• Bulletin of the Korean Space Science Society
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• 2010.04a
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• pp.28.1-28.1
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• 2010

이 연구에서는 기존 선형 상대운동방정식에 차등중력, 주위성의 이심율, J2 섭동 등의 비선형항을 추가하여 보다 정확한 상대운동방정식을 만든 후 섭동이론을 적용하여 위성편대 연료최적화 재배치 문제에 대한 근사 해석해를 구하고자 한다. 먼저, 비선형 섭동항을 테일러 급수를 이용하여 2차항까지 전개한 후, 이를 기존 선형상대운동방정식에 추가하여 새로운 비선형 상대운동방정식을 만든다. 이 때 사용된 선형상대운동방정식은 힐스 방정식으로 주위성의 궤도가 일반적인 타원이고 위성 간 상대거리가 충분히 가깝다고 가정한다. 최적화 조건으로부터 상태벡터와 라그랑지 곱수로 이루어진 연립 미분방정식이 만들어 지는데, 이 식은 힐스 방정식에 기인한 선형부분과 2차 비선형항에 기인한 섭동부분으로 나뉜다. 이 때, 이 연립미분방정식의 해는 선형부분의 해와 섭동으로 인한 변화량의 합으로 근사할 수 있으며 그 변화량은 섭동이론을 적용하여 얻을 수 있다. 이와 같이 얻어진 해는 여러 섭동의 비선형항을 2차까지 포함한 상대운동방정식을 사용했기 때문에, 기존 선형상대운동방정식을 사용하여 구한 최적해 보다 더 정확한 결과를 얻을 것이라 예상한다.

• Proceedings of the Korean Nuclear Society Conference
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• 1998.05b
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• pp.929-934
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• 1998

KT(KAERI Tokamak) 장치의 언저리 영역에서 삼중정전탐침을 이용하여 플라즈마밀도, 전자온도 및 부유(floating)전압을 측정하였다. 토카막 방전조건에 따라 고정된 위치에서의 측정값들은 시간에 대한 변화를 보였다. 특히 플라즈마 밀도 값 <η$_{e}$>은 약 두 배까지의 시간에 따른 변화 폭을 보였다. 반면에 밀도 섭동량(fluctuation) $\delta$η$_{e}$/<η$_{e}$>은 다른 섭동량과 마찬가지로 거의 일정한 값을 나타냈다. z 방향에 대해 측정한 proafile 결과는 모두 z/a에 따라 감소하였으며, 반면에 섭동량은 증가하는 경향을 나타냈다. 부유전압 및 압력구매에 의하여 발생되는 poloidal 방향의 drift속도를 profile 결과로부터 얻었으며, 언저리 영역에서 섭동량은 이온 diamagnetic 방향으로 최대 + 2 $\times$$10^{5}$ cm/sec의 속도로 이동함을 예상할 수 있었다 섭동량 자체에 의해 유기되는 전기장 \ulcorner(equation omitted) 로부터, 반경방향으로 이동되는 속도는 측정한 부유전압의 섭동량에 대한 z 방향 profile로부터 언저리 영역에서 $\upsilon$$_{r}$가 최대 + 1.2 $\times$ $10^{5}$ cm/sec가 됨을 알 수 있었다. 언저리 영역에서 섭동량이 장치 벽쪽으로 이동하는 정도를 진행 속도 값으로부터 예상할 수 있었다.있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.05a
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• pp.94-97
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• 2003

The effect of pressure perturbation in the ramjet engine on the characteristics of the inlet is studied via numerical simulation. The frequency and amplitude of the pressure perturbation are assumed to be 500Hz and 20% of the exit back pressure, respectively. The simulation shows the characteristics of the normal shock in the inlet according to the pressure perturbations. The relation between the captured mass flow rate and downstream pressure perturbation is studied. The mass flow rate decreases when the downstream pressure perturbation starts.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.28-30
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• 2012

A mechanical pulsator is manufactured for study of combustion instabilities in a model chamber with impinging-jet injectors. Artificial disturbance is generated by the device and thereby, artificial instability can be examined experimentally. A sample F(fuel)-O(dxidizer)-O-F impinging-jet injector is adopted for the test. The model chamber was designed based on the methodologies proposed in the previous work regarding geometrical dimensions and operating conditions. Pressure fluctuation data, which is obtained from the dynamic pressure transducers installed in combustion chamber, is analyzed.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.36 no.9
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• pp.907-913
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• 2012

High-order perturbation solutions have been obtained for the simple physical model describing the liquid pool spreading with a continuous spill, and these are shown to improve over first-order perturbation solutions. The non-dimensional governing equations for the model are derived to obtain more general solutions. Non-dimensional parameters are sought as the governing parameters for the non-dimensional equations, and the non-dimensional evaporation rate is used as the perturbation parameter. The results show that the high-order solutions exhibit an improvement over the first-order solutions with respect to the pool volume as well as the spreading radius. In addition, as the order of the perturbation solutions increases, the difference between the numerical solutions and the perturbation solutions is significantly reduced. Finally, it is revealed that the third-order solutions are reasonable because they almost agree with the numerical solutions.

