• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.69-75
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• 2009

This paper studies the aerodynamic performance that the vent mixer-new conceptual supersonic mixer-showed with its geometric characteristics. The hole is 2 mm with 2 mm's distance from the wall in case 1 and with no distance in case 2. In case 3 die hole is 1 mm. Case 1 and case 2 showed the same total pressure recovery ratio, of which the case 3 was lower than that. While cases 1-3 had the same reattachment length, the shear layer was thicker in cases 1 and 2 than in case 3. Within the recirculation zone, cases 1 and 2 had lower pressure loss and higher velocity gradient difference than case 3-they enhance mixing between air and fuel. Separation bubble which is developed by the inflow into the recirculation zone has a significant effect on the total pressure recovery ratio in the combustor. Also separation bubble influences pressure distributions and recirculation flows in the recirculation zone. Therefore, inflow rate of air into the recirculation zone mainly affects the performance of vent mixer.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.12
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• pp.1031-1038
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• 2017

In order to improve the performance of the air breathing engines, it is important to maximize the total pressure recovery through air intake. In this study, we investigated whether the Oswatitsch method, which guarantees the maximum pressure recovery for supersonic intake, is effective at hypersonic speed by compressing the intake air with the same intensity at each ramp. The non-linearity of the shock wave normal Mach number at each ramp stage was analyzed by comparing the compression ramp angle and the number of ramp to the inflow Mach number in terms of compressible thermodynamics and the operation limits of the inlet. Based on this analysis, the Oswaitisch technique yields valid conditions not only in supersonic but also hypersonic flight regime.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.10
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• pp.68-74
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• 2005

Optimal shape of a typical ramjet intake is examined numerically to maximize the total pressure recovery. A response surface method is introduced to approximately predict its performance with respect to the design parameters over the each design domain. The first deflection angle of ramp, the area of inlet throat, and the diffuser angle are chosen as a design parameter. ANOVA is used to verify the trustability of the achieved response surface. The total pressure recovery of the optimum model, compared to that of the base model, is increased by 36%. The loss of viscosity through the diffuser is estimated less than 5%.

• Proceedings of the KIPE Conference
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• 2008.06a
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• pp.203-205
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• 2008

기존의 부스트 컨버터에서는 출력 전압이 커질수록 스위치의 전압 및 전류스트레스가 커지고 다이오드 역방향회복에 의한 서지로 인해 실제 사용 가능한 승압비가 제한된다. 본 논문에서는 높은 승압을 요구하는 대전력 응용에도 적합한 새로운 비절연 DC-DC 컨버터를 제안한다. 제안한 컨버터는 듀티비 0.5로 약 6배의 승압비를 가지며 CCM에서도 영전압 스위칭이 가능하다. 또한 스위치 및 다이오드 전압정격이 출력전압의 1/3로 되고 인터리빙이 가능하여 입출력 수동소자의 정격도 작다. 다이오드도 ZCS 턴오프 동작으로 역방향 회복에 의한 서지가 없다. 제안하는 컨버터의 동작원리를 설명하였고 이론적 해석과 시뮬레이션 및 실험파형을 통해 타당성을 검증하였다.

• Proceedings of the KIEE Conference
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• summer
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• pp.76-78
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• 2004

본 논문에서는 전력시스템에서 상정 사고로 인해서 부하가 급변할 때 계통의 신뢰도를 유지하기 위해서 발전 모선의 전압을 조절하여 부하 모선의 전압을 정상상태의 범위에서 유지시키기 위한 알고리즘을 구조개편 후 비상시에 취할 수 있는 중요한 조치 중 하나로서 재조명한파. 이에 먼저 전력 계통의 상태를 발전기의 예비력을 기준으로 정상상태와 비상상태로 나누고, 계통에서 발생한 상정사고에 대하여 발전 모선의 전압변동을 통해서 부하 모선의 전압을 정상상태의 범위에서 유지하도록 한다. 하지만 심각한 상정사고가 발생하여 발전기의 출력이 정상상태의 예비력 기준을 초과하여 발전을 해야만 하는 상황이면, 이를 계통의 비상상태로 선언하고, 이를 다시 정상상태로 회복시킬 수 있도록 하는 새로운 알고리즘을 제안하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.3
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• pp.38-48
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• 2005

For the development of Scramjet engine technology, intake designing processes are investigated. The basic geometry is determined by the inviuld relation such as shock wave relations and geometric relations. Furthermore, bleed duct is installed for preventing boundary layer development and shock wave impingement. Performance of the designed intake is validated by numerical analysis. As a result, double- wedge intake showed better characteristics in total pressure recovery than single-wedge intake.

• Journal of the Korean Society of Propulsion Engineers
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• v.6 no.2
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• pp.65-74
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• 2002

Optimal supersonic diffuser shape of integrated rocket ramjet engine was derived which maximizes the total pressure recovery. Mass flux is considered as a design constraint and the second oblique shock angle of the external ramp, the cowl-lip angle and the throat area are selected as design variables. Refined response surface method through design space transformation technique was developed and employed, and high confidence level of the regression model could be obtained. Genetic algorithm was implemented for both system optimizer and subspace regression model optimization. Virtual nozzle was located at the end of throat to adjust the back pressure. With only 20 aerodynamic analyses, optimal supersonic diffuser shape which has 14% improved total pressure recovery characteristics was successfully designed.

• Proceedings of the KIEE Conference
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• 2009.07a
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• pp.87_88
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• 2009

계통의 전압 불안정 현상은 다양한 무효전력 공급 설비를 통해 회복될 수 있다. 발전기를 통한 무효전력 공급은 유효전력 출력의 저감으로 이어질 수 있으며, 여기서 기회비용의 발생 가능성이 존재한다. 또한 상정사고가 발생하면 계통의 전압을 안정한 상태로 유지하기 위해 발전기의 적정 무효전력 예비력을 확보하는 것이 필요하다. 하지만 현재 국내에서는 발전사업자가 적정한 무효전력 예비력을 확보하고, 계통의 전압이 떨어지는 경우에 무효전력을 공급하여 안정된 전압을 유지하는 무효전력 보조서비스 제도가 없는 실정이다. 본 연구는 무효전력 보조서비스 제도 도입 준비의 일환으로 발전기의 무효전력 공급에 대한 부하 모선의 민감도를 분석하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.4
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• pp.10-20
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• 2022

The performance analysis test of the scramjet engine intake was conducted under the Mach 5 condition of the scramjet engine test facility, a free-jet ground test facility of the Korea Aerospace Research Institute. A pitot/static pressure rake installed at the rear of the isolator was designed and manufactured to measure the total pressure recovery rate and mass capture ratio, which are typical performance factors of the scramjet engine intake. The effect of the rake mounted at the rear of the isolator on the intake, the performance analysis measured by the rake, and the change in wall static pressure distribution according to the angle of attack were performed. Finally, the point at which the intake unstart occurred was confirmed by using the rear back pressure adjusting device, which simulates pressure rise in the combustor, and the results are summarized in this paper.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.6
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• pp.16-27
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• 2020

For the operation of the scramjet engine in the wide flight range, the design of the inlet must show stable performance in various flight conditions. In this study, the design methods of a 2D fixed inlet for stable performance in wide flight ranges of Mach number 4 to 6 and angle -6° to 6°, is performed. After proposing the design method and design focus, performance prediction and analysis were performed by various initial compression angles and design Mach numbers, which are essential design factors in total pressure recovery and inlet capture area ratio in the wide flight range. Based on the analysis results, we present the selection criteria for the two main design elements to represent stable performance in the wide flight range.