• 한국연소학회:학술대회논문집
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• 한국연소학회 2005년도 제31회 KOSCO SYMPOSIUM 논문집
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• pp.32-39
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• 2005

Recently, renewed interest on the scramjet engine has been demonstrated through the many international activities along the several Asia-Pacific countries. Here, a short review of current activities on supersonic combustion in a scramjet engine will be addressed followed by the discussions on the review of numerical simulation on supersonic combustion phenomena related with scramjet engine combustors and ram accelerator. Emphasis was put on the grid refinement, scheme, unsteadiness and phenomenological differences.

• 한국추진공학회지
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• 제4권2호
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• pp.21-30
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• 2000

본 연구에서는 램 가속기의 성능 향상을 위한 수치최적화를 수행하였다. 일정한 형상과 질량을 가진 탄체를 최초의 속도 $V_o$로부터 목표 속도 $V_e$로 가속시킬 때까지의 최소의 램 가속관 길이를 탐색하는 것을 목표로 하였고 $H_2$, $O_2$, $N_2$로 구성된 예 혼합기의 각 화학종의 몰수를 설계변수로서 채택하였다. 목적함수와 구속조건은 설계 과정에서 선형화 하여 구배법과 SLP기법을 적용하였다. 내부유동은 이차원 비점성 유동을 가정하고 화학반응의 해석은 8단계 7화학종 모델을 적용하였다. 가속관 길이의 결정을 위하여 램 가속관 내부의 유동은 준 정상상태로 가정하고 몇 개의 동일 구간으로 분할하여 각 속도에서의 추력 계수와 가속도를 동시에 구하여 전 속도 영역에 대하여 수치 적분하였다. 본 연구를 통하여 7회의 설계 반복으로 가속관의 길이를 19% 감소시켰다. 본 연구의 결과로부터 다단계, 다 화학종의 램 가속기의 설계최적화 문제에 직접적으로 적용할 수 있음을 확인하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 1997년도 제8회 학술강연회논문집
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• pp.43-51
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• 1997

Steady and unsteady numerical simulations are conducted for the experiments performed to investigate the ram accelerator flow field by using the expansion tube facility in Stanford University. Navier-Stokes equations for chemically reacting flows are analyzed by fully implicit and time accurate numerical methods with Jachimowski's detailed chemistry model for hydrogen-air combustion involving 9 species and 19 reaction steps. Although the steady state assumption shows a good agreement with the experimental schlieren and OH PLIF images for the case of $2H_2$+$O_2$+$17N_2$, it fails in reproducing the combustion region behind the shock intersection point shown in the case of $2H_2$+$O_2$+$12N_2$, mixture. Therefore, an unsteady numerical simulation is conducted for this case and the result shows all the detailed flow stabilization process. The experimental result is revealed to be an instantaneous result during the flow stabilization process. The combustion behind the shock intersection point is the result of a normal detonation formed by the intersection of strong oblique shocks that exist at early stage of the stabilization process. At final stage, the combustion region behind the shock intersection point disappears and the steady state result is retained. The time required for stabilization of the reacting flow in the model ram accelerator is found to be very long in comparison with the experimental test time.

• 한국연소학회지
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• 제5권1호
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• pp.31-41
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• 2000

A numerical study was conducted to investigate the combustion phenomena of regular start and unstart processes based on ISL#s RAMAC 30 experiments with different diluent amounts in a ram accelerator. The initial projectile launching speed was 1800m/s which corresponded to the superdetonative speed of the stoichiometric $H_2/O_2$ mixture diluted with $5CO_2\;or\;4CO_2$. In this study, it was found that neither shock nor viscous heating was sufficient to ignite the mixture at a low speed of 1800m/s, as was found in the experiments using a steel-covered projectile. However, we could succeed in igniting the mixtures by imposing a minimal amount of additional heat to the combustor section and simulate the regular start and unstart processes found in the experiments with an aluminum-covered projectile. The numerical results matched almost exactly to the experimental results. As a result, it was found that the regular start and unstart processes depended on the strength of gas mixture, development of shock-induced combustion wave stabilized by the first separation bubble, and its size and location.

