• 제어로봇시스템학회논문지
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• 제17권4호
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• pp.289-294
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• 2011

Digital redesign is yet another efficient tool to convert a pre-designed analog controller into a sampled-data one to maintain the analog closed-loop performance in the sense of state matching. A rising difficulty in developing a digital redesign technique for trackers with time-varying references is the unavailability of a closed-form discrete-time model of a system, even if it is linear time-invariant. A way to resolve this is to approximate the time-varying reference as a piecewise constant one, which deteriorates the state matching performance. Another remedy may be to decrease a sampling period, which however could numerically destabilize the optimization-based digital redesign condition. In this paper, we develop a digital redesign condition for time-varying trackers by approximating the time-varying reference through a triangular hold and by introducing delta-operated discrete-time models. It is shown that the digitally redesigned sampled-data tracker recovers the performance of the pre-designed analog tracker under a fast sampling limit. Simulation results on the formation flying of satellites convincingly show the effectiveness of the development.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2017년도 제48회 춘계학술대회논문집
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• pp.647-650
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• 2017

초음속 비행체 개발의 필요성이 증가됨에 따라 저고도에서부터 고고도까지 다양한 고공환경을 비행하는 비행체의 공력특성 데이터 확보가 요구되고 있다. 기존의 건국대학교 불어내기식 초음속 풍동(MAF)의 유동가열장치를 개선하여 고고도/실기체 환경 모사가 가능하도록 장비를 구축하였다. 본 장비를 활용하여 유도무기체계 및 초음속 비행체 선두부에 발생하는 유동과 그에 따른 온도 분포 및 속도 분포에 관하여 연구할 예정에 있다.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2007년도 춘계학술대회B
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• pp.2857-2861
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• 2007

Flow and aerodynamic characteristics were analyzed numerically for a commercial passenger airplane, Boeing 747-400, flying in the cruising condition. The model geometry with 100:1 in scale was obtained by the photo scanning measurement with the maximum error of 1.4% comparing with the real airplane dimension. The three-dimensional inviscid steady compressible governing equations were solved by the finite volume method in the unstructured grid system. The convective terms were treated by the Crank-Nicholson and first-order upwind schemes. In the computational results, the strong wing-tip vortices were clearly observed and the pressure contours on the airplane surface were suggested. The lift and drag forces in the wing with engines increase by 1.49% and 3.9%, respectively compared with the case without engines. The aerodynamic forces were estimated quantitatively for each element which consists of the airplane.

• 한국군사과학기술학회지
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• 제16권5호
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• pp.607-612
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• 2013

The effect of the flow actuator on the asymmetric vortex structure around the ogive-cylinder body with fineness ratio of 4 flying at the speed of Mach 0.1 at angle of attack of 50 degree is studied. The ogive-cylinder model is developed with the actuator placed near the nose tip and numerically simulated using the in-house CFD code named KFLOW. The numerical simulation employs two different actuator modeling: one is the boundary condition given by blowing normal to the surface and another shearing on the surface. The numerical simulation reveals that response of the vortex structure to the actuation is dependent on the type of modeling as well as the strength and direction of the actuation.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.92-92
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• 2000

Helicopter offer the signigicant advantage over traditional air vehicles, in that the provide extended maneuverability, such as vertical climb, hovering, longitudinal and lateral flight, hovering turns and bank turns. But helicopter have the strong cross couplings and nonlinearities for each lateral, longitudinal and rotational motion mutually. However, it is possible to ignore this couplings for the hovering condition, so using this properties we can control the attitude of helicopter. That is, by implementing the dynamic of each rotational axis(roll, pitch, yaw) of independent mutually, 3-DOF(degree of Freedom) attitude control for the helicopter is possible. In this paper, we identify decoupled input-coutput relations of each three rotational axis about the helicopter mounted on the 3-DOF gimbal by experiment, and on these basis implement 3-DOF attitude controller using the PID control method.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2004년도 춘계학술대회
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• pp.716-721
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• 2004

In this study, dome port bringing up for discussion where the ramjet occurs in flying it presents the tendency of distribution of thermal contour due to temperature and pressure. It is assumed that the material of ramjet is steel for the ease of result analysis. It applied matrial property which it follows by temperature and input boundary condition that changing temperature and pressure on each region by time difference for transient analysis. Thermal analysis region is decided until dome port part is separated and operate analysis in 0.5 second. Finally we draw tendency of thermal contour in ramjet dome port part by temperature and pressure.

