• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.6
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• pp.487-497
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• 2011

Numerical analysis has been performed to investigate the rotor speed and pitch range variations when the airspeed is increased in autorotation. Transient Simulation Method(TSM) was used to obtain the steady states of autorotation. The rotor blade was analyzed by the two-dimensional compressible Navier-Stokes solver in order to adapt to the airspeed increase and the results were used in the transient simulation method. Meanwhile, the Pitt/Peters inflow theory was used to supply the induced velocity fields. For the prescribed torque equilibrium state, the combinations of velocity, shaft angle, and pitch angle were produced to investigate the rotor speeds and variable ranges. The rotor tip Mach number and rotor speed were correlated and the trim range of pitch angle was observed with respect to the shaft angle decrease.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.1
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• pp.12-22
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• 2012

Performance variation of autorotating rotor was investigated. The shaft angle of the rotor is reduced while the flight velocity is increased. The BO-105 helicopter rotor blade was replaced by untwisted NACA 0012 airfoil and the rotor was simulated by using Transient Simulation Method(TSM) to judge the autorotation region for the variables. To simulate the compressibility effect at high speed flight, two-dimensional aerodynamic data was analyzed by compressible Navier-Stokes solver and Pitt/Peters inflow theory was adopted to simulate the induced velocity field. Thrust and lift coefficients, lift to drag ratio variations were investigated, also the lift and power were compared to those of BO-105 helicopter. Sharing lift and power between the autorotating rotor and wing was considered when the compound aircraft concept is introduced.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.6
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• pp.498-504
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• 2011

The flapping characteristics and advance ratios at torque equilibrium state of autorotation were investigated when the airspeed, shaft angle, and pitch angle were varied. To simulate the airspeed increase, the aerodynamic data analyzed by using the compressible Navier-Stokes solver and Pitt/Peters inflow theory were used. Transient Simulation Method(TSM) was used to catch the torque equilibrium states. The maximum flapping angles at torque equilibrium state were correlated to the airspeed, shaft angle, and pitch angle. By comparing flapping behavior to the variation of advance ratio, the phenomenon that the extension of reverse flow area of retreating blade affects the characteristics of autorotation was qualitatively considered.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.1
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• pp.1-11
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• 2012

Performance analysis was performed for an autorotating rotor. For a given airspeed, shaft angle, and collective pitch, the steady state of autorotation was judged by using the transient simulation method(TSM), then the thrust, lift, and drag coefficient for that state were computed. Average thrust was calculated from the instantaneous thrusts, in which the TSM was used in blade thrust integration. The analysis method was applied to the model rotor that had been tested by wind tunnel. Some comparison between analysis and test was provided. Two types of two-dimensional airfoil aerodynamic data were utilized in analysis, and they were made by Navier-Stokes Solver in terms of Reynolds and Reynolds-Mach number. The quantitative difference of results using two data set was examined and compared.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.971-977
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• 2015

A numerical analysis for the performance of compound gyroplane in forward flight was performed. TSM(Transient Simulation Method) was used to analyze the performance of autorotating rotor. CFD was conducted for the fuselages to recognize the variation of aerodynamic performance according to flight speed. At given conditions; airspeed, shaft angle and collective pitch, the quasi-static states of autorotation were determined and the variation of rotor performance was observed. Performance analysis results showed that the effect of aerodynamic characteristics in accordance with the shape of fuselage is so important that the streamlined fuselage is essential to fly fast. Forward flight speed limit is dependent on the autorotation performance of rotor.

• Journal of the Society of Naval Architects of Korea
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• v.39 no.4
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• pp.1-10
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• 2002

For the time-domain simulation of incipient breaking waves, usually the boundary integral method has been used so far, and it seems to be successful except a problem of too much computation time. The present paper shows a new computation technique for the simulation of breaking wave experiment. This technique uses the high-order spectral/boundary element method and the boundary integral method in sequence, and reduces the computation time remarkably. The wave generation and energy focusing process is efficiently simulated by the high-order spectral/boundary element method. Only the wave over-turning process is simulated by the boundary integral method. In the example calculation result, salient features of breaking waves such as high particle velocities and accelerations are shown.

• Proceedings of the Korean Nuclear Society Conference
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• 1999.10a
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• pp.54.1-54
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• 1999

• The Korean Journal of Rheology
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• v.9 no.3
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• pp.103-110
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• 1997

고분자 복합재료 제조방법의 하나인 수지이동성형의 충전공정을 모사하기 위한 수 치모사 코드를 개발하였다. 수지이동성형의 충정공정문제를 수학적 공식으로 표현하기 위하 여 비등방성 다공질체를 통과하는 유동에 대한 이론을 사용하였다. 과도상태로 진행하는 자 유표면의 동적 충전거동을 묘사하기 위하여 수치격자 생성을 포괄하는 경계적합 좌표계의 계산기법을 적용하였다. 이와 아울러 불규칙적인 구저와 다중으로 연결된 금형면의 충전모 사에 저합한 복합격자의 개념을 도입하였다. 복합격자들 간의 가상의 경계에 대해서는 검사 체적 기법을 이용하여 물질보존을 만족시켜 주었다. 임의의 금형 두께와 투과도를 가지는 다수의 금형면이 결합된 두 개의 입구를 지닌 금형을 대상으로 하여 몇가지 예를 시험해 보 았다. 수치모사의결과 복합격자의 개념을 도입한 수치모사 코드는 수지이동성형의 복잡한 충전공정을 보다 정교하게 모사하는데 응용될수 있음을 보여주었다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.6
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• pp.34-48
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• 2004

In this paper an optimization algorithm is suggested to reduce the huge computation time in the optimum design of large structures, especially in spacecraft structures. It combines the coupled load analysis model using a constrained mode of component mode synthesis and the modal transient analysis. The computer simulation code is developed and evaluated in optimizing spacecraft platforms. The developed algorithm can alleviate the computational load with adequate accuracy. From the optimization of a spacecraft structural member, the characteristics of each structural member can be understood.

• The Korean Journal of Rheology
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• v.5 no.2
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• pp.109-124
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• 1993

본 연구의 목표는 임의의 3차원 사출성형 금형 공간내에서 단섬유 강화 플라스틱의 충전 공정에서의 과도기적 섬유방향성을 예측하는 수치해석 프로그램의 개발에 있다. Hele-Shaw 방정식에 단섬유에 의해서 추가된 응력을 고려한 Dinh-Armstrong의 모델을 도 입함으로써 새로운 충전과정의 압력 지배 방정식이 유도되었다. 새로운 압력지배 방정식은 단섬유에 의한 응력 때문에 몇 개의 새로운 항들을 포함하고 있다. 충전 과정의 해석은 새 로운 압력지배방정식과 에너지 방정식을 유한효소법과 유한 차분법을 이용하여 풀고 동시에 배향텐서(roientation tensor)의 변화 방정식을 4차 Runge-Kutta 방법을 이용하여 풀었다. 단섬유 배향 텐서를 텐서의 변환 법칙을 이용하여 임의의 3차원 금형 공간내의 모든유한요 소의 중심에서 두께방향의 모든유한 차분 격자를 따라 계산하였다. 이러한 방법으로 임의의 3차원 사출성형 금형 공간내에서 비등온 충전유동과 과도기적 3차원 섬유배향상태를 서로의 상호작용을 고려하여 수치 모사하여 다양한 유동 형태에 따른 단섬유 배향 상태의 변화에 대하여 알아보고자 한다.