• 한국컴퓨터산업교육학회:학술대회논문집
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• 2003.11a
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• pp.33-38
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• 2003

Reports have a significant meaning in time-constrained large transaction environments, such as airplane control systems or wargame simulations. This is due to the necessity of generating reports within a limited scope of time without restraining the operation performance of large transaction environments. In order to generate reports in large transaction environments while satisfying time - constrained requirements, this paper propose a model which combines the incremental operation mechanism and materialized view mechanism using triggers and stored procedures. Further, the implementation and evaluation of the preposed model provides analysis for model characteristics.

• Journal of Advanced Navigation Technology
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• v.10 no.4
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• pp.299-305
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• 2006

DURUMI-II is developed into test bed airplane for the multi-purpose flight test. It satisfied the civil aeronautics law. DURUMI-II is equipped with Airborne System for acquiring of flight test data and can fly by oneself. In this paper, the redundancy of DURUMI-II control system is operated sequentially is explained. The divided control surface and the requiring program method for flight test are described. Also, it is described that the exact control input is applied using the new method. Finally, the results of flight test for new method are analyzed.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.424-424
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• 2000

The implementation of a insect-based flying microrobot has been previously proposed as using magnetic force. The flying principle of a butterfly is different from that of a airplane, which obtain lifting force above the wings by a air stream with low pressure. Butterflies obtain lifting force below the wings by flapping. They can fly when drag during the down stroke is greater that during the up stroke. The structure of flying microrobot must satisfy these condition. And that must be manufacture lightly and keep balance for rising to the air sufficiently. Moreover the efficiency of an electromagnet is high and the flux density is sustained uniformly and widely Nevertheless these condition is satisfied, the implementation of a flying microrobot is very difficult as the flying microrobot has to fly without guides or sensor. We propose differently a new model il] comparison with that other paper has suggested. This imitates the form of the Korean shield-shaped kite.

• Journal of the Korean Society for Precision Engineering
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• v.20 no.2
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• pp.136-145
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• 2003

The integrity of stiffened panels with stringers in airplane structure is generally enhanced by investigating the fatigue crack propagation behavior in detail and providing the technical methodology to deal with the propagating crack. This paper attempts to clarify the effect of load-ratio on the fatigue crack propagation rate and the fatigue life for the thin aluminum 2024-T3. Both the variable and the constant fatigue loading conditions are considered for the fatigue crack propagation behavior in stiffened panels with stringers.

• Transactions of Materials Processing
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• v.6 no.4
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• pp.291-299
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• 1997

This paper is concerned with the design of process sequence to form the inner skin of landing gear. The inner skin of landing gear is a part of airplane which is known to be difficult to form its shape. Our study investigates the production method of inner skin and examines the design criteria by three dimensional elastic-plastic finite element method. Based on the results of simulation, design strategy for improving the process sequence is developed using stretch forming process. The final product of inner skin is produced in multi-stage operations with annealing treatment to meet the required capacity of press. The numerical results show that the newly designed process can produce the required part successfully within the design criteria.

• International Journal of Aeronautical and Space Sciences
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• v.6 no.2
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• pp.17-22
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• 2005

As one of validation tool for attitude determination system, we have used various constraints using priori information which is known through base vector set up. However these conventional constraints cannot guarantee validity in terms of final solutions such as Euler angle. So we suggest attitude boundary concept to verify the final attitude solution on the flying airplane, it is based on the combination of velocity based attitude estimation technique and ambiguity resolution. we can say it can check invalid solution effectively at just one epoch without repeatability test of resolved cycle ambiguity. In this paper we show that the suggested constraint can effectively reject incorrectly resolved cycle ambiguity the conventional constraints have missed.

• Proceeding of EDISON Challenge
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• 2015.03a
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• pp.274-278
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• 2015

There are different kinds of aircrafts, such as conventional airplane, rotorcraft, fighter, and unmanned aerial vehicle. Their shape and feature are dependent upon their assigned mission. One of the fundamental analyses during the design of the aircraft is the structural analysis. The structural analysis becomes more complicated and needs more computations because of the on-going complex aircrafts' structure. In order for efficiency in the structural analysis, a simplified approach, such as equivalent beam or plate model, is preferred. However, it is not clear which analysis will be appropriate to analyze the realistic configuration, i.e., an equivalent beam or plate analysis for an aircraft wing. It is necessary to assess the boundary between the one-dimensional beam analysis and the two-dimensional plate theory for an accurate structural analysis. Thus, in this paper, the static structural analysis results obtained by EDISON solvers were compared with the three-dimesional results obtained from MSC NASTRAN. Before that, EDISON program was verified by comparing the results with those from MSC NASTRAN program and analytic solution.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.14 no.2
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• pp.71-78
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• 2006

In this paper, it is described on the exportation trend and future development paradigm of the localized small aircraft which was recently developed four seated canard type aircraft for exportation purpose. Presently, even though the development of small aircraft is recessed, if we start development of the proper airplane models by integrating domestic power of industry-university-institute on the base of research experience from now on, we can go into the global market and take up the level of world top 10 makers without doubt. For successful operation of exportation system of small aircraft, it is needed to set up development strategy paradigm by forming consortium centering around the medium and small enterprises.

• Bulletin of the Society of Naval Architects of Korea
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• v.20 no.2
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• pp.43-49
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• 1983

Stiffened plates, mostly used in the major part of ship and airplane structures, have been studied by various way-theoretical and experimental. In case of the fore and aft parts of the parallel middle body of ship structure, the stiffeners are not right-angled to the plate but acute angled. This paper presents the analysis of plates having included stiffeners by Finite Strip Method. The results of calculation show the influence of inclined angle which is less than $10^{\circ}$is ignorable. It is recommended that, when the inclined angle is over $20^{\circ}$, the section modulus of stiffener should be increased.

• Journal of the Society of Naval Architects of Korea
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• v.40 no.6
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• pp.88-95
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• 2003

Liquid storage rectangular tank structures are used in many fields of airplane and marine engineering. Fatigue damages are sometimes observed in these tanks which seem to be caused by resonance. Therefore it is essentially important to estimate vibration characteristics of tank structures. Many Investigators studied the vibration of cylindrical and rectangular tank structures containing still fluid. In general, the eigenbehavior of interior liquid is characterized by the sloshing mode while that of the structure by the bulging mode. However, the structure deformation to the sloshing mode and the liquid free-surface fluctuation to the bulging mode have been neglected in the classical added-mass computation. in the present paper, we study the vibration characteristics with sloshing mode effect.