. Failure and buckling analysis of the composite fuselage components have been done for structural design. The loads of MD90-30 are applied to each component. Various shapes of section such as I, Z and T-type are chosen as candidate composite stringer and frame. The analysis results of composite fuselage components are compared according to ply-angle and ply-number, and the section type. The numerical results shows that ply-angle and ply-number have important effects on failure caused by axial load for the frame are important design parameters of composite fuselage components. This study suggests several design tips for composite fuselage components.

• Journal of the Korean Society for Precision Engineering
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• v.29 no.5
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• pp.538-544
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• 2012

In this paper, design optimization of C-frame of a precision drilling and autorivet machine has been performed. The machine, Autoriveter has been developed by Korea Aerospace Industry (KAI), For current autoriveter, it is hard to achieve high efficiency because of heavy weight of the machine. In this paper, we suggest new structure of the current C-frame, a part of autoriveter, by optimization. The result of the study can give much profit for mass-production of the machine.

• Advances in aircraft and spacecraft science
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• v.2 no.3
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• pp.233-248
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• 2015

Frame structures have been traditionally represented as an assembling of components, these last described within the beam theory framework. In the case of frames involving complex components in which classical beam theory could fail, 3D descriptions seem the only valid route for performing accurate enough analyses. In this work we propose a framework for frame structure analyses that proceeds by assembling the condensed parametric rigidity matrices associated with the elementary beams composing the beams involved in the frame structure. This approach allows a macroscopic analysis in which only the condensed degrees of freedom at the elementary beams interfaces are considered, while fine 3D parametric descriptions are retained for local analyses.

• 한국전산유체공학회:학술대회논문집
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• 2011.05a
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• pp.447-452
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• 2011

Propeller shall have high efficiency and improved aerodynamic characteristics to get the thru5t to fly at high speed for the Regional turboprop aircraft. That is way Clark-Y airfoil which is used to conventional turboprop aircraft propeller is selected as a blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the propeller design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point of Regional turboprop aircraft. The propeller design results indicate that is evaluated to be properly constructed, through analysis of propeller aerodynamic characteristics using the Meshless method and MRF, SM method.

• The KSFM Journal of Fluid Machinery
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• v.15 no.3
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• pp.19-24
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• 2012

Propeller shall have high efficiency and improved aerodynamic characteristics to get the thrust to fly at high speed for the turboprop aircraft. That is way Clark-Y airfoil which is used to conventional 1600kW class aircraft propeller is selected as a blade airfoil. Adkins method is used for aerodynamic design and performance analysis with respect to the propeller design point. Adkins method is based on the vortex-blade element theory which design the propeller to satisfy the condition for minimum energy loss. propeller geometry is generated by varying chord length and pitch angle at design point of turboprop aircraft. The propeller design results indicate that is evaluated to be properly constructed, through analysis of propeller aerodynamic characteristics using the Meshless method and MRF, SM method.

• Journal of Aerospace System Engineering
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• v.12 no.4
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• pp.18-25
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• 2018

The head frame structure of a machine tool for aircraft parts, which requires machining precision and machining of difficult-to-cut materials is required to be light-weighted for precision high-speed machining and to minimize possible deformation by cutting force. To achieve high stiffness and for light-weight structure optimization design, a preliminary model was designed based on finite element analysis. The topology optimization design of light-weight, high stiffness, and low vibration frame structure were performed by minimizing compliance. As a result, the frame weight decreased by 17.3%, the maximum deflection was less than 0.007 mm, and the natural frequency increased by 30.6%. The static stiffness was increased in each axis direction and the dynamic stiffness exhibited contrary results according to the axis. Optimized structure with the high stiffness of low vibration in topology optimization design was confirmed.

• Journal of the Korea Society for Simulation
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• v.23 no.4
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• pp.151-161
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• 2014

It is very important to evaluate proper acquisition of military aircraft against future threats in our military defense field. In previous studies, the evaluation has been determined in terms of tasking order or weapon power index. These methods compare the combat-effectiveness index and the number of aircraft. However, this study provides simulation analysis of proper quantity decision based on actual operational senarios of military aircraft using System Dynamics. The method reflects the properties of military aircraft operation concepts and considers the rate of failure of main systems on subsystems, as well as repair and crash rates caused by differentials in peacetime and wartime frame.

• Korea-Australia Rheology Journal
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• v.18 no.4
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• pp.171-181
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• 2006

We present a short review for authors' previous work on direct numerical simulations for inertialess hard particle suspensions formulated either with a Newtonian fluid or with viscoelastic polymeric fluids to understand the microstructural evolution and the bulk material behavior. We employ two well-defined bi-periodic domain concepts such that a single cell problem with a small number of particles may represent a large number of repeated structures: one is the sliding bi-periodic frame for simple shear flow and the other is the extensional bi-periodic frame for planar elongational flow. For implicit treatment of hydrodynamic interaction between particle and fluid, we use the finite-element/fictitious-domain method similar to the distributed Lagrangian multiplier (DLM) method together with the rigid ring description. The bi-periodic boundary conditions can be effectively incorportated as constraint equations and implemented by Lagrangian multipliers. The bulk stress can be evaluated by simple boundary integrals of stresslets on the particle boundary in such formulations. Some 2-D example results are presented to show effects of the solid fraction and the particle configuration on the shear and elongational viscosity along with the micro-structural evolution for both particles and fluid. Effects of the fluid elasticity has been also presented.

• Aerospace Engineering and Technology
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• v.11 no.1
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• pp.7-18
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• 2012

Full-scale static test was introduced for the KC-100 aircraft which is domestic civil aircraft to be certified for the first time. Test requirement, test frame, and important test stystems such as loading system, counterbalance system, restraint system and jacking system are explained in detail. Especially, the way to satisfy compliance for the installation of test article and loading system is introduced by using check sheets for the installations. 15 Full-scale and 7 local test conditions were successfully completed and the test data was obtained.