• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.74-77
• /
• 2011

A mixing characteristics on recess length change of Gas-centered swirl coaxial injector using high-performance staged combustion rocket engine carry out study through CFD(Computational fluid dynamics). propellant phase that combined gas-liquid simulate gas-gas. In order to measure spreading angle, velocity distribution to injector exit and spray structure of propellant analyzed. Axial velocity increase by increasing recess length, but tangential velocity decrease. The result confirmed qualitative characteristics that the spreading angle decreases.

• 한국신재생에너지학회:학술대회논문집
• /
• 2007.11a
• /
• pp.637-641
• /
• 2007

화석연료의 고갈이 가시화됨에 따라 이를 해결하기 위한 대체에너지원의 확보를 위해 다양한 연구가 수행되어 왔다. 본 연구에서는 폐기물 특히 플라스틱 폐기물의 안정적인 처리 및 청정가스의 생산방법을 연구하기 위해서 선행적으로 플라스틱 폐기물의 열분해 특성을 조사하였으며, 그 반응모델을 제시하여 열분해로의 설계인자의 도출하고자 하였다. 대상 폐 플라스틱류로서 PE, PP, PVC, RPF 등을 이용하였고, 열중량분석기와 tube furnace를 통해서 온도에 따른 분해반응 특성을 확인하였다. 열분해 특성조사를 한 결과 PE, PP 등은 잔류 char가 없이 $400^{\circ}C$ 전후에서 완전 분해하였으며, PVC의 경우 $400^{\circ}C$ 이후에도 약 20% 이상의 char가 잔류함을 확인하였고, RPF의 경우에도 약 10%의 char이 잔류함을 확인하였다. 또한 각각의 열분해 특성을 DTG/TGA분석을 통해서 적정체류시간을 구할 수 있었고, 다단열분해 가스화기를 이용하여 합성가스를 제조한 결과 2500 kcal / $Nm^3$의 높은 발열량을 가진 합성가스를 제조할 수 있었다.

• Journal of ILASS-Korea
• /
• v.17 no.1
• /
• pp.1-8
• /
• 2012

This study described the effect of the multiple injections and diesel-ethanol on the NVH, combustion and emission characteristics of 4 cylinder common rail diesel engine. In order to investigate the influence of diesel-ethanol blended fuel in a light-duty common rail diesel engine, the injection strategy was varied with pilot injection, double pilot injections, and one main injection at various operating conditions. The results showed that diesel-ethanol blended fuel had longer ignition delay than that of the ultra low diesel fuel(ULSD). Also, in the case of multiple injections, the combustion pressure is increased smoothly near the TDC and the NVH are decreased. In the emission characteristics, diesel-ethanol blended fuel produced lower indicated specific nitrogen oxides(IS-NOX) and indicated specific Soot(IS-soot) emissions, however, indicated specific unburned hydrocarbon(IS-HC) and indicated specific carbon monoxide(IS-CO) emissions are slightly increased.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.153.1-153.1
• /
• 2012

조립 후 발사대로 이송된 추진기관(또는 발사체)는 지상시험 및 비행시험을 위한 충전을 하게 되는데, 추진제 및 고압가스 등 추진기관 구성품의 운용절차는 하드웨어의 설계 단계에서 그 개념이 수립되어야 한다. 다시 말해, 발사체 및 추진기관 설계 단계에서 연료와 산화제의 충전/배출, 시험 취소시의 운용절차 개념이 수립되어 있어야 추진기관 구성품들의 설계, 지상인터페이스 구성품의 설계에 그 내용이 반영될 수 있다. 따라서, 본 논문에서는 발사체 및 추진기관 운용와 관련된 일반적인 충전/배출 절차와 지연 또는 취소시의 작업절차의 주요개념을 다루었고, 추진기관 운용에 필요한 각종 지상설비에 요구되는 주요 기능을 검토하였다. 또한, 추진제 충전 이후 발사 대기시까지의 업무와 발사 전에 수행되어야 하는 추진기관 운용 업무(Pre-Launch Operation)도 다루었다. 특히 다단 발사체의 경우에는 운용과 관련된 준비 업무량이 단수에 비례하여 늘어나므로, 효율적으로 모든 시험 준비 업무를 마치기 위해, 지상에서의 추진기관 운용절차는 각 단별로 유기적으로 진행되어야 한다. 즉, 각 단별 하드웨어에 대한 사전 검사, 충전, 대기 등의 운용시간 설계 및 그 절차가 중요하다. 한국형 발사체 및 추진기관의 운용 개념설계를 수행하는데에는 기 확보된 운용기술을 활용하였다.