• International Journal of Aeronautical and Space Sciences
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• 제17권3호
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• pp.358-365
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• 2016

In this study, one-dimensional analysis under the assumption of an inviscid flow was conducted for the experiment initiated by the French-German Research Institute of Saint-Louis (ISL) in order to investigate the energy effect of aluminum combustion. Previous theoretical analysis based on the assumptions of isentropic compression and a constant specific heat derived by ISL claimed that the experiment was not affected by the heat of aluminum combustion. However, rigorous analysis in present investigation that considered the average properties behind the shock wave compression and temperature-dependent specific heat showed that the S225 experiment was partially affected by the aluminum combustion. The increase in heat due to aluminum combustion was estimated from the rigorous analysis.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2000년도 춘계 학술대회논문집
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• pp.159-165
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• 2000

In this paper, numerical study has been done for the improvement of the superdetonative ram accelerator performance and for the design optimization of the system. The objective function to optimize the premixture composition is the ram tube length required to accelerate projectile from initial velocity $V_o$ to target velocity $V_e$. The premixture is composed of $H_2,\;O_2,\;N_2$ and the mole numbers of these species are selected at design variables. RSM(Response Surface Methodology) which is widely used for the complex optimization problems is selected as the optimization technique. In particular, to improve the non-linearity of the response and to consider the accuracy and efficiency of the solution, design space stretching technique has been applied. Separate sub-optimization routine is introduced to determine the stretching position and clustering parameters which construct the optimum regression model. Two step optimization technique has been applied to obtain the optimal system. With the application of stretching technique, we can perform system optimization with a small number of experimental points, and construct precise regression model for highly non-linear domain. The error to compared with analysis result is only $0.01\%$ and it is demonstrated that present method can be applied more practical design optimization problems with many design variables.

• 한국통신학회논문지
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• 제30권2B호
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• pp.1-10
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• 2005

빠른 데이터 처리를 위하여 기존에는 소프트웨어방식으로 구현되었던 TCP/IP를 고속의 하드웨어로 구현함에 있어, TCP/IP 하드웨어와 외부 블록간의 통신을 중계하는 블록인 Host Interface를 구현하였다. Host Interface는 TCP/IP 하드웨어와 외부 블록의 중간에 위치하여 외부 블록과의 통신을 위해 AMBA AHB 규약을 따른다. Host Interface는 내부의 Command/Status Register를 통하여 CPU와 TCP/IP 하드웨어 간의 명령, 상태, 헤더 정보 등을 전달하는데 이 때에는 AMBA AHB의 Slave로서 동작한다. Data Flow를 위해서 Host Interface는 AMBA AHB의 Master로서 동작하는데, 데이터 흐름의 방향에 따라 Data flow는 데이터를 수신하는 Receive flow와 데이터를 패킷으로 만들어 보내는 Transmit Flow로 나된다. Rx Flow의 경우, UDP 블록이나 TCP Buffer로부터 받은 데이터를 내부의 작은 RxFIFO를 통해 외부 RxRAM에 써서 CPU가 읽어갈 수 있도록 하고, Tx Flow의 경우에는 외부 TxRAM에서 전송할 데이터를 읽어 와서 TxFIFO를 거쳐 UDP Buffer나 TCP Buffer에 씀으로써 패킷을 만들어 보내도록 한다. 외부 RAM의 액세스에는 Command/Status Register에 위치한 Buffer Descriptor의 정보를 이용하게 된다. Host Interface는 이러한Data Flow의 원활한 흐름을 위해서 여러 세부 기능들을 수행하게 된다. Host Interface의 기능을 검증하기 위하여 여러 testcase들이 수행되었으며, 0.18 마이크론 기술을 사용하여 synthesis한 결과, 내부의 Command/Status Register와 FIFO를 모두 포함하여 약 173K 게이트가 소요됨을 보았다.