• 한국철도학회:학술대회논문집
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• 한국철도학회 2006년도 추계학술대회 논문집
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• pp.414-419
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• 2006

The ballast or other objects may be located on the rail road by a lump of ice, repairing operation on the track, or the strong gust due to the high speed running of the train. When a train operated in this condition, it causes serious damages to the wheel, train, and structures near the track, or the secondary ballast flying. To remove these objects safely, a ballast blower is suggested which was attached under the train. Firstly, the numerical analyses are investigated to find out the basic flow characteristics of the ballast blower. Next, the performance of the ballast blower is verified by wind tunnel experiments. Through these studies, it is expected that the ballast blower can be applied practically.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년도 제31회 추계학술대회논문집
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• pp.167-170
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• 2008

아음속과 초음속 영역에서 모두 비행하는 재사용 비행체의 추진기관인 TBCC(Turbine Based Combined Cycle)엔진의 성능 설계 기법에 대한 연구를 수행하였다. 이 엔진은 터보제트엔진과 램제트 엔진의 복합 사이클 엔진으로 구성되어 있으며, 비행 마하수 영역별로 터보제트엔진의 작동과 램제트 엔진의 작동 그리고 터보제트엔진과 램제트엔진이 동시 작동하는 구간으로 구성된다. TBCC엔진의 성능해석 기법을 제안하고, 개별 엔진의 성능 결과를 검증 하였으며, 가상의 비행 영역에서 TBCC엔진의 성능을 해석하였다.

• 대한조선학회논문집
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• 제48권5호
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• pp.381-389
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• 2011

In this study, we are focusing our attention on lift characteristics of the low aspect wings for Wing-In Ground effect crafts (WIG). Experimental measurements at an open-type wind tunnel are carried out and results are comparatively presented. In order to simulate the realistic ground condition in where the WIG craft is flying, moving ground is implemented by a conveyor belt rotating with the same velocity of the inflow. We consider two different wings (NACA0012 and DHMTU section) which have four different aspect ratios (0.5, 1.0, 1.5 and 2.0). Forces acting on the wings are measured and lift characteristics are elaborately investigated for various different conditions. In addition, end-plate effects are estimated. Results are validated by comparing with theoretic solutions of the symmetric airfoil. Present results show that ground effects are differently generated in moving or fixed ground conditions, and hence left characteristics are affected by the ground condition. Consequently, accurate aerodynamic forces acting on the WIG craft are guaranteed in a realistic moving ground condition.

• 한국식품영양학회지
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• 제16권2호
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• pp.130-137
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• 2003

The squid had not been utilized for gel products because of its lower gel forming ability. The objectives of this study were as followed; 1) the optimum heating condition on squid meat paste products and 2) the optimum added level for jelly strength of squid meat paste products. Optimum heating conditions of squid meat kamaboko were as followed; setting(pre-heating) at 15$^{\circ}C$ or 55$^{\circ}C$ for 2 hours and heating at 9$0^{\circ}C$ for 60 minutes. The additives examined were as follows; 20mM EDTA, 10mM PMSF, 5 $\mu$mol/100g TGase, 0.2% potassium bromate, 2% collagen, 2% sucrose ester of stearic acid and 1% egg shell powder. The effects of additives on jelly strength were observed as follow, in descending order; 10mM of PMSF>5 $\mu$mo1/100g of TGase>0.2% of potassium bromate>20mM of EDTA. But sucrose ester of stearic acid and 1% egg shell powder were no effect. The solvents examined were as follows; n-amyl alcohol, n-butyl alcohol, n-hexyl alcohol, ethyl alcohol, ethylene glycol, propylene glycol and glycerin glycol. It showed that high jelly strength as 787gㆍcm for 3% of n-butyl alcohol and 749gㆍcm for 3% of n-amyl alcohol. To adding 5% of n-butyl alcohol and n-amyl alcohol, gave the highest jelly strength and water holding capacity(WHC). Effect of alcohol on jelly strength appeared higher value at added 5% of n-butyl alcohol than n-amyl alcohol, and flying squid product was higher than jumbo squid product.