• The Journal of the Acoustical Society of Korea
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• v.43 no.1
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• pp.131-137
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• 2024

Aerodynamic noise generated by the surrounding flow of a train traveling at high speed affects both outdoor and indoor noise. This study's goal is to develop a test method to measure and quantitatively evaluate aerodynamic noise through pressure perturbation data on the train surface. To accurately evaluate aerodynamic noise, it is important to separate and evaluate the compressive and incompressible pressure fluctuations mixed in the acquired surface pressure fluctuation data. This is because the noise transmission characteristics of the two pressure fluctuations are different. First, the installation length and interval of the microphone were determined to acquire surface pressure fluctuation data, and wavenumber-frequency analysis was performed to separate incompressible pressure fluctuation and compressible pressure fluctuation to obtain a sound pressure level spectrum. Finally, as a result of comparing the test results measured in the train head and trail, It was confirmed that the pressure fluctuation on the train head surface was greater than that on the tail.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.2
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• pp.19-28
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• 2010

Generally, combustion instability is generated by the mutual coupling between the heat release and the acoustic pressure in the combustor. On the occasion, the acoustic pressure generates the oscillation of the mass flow rate of propellant injected from injector, and this oscillation again affects combustion in the combustor. So, the dynamic characteristics of the injector have been studied to control combustion instability using injector itself in Russia from 1970's. In order to study injector dynamics, a mechanical pulsator for forced pressure pulsation is produced and the method to quantify the mass flow rate of the propellant that is oscillating at the exit of the injector is developed. With the pulsator and the method, pulsating values of the mass flow rate, pressure, liquid film thickness, and axial velocity generated at the exit of the simplex swirl injector are measured in real time. And phase-amplitude characteristics of each parameter are analyzed using these pulsating values acquired at the exit of the simplex swirl injector.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.23 no.12
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• pp.1638-1643
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• 2019

In this paper, we propose an adaptive-perturbation-aided opportunistic precoding (APOP) scheme for multiple-input multiple-output (MIMO) systems. To update a precoding matrix in MIMO systems, the proposed algorithm produces a random perturbation in each time slot. Then the additional adaptive perturbation is also applied, which depends on the reports of achievable data-rates from users. If the prior random perturbation increased the data rate, the adaptive perturbation is set to be the same as the prior random perturbation, otherwise the negative value of the prior random perturbation is applied for adaptive perturbation. Furthermore, to enhance the achievable data rates, the information on the stored precoding matrices in the memory as well as the currently generated precoding matrix is used for scheduling. Simulation results show that compared to conventional opportunistic precoding schemes, higher data rates are achieved by the proposed APOP scheme, especially when there are a relatively small number of users.

• Communications of the Korean Mathematical Society
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• v.18 no.4
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• pp.587-602
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• 2003

본 논문에서는 벡터값을 가지는 함수로 이루어진 벡터 변분 부등식들의 해집합사이의 관계, 미분 불가능한 볼록함수로 이루어진 벡터 볼록 최적화 문제의 해집합들과 볼록함수의 아래미분으로 표현된 벡터 변분부등식의 해집합들과의 관계, 제약집합이 볼록 함수로 구체적으로 주어질 때의 벡터 변분부등식의 해가 될 필요 충분조건, 섭동된 강 단조 벡터 변분부등식의 안정성 결과와 섭동된 벡터 강 볼록 최적화문제에의 적용에 대한 최근 연구 결과를 정리한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2003.10a
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• pp.65-70
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• 2003

In this work variations of orbital parameters are first derived from the perturbation equations using difference equation method under Earth oblateness and atmospheric drag. A simple and effective scheme is proposed to compute the required delta v and fuel consumption to compensate for atmospheric drag. The scheme is applied to KOMPSAT example. And by means of numerical simulations we quantitatively analyze influences due to each perturbation source, i.e., nonspherical Earth, atmospheric drag, third body gravities (Sun, Moon), and solar radiation.