• 한국연소학회:학술대회논문집
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• 한국연소학회 2002년도 제24회 KOSCO SYMPOSIUM 논문집
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• pp.123-132
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• 2002

A numerical study was conducted to investigate the combustion phenomena of normal start and unstart processes based on ISL's RAMAC 30 experiments with different diluent amounts and fill pressures in a ram accelerator. The initial projectile launching speed was 1.8 km/s which corresponded to the superdetonative speed of the stoichiometric $H_2/O_2$ mixture diluted with 5 $CO_2$ or 4 $CO_2$. Experiments with same condition except for projectile surface material demonstrated that ignition was successful with an aluminum projectile, but no combustion was observed in case of a steel projectile. In this study, it was found that neither shock nor viscous heating was sufficient to ignite the mixture at a low speed of 1.8 km/s, as was found in the experiments using a steel projectile. However, we could succeed in igniting the mixtures by imposing a minimal amount of additional heat to the combustor section and simulate the normal start and unstart processes found in the experiments with an aluminum projectile. For the numerical simulation of supersonic combustion, multi-species Navier-Stokes equations coupled with a Baldwin-Lomax turbulence model and detailed chemistry reaction equations of $H_2/O_2/CO_2$ suitable for high-pressure gaseous combustion were considered. The governing equations were discretized by a high order accurate upwind scheme and solved in a fully coupled manner with a fully implicit, time accurate integration method. The numerical results matched almost exactly to the experimental results. As a result, it was found that the normal start and unstart processes depended on the strength of gas mixture, development of shock-induced combustion wave stabilized by the first separation bubble, and its size and location.

• 한국연소학회지
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• 제1권1호
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• pp.83-91
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• 1996

A numerical study is carried out to examine the ignition and propagation process of detonation wave in SCRam-accelerator operating in superdetonative mode. The time accurate solution of Reynolds averaged Navier-Stokes equations for chemically reacting flow is obtained by using the fully implicit numerical method and the higher order upwind scheme. As a result, it is clarified that the ignition process has its origin to the hot temperature region caused by shock-boundary layer interaction at the shoulder of projectile. After the ignition, the oblique detonation wave is generated and propagates toward the inlet while constructing complex shock-shock interaction and shock-boundary layer interaction. Finally, a standing oblique detonation wave is formed at the conical ramp.

• 한국정보통신학회논문지
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• 제23권12호
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• pp.1609-1617
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• 2019

ECC (Elliptic Curve Cryptography)와 RSA를 기반으로 하는 다양한 공개키 암호 프로토콜 구현을 지원하는 하드웨어 가속기 설계에 관해 기술한다. NIST 표준으로 정의된 소수체 상의 5가지 타원곡선과 3가지 키길이의 RSA를 지원하며 또한, 4가지 타원곡선 점 연산과 6가지 모듈러 연산을 지원하도록 설계되어 ECC와 RSA 기반 다양한 공개키 암호 프로토콜의 하드웨어 구현에 응용될 수 있다. 저면적 구현을 위해 내부 유한체 연산회로는 32 비트의 데이터 패스로 설계되었으며, 워드 기반 몽고메리 곱셈 알고리듬, 타원곡선 점 연산을 위해서는 자코비안 좌표계, 그리고 모듈러 곱의 역원 연산을 위해서는 페르마 소정리를 적용하였다. 설계된 하드웨어 가속기를 FPGA 디바이스에 구현하여 EC-DH 키교환 프로토콜과 RSA 암호·복호 둥작을 구현하여 하드웨어 동작을 검증하였다. 180-nm CMOS 표준 셀 라이브러리로 합성한 결과, 50 MHz 클록 주파수에서 20,800 등가게이트와 28 kbit의 RAM으로 구현되었으며, Virtex-5 FPGA 디바이스에서 1,503 슬라이스와 2개의 BRAM으로 구현되었다.