• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2006년도 제26회 춘계학술대회논문집
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• pp.257-263
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• 2006

액체로켓엔진 연소기는 연소성능 및 연소안정성 분야에 있어서 높은 신뢰도를 가져야 한다. 특히, 추진제의 혼합을 담당하는 분사기는 이 신뢰도를 결정짓는 중요한 요소이다. 연소안정성 관점에서 수행된 본 연구는 모델 상사 기법을 이용하여 동축 와류 분사기의 연소안정성 특성을 평가하였다. 또한 연소안정성 증대를 위해 사용하는 배플의 경우 축방향 길이 및 간극 변화로부터 나타나는 효과를 검토하였다.

• International Journal of Concrete Structures and Materials
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• 제11권2호
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• pp.377-389
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• 2017

Tests of the lateral and torsional stability are quite sensitive to the experimental conditions, such as support conditions and loading system. Controlling all of these conditions in a full-size test is a very challenging task. Therefore, in this paper, an experimental measurement method that can control the experimental conditions using a small-scale model was proposed to evaluate the lateral and torsional stability of beams. For this, a loading system was provided to maintain the vertical direction of the load applied to the beam, and a support frame was produced to satisfy the in-plane and out-of-plane support conditions. The experimental method using a small-scale model was applied successively to the lateral and torsional behavior and stability of I-shaped beams. The proposed experimental methods, which effectively accommodate the changes in the geometry and length of the beam, could contribute to further experimental studies regarding the lateral and torsional stability of flexural members.

• Advances in aircraft and spacecraft science
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• 제10권5호
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• pp.419-437
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• 2023

This paper presents the study of the effects of rigid-body motion simultaneously with the presence of the effects of temporal variation due to the existence of morphing speed on the aeroelastic stability of the two-stage telescopic wings, and hence this is the main novelty of this study. To this aim, Euler-Bernoulli beam theory is used to model the bending-torsional dynamics of the wing. The aerodynamic loads on the wing in an incompressible flow regime are determined by using Peters' unsteady aerodynamic model. The governing aeroelastic equations are discretized employing a finite element method based on the beam-rod model. The effects of rigid-body motion on the length-based stability of the wing are determined by checking the eigenvalues of system. The obtained results are compared with those available in the literature, and a good agreement is observed. Furthermore, the effects of different parameters of rigid-body such as the mass, radius of gyration, fuselage center of gravity distance from wing elastic axis on the aeroelastic stability are discussed. It is found that some parameters can cause unpredictable changes in the critical length and frequency. Also, paying attention to the fuselage parameters and how they affect stability is very important and will play a significant role in the design.

• 대한수학회보
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• 제49권2호
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• pp.319-327
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• 2012

The equations of a multifluid interpenetration mix model are analyzed. The model is an intermediate mix model in the sense that it is defined by partial pressures but only a single global pressure and a single global temperature. It none-the-less avoids the stability difficulty. It is shown that the model is hyperbolic so that it is mathematically stable.

• Korean Journal of Mathematics
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• 제13권2호
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• pp.149-159
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• 2005

We study an age-dependent s-i-s epidemic model with spatial diffusion. The model equations are described by a nonlinear and nonlocal system of integro-differential equations. Finite difference methods along the characteristics in age-time domain combined with finite elements in the spatial variable are applied to approximate the solution of the model. Stability of the discrete periodic solution is investigated.

• 해양환경안전학회지
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• 제20권4호
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• pp.443-450
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• 2014

본 연구에서는 수중익 배치와 종모멘트 특성이 전몰형 수중익선의 종방향 운동 안정성에 미치는 영향에 대하여 Tandem 수중익 모형의 시험을 통하여 고찰한다. 먼저, Canard 날개배치를 가지는 Tandem 수중익 모형을 제작하고 수중익의 양력 및 항력 계측 실험을 수행하여 양력 및 항력 특성을 평가하였다. 또한 종방향 운동의 초기 안정성과 자기 안정성을 가지는 Tandem 수중익 모형의 날개 배치를 결정하였다. Tandem 수중익 모형의 종안정성 시험에서는 선수 및 선미 수중익의 종방향 간격 변화와 종모멘트의 자기안정성 변화에 따른 Pitch 및 Heave 운동 특성, 익주 상태의 종안정성을 평가하였다. 먼저, Canard 날개배치를 가지는 Tandem 수중익 모형을 제작하고 수중익의 양력 및 항력 계측 실험을 수행하여 양력 및 항력 특성을 평가하였다. 또한 종방향 운동의 초기 안정성과 자기 안정성을 가지는 Tandem 수중익 모형의 날개 배치를 결정하였다. Tandem 수중익 모형의 종안정성 시험에서는 선수 및 선미 수중익의 종방향 간격 변화와 종모멘트의 자기안정성 변화에 따른 Pitch 및 Heave 운동 특성, 익주 상태의 종안정성을 평가하였다. 실험 수행 결과 본 연구의 주요 결론의 다음과 같다. 종 모멘트 자기 안정성이 클수록 주어진 고정 pitch 각에서 pitch운동에 대한 자기안정성이 높다. 다음 종모멘트 자기 안정성이 클수록, pitch각도 변화에 따른 pitch운동 및 heave운동의 변동 폭이 상대적으로 작으며 종방향 안정성이 우수하다. 마지막으로 종모멘트 자기안정성이 클수록, 수중익 양력이 동일한 경우, Tandem 수중익의 안정적인 익주를 위해서는 충분한 종모멘트의 자기안정성을 확보하는 것이 필수적인 것을 시험을 통하여 확인하였다.