• Journal of Korea Society of Industrial Information Systems
• /
• v.22 no.5
• /
• pp.39-49
• /
• 2017

A Space Launch Vehicle (SLV) for Launching Satellites Consists of Multi-stage Rockets for the Purpose of Efficient Flight and Accomplishes the Launch Mission through Flight Events such as Stage Separation, Engine Start and Stop. In this Process, the SLV is Supposed to Undergo the Processes of the Powered Flight Section in which the Engine Generates Thrust and the Ballistic Flight Section in which there is no Thrust Repeatedly. Because it is Difficult to Express these Flight Characteristics of the SLV as a Single Dynamics Model, much Research on Tracking Algorithms using Multiple Models has been Undertaken. In case of using the Multiple Model Tracking Algorithm, it is Expected to Improve the Tracking Performance of the SLV. However, it is Difficult to Select Proper Dynamics Models to be used and the Calculation Amount Increases due to the use of Multiple Models. In this Paper, we Propose a Method to Track the SLV with Diverse Flight Characteristics Efficiently by only Two Kalman Filters using Constant Acceleration Model and Adaptive Singer Model.

• Journal of Advanced Navigation Technology
• /
• v.18 no.2
• /
• pp.165-169
• /
• 2014

Digital load is increasing suddenly for various reasons, such as easy control and management. Accordingly, a consumption pattern of load is becoming DC. However, the power supply is supplied by AC power. The load power supply substantially needs DC power. AC power has to be converted to DC power. Renewable energy sources like solar, wind, fuel cells are DC power generation, but the transfer needs to through by AC power, thus DC power has to be converted to AC power. Resultantly, a multi-stage conversion loss is constantly increasing. The power distribution system of DC-based is required for effective use of these energy sources. This requires a DC load, as well as is necessary to develop DC ELCB which are able to detect DC leakage current for implementing protection. In this study, it realize detection algorithm about DC leakage current to verify the performance of the sensor and apply it to the ELCB which is based on DC. Therefore, it is expected to protect operating of DC power distribution system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.629-634
• /
• 2011

A prestudy on expendable turbine engine for high-speed vehicle was conducted. The two possible mission profiles were established to decide the engine requirements and Design Point, and Design Point analysis was performed with the values of design parameter which were obtained from similar class engines and technical references. The results showed that Specific Net Thrust is 2599.4 ft/s and Specific Fuel Consumption is 1.483 lb/($lb^*h$) at the flight condition of Sea Level, Mach 1.2. It was also found through the performance analysis on the two possible mission profiles that major design parameters for determining Net Thrust were Turbine Inlet Temperature for low supersonic flight speed and Compressor Exit Temperature for high supersonic flight speed. In addition, simple turbojet engine with axial compressor, straight annular combustor, axial turbine and fixed throat area converge-diverge exhaust nozzle was proposed as the configuration of simple low cost light engine.

• Journal of Advanced Navigation Technology
• /
• v.19 no.3
• /
• pp.250-256
• /
• 2015

Digital load is increasing suddenly for various reasons, such as easy control and management. Accordingly, a consumption pattern of load is becoming DC. However, the power supply is supplied by AC power. The load power supply substantially needs DC power. AC power has to be converted to DC power. Renewable energy sources like solar, wind and fuel cells are DC power generation, but the transfer needs to through by AC power, thus DC power has to be converted to AC power. Resultantly, a multi-stage conversion loss is constantly increasing. The power distribution system of DC-based is required for effective use of these energy sources. This requires a DC load, as well as is necessary to develop DC breaker. This study is expect for system and equipment for reliable DC power distribution through the study of the arc extinguish technology for direct current a hybrid arc extinguishing technology with permanent magnets technology.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.17 no.1
• /
• pp.97-102
• /
• 2013

A prestudy on expendable turbine engine for high-speed vehicle was conducted. After two possible mission profiles were established to decide the engine requirements, design point analysis was performed with the values of design parameter which were obtained from similar class engines, references, etc. The results showed that specific net thrust and specific fuel consumption with turbine inlet temperature of 3,600 R are 2,599.4 ft/s and 1.483 lb/(lb*h) respectively at the flight condition of sea level, Mach 1.2. It was also found that major design parameters for determining maximum net thrust were turbine inlet temperature for low supersonic and transonic flight speed and compressor exit temperature for high supersonic flight speed from the results of performance analysis on the two possible mission profiles. In addition, simple turbojet engine with an axial compressor, a straight annular combustor, an one stage axial turbine and a fixed throat area converge-diverge exhaust nozzle was proposed as the configuration of simple low cost lightweight turbine engine.

• Journal of Korean Society of Environmental Engineers
• /
• v.36 no.2
• /
• pp.147-152
• /
• 2014

In this research, polysulfone hollow fiber membrane was used to recover $CO_2$ which is one of greenhouse gases from flue gas stream being emitted after the combustion of fossil fuels. The prerequisite requirement is to design the membrane process producing high-purity $CO_2$ from flue gas. For separation of $CO_2$, a membrane module and flue gas containing 10% carbon dioxide was used. The effects of operating conditions such as pressure, temperature, feed gas composition and multi-stage membrane on separation performance were examined at various stage cuts. Higher operating pressure and temperature increased carbon dioxide concentration and recovery ratio in permeate. Recovery ratio and separation efficiency increased if a higher content of $CO_2$ injection gas composition. Three-stage membrane system was producing a 95% $CO_2$ with 90% recovery from flue gas. The separation efficiency of three-stage membrane system was higher than one-stage system.