• Wind and Structures
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• 제10권4호
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• pp.367-382
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• 2007

A nonlinear numerical method was developed to assess the stability of suspension bridge catwalks under a wind load. A section model wind tunnel test was used to obtain a catwalk's aerostatic coefficients, from which the displacement-dependent wind loads were subsequently derived. The stability of a suspension bridge catwalk was analyzed on the basis of the geometric nonlinear behavior of the structure. In addition, a full model test was conducted on the catwalk, which spanned 960 m. A comparison of the displacement values between the test and the numerical simulation shows that a numerical method based on a section model test can be used to effectively and accurately evaluate the stability of a catwalk. A case study features the stability of the catwalk of the Runyang Yangtze suspension bridge, the main span of which is 1490 m. Wind can generally attack the structure from any direction. Whenever the wind comes at a yaw angle, there are six wind load components that act on the catwalk. If the yaw angle is equal to zero, the wind is normal to the catwalk (called normal wind) and the six load components are reduced to three components. Three aerostatic coefficients of the catwalk can be obtained through a section model test with traditional test equipment. However, six aerostatic coefficients of the catwalk must be acquired with the aid of special section model test equipment. A nonlinear numerical method was used study the stability of a catwalk under a yaw wind, while taking into account the six components of the displacement-dependent wind load and the geometric nonlinearity of the catwalk. The results show that when wind attacks with a slight yaw angle, the critical velocity that induces static instability of the catwalk may be lower than the critical velocity of normal wind. However, as the yaw angle of the wind becomes larger, the critical velocity increases. In the atmospheric boundary layer, the wind is turbulent and the velocity history is a random time history. The effects of turbulent wind on the stability of a catwalk are also assessed. The wind velocity fields are regarded as stationary Gaussian stochastic processes, which can be simulated by a spectral representation method. A nonlinear finite-element model set forepart and the Newmark integration method was used to calculate the wind-induced buffeting responses. The results confirm that the turbulent character of wind has little influence on the stability of the catwalk.

• 경영정보학연구
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• 제20권4호
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• pp.79-96
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• 2018

본 연구는 기술력 평가항목 중 기업의 재무안정성과 관련된 항목을 신용평가모형에 반영하여 중소기업뿐만이 아닌 전체 기업을 대상으로 한 신용평가모형의 부도변별력을 높이기 위한 기술력 평가모형의 신용평가모형 내 내재화에 착안하여 시작되었다. 따라서 기술력 평가모형이 부채비율 기준의 고안정성 중소기업을 사전에 판별하는 데 적용될 수 있는지 검증하는 것을 목표로 한다. 대상 기업을 업종(제조업 vs. 비(非)제조업)과 업력(창업기업 vs. 비(非)창업기업)으로 구분하고, 3개년 동안 해당 군집의 평균 부채비율 1/2 이하를 달성한 기업에 대해 고안정성 중소기업으로 정의한 후, C5.0 기법을 적용하여 모형의 판별력을 검증하였다. 분석결과 소항목 수준에서는 업종과 업력에 따라 중요도 간 차이가 있지만, 중항목 수준에서는 기술개발역량이 고안정성 중소기업을 판별하는 중요변수로 도출되었으며, 기업의 업력에 따라 창업 초기에는 자금조달능력(수익창출능력을 고려한 자본구조, 자본비용 및 자금조달 방법의 다양성)이 미래 고안정성 중소기업 여부를 결정하는 중요변수이지만, 업력이 증가함에 따라 지속적인 성과를 가능하게 하는 기술개발 인프라가 재무안정성에 영향을 미치는 중요 변수로 변화한다는 결론을 도출하였다. 업종과 업력에 따른 모형의 분류 정확도는 71~91% 수준이며, 기술력 평가항목을 이용하여 고안정성 중소기업을 판별할 수 있다는 가능성을 확인하였다.

• Journal of Mechanical Science and Technology
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• 제18권6호
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• pp.1010-1018
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• 2004

This study presents the methodological aspects of combustion instability modeling and provides the numerical results of the model (sub-scale) combustion chamber, regarding geometrical dimensions and operating conditions, which are for determining the combustion stability boundaries using the model chamber. An approach to determine the stability limits and acoustic characteristics of injectors is described intensively. Procedures for extrapolation of the model operating parameters to the actual conditions are presented, which allow the hot-fire test data to be presented by parameters of the combustion chamber pressure and mixture (oxidizer/fuel) ratio, which are customary for designers. Tests with the model chamber, based on the suggested scaling method, are far more cost-effective than with the actual (full-scale) chamber and useful for injector screening at the initial stage of the combustor development in a viewpoint of combustion instabilities.

• 대한전기학회논문지
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• 제36권8호
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• pp.584-593
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• 1987

A new combined approximation method using Routh stability array and mean-square error (MSE) method is proposed for deriving reduced-order z-transter functions for discrete time systems. The Routh stability array is used to obtain the reduced-order denominator polynomial, and the numerator polynomial is obtained by minimizing the mean-square error between the unit step responses of the original system and reduced model. The advantages of the new combined approximation method are that the reduced model is always stable provided the original model is stable and the initial and steady-state characteristics of the original model can be preserved in the reduced model.