• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.464-466
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• 2011

This technical paper presents a new solid propellants family. The views are based on open literature and patents recently. Electrically controlled extinguishable solid propellants (ESCSP) are capable of multiple ignitions, extinguishments and throttle control by the application of electrical power. Both core and end burning no moving parts ECESP grains/motors to three inches in diameter have now been tested. Ongoing research has led to a newer family of even higher performance ECESP providing up to 10% higher Isp, manufacturing ease, and significantly higher electrical conduction.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.942-948
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• 2011

Solid propulsion systems have simple structures compared to other propulsion systems and are suitable for long-term storage. However the systems generally have limits on control of thrust levels. In this paper we introduce controllers for combustion chamber pressure using on-off control techniques which have been known for relatively easy implementation and energy efficiency. For this, we use a simple pressure change model by considering only mass conservation within the combustion chamber and we design a classical controllers and on-off controllers with are Pulse Width Modulation(PWM) and Pulse Width Pulse Frequency Modulation (PWPFM). Then we compare the performance results of the controllers through numerical simulations.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.167-174
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• 2011

Solid propulsion systems have simple structures compared to other propulsion systems and are suitable to long-term storage. However the systems generally have limits on control of thrust levels. In this paper we suggest control algorithms for combustion chamber pressure of variable thrust solid propulsion systems using special nozzles such as pintle valve. For this we use a simple pressure change model by considering only mass conservation within the combustion chamber, design a classical algorithm and also a nonlinear controller using feedback linearization technique. Derived thrust equation and designe a thrust control model. We design the proportion-integral controller for linearizing about operating point. We also demonstrate the performance of controller model through numerical simulations.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.105-108
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• 2008

Nowadays, as there is so much interest in environment, hydrogen peroxide attracts attention as an eco-propellant. Hydrogen peroxide is widely used for mono-propellant of thruster, and oxidizer of bi-propellant rocket. Especially, it is used as mono-propellant of the thruster for attitude control of satellite and military weapons. So, the need of long time storage of hydrogen peroxide appears and storage test is required. In this paper, necessity of storage test of hydrogen peroxide and some conditions and methods are introduced. In addition, the results of storage tests under some condition are compared and analyzed.

• Proceedings of the Korean Nuclear Society Conference
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• 1996.05c
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• pp.391-396
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• 1996

방사성폐기물관리시설의 부지 확보사업이 계속 난항을 겪자 정부는 부지확보와 그에 따른 지역개발사업을 촉진하기 위하여 방촉법을 제정하였다. 이를 근거로 '95년 2월 굴업도를 방사성폐기물 관리시설지구로 고시하고 시설지구 개발사업 및 주변지역지원사업계획을 수립, 사업을 추진하게 되었다. 시설지구의 토지매수업무 및 주변지역 지원사업을 법적절차에 따라 수행하던 중 '95년 10월 굴업도 주변에서 활성단층이 발견되고 12월 시설지구 지정고시가 해제되어 사업이 원점으로 돌아가게 되었다. 그동안 수행했던 굴업도 프로젝트의 사업추진경위를 살펴보고 추진과정에서 발생한 문제점들을 분석하여 신부지 확보시 고려되어야 할 부지확보절차, 지역지원사업 및 지역홍보 등의 개선방향을 제시하였다.

• Proceedings of the KIPE Conference
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• 2014.07a
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• pp.140-141
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• 2014

본 논문에서는 DC배전 전기추진 선박에서 전력품질 향상 및 전력 공급 안정성을 위한 리튬-이온 배터리 에너지 저장장치(BESS)를 적용하고 이에 대하여 기술한다. MATLAB/Simulink를 이용하여 DC배전 전기추진 선박 및 리튬-이온 배터리 에너지 저장장치의 시뮬레이션 모델을 구현하였으며, 구현된 시뮬레이션 모델에 발전 전력과 소비 전력 간의 전력 수급 차로 DC 계통의 전압 변동이 발생되는 추진전동기의 급격한 가, 감속 운전 시나리오를 적용하였다. 적용 시나리오에 의해 발생된 전압 맥동 현상은 리튬-이온 배터리 에너지 저장장치를 이용하여 IEEE STD. 1709 - 2010에서 제시하는 전압 허용 범위를 만족함으로써 DC배전을 갖는 전기추진 선박의 전력품질 향상 및 전력 공급의 안정성 여부를 검토한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.77-84
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• 2006

With the development of micro/nano spacecraft, concepts of micro propulsion are introduced for orbit transfer and drag compensation as well as attitude control. Micro solid propellant thruster has been attention as one of possible solution for micro thruster. In this paper, micro solid propellant thruster is introduced and research on basic components of a micro solid propellant thruster is reported. Micro Pt igniter was fabricated through negative patterning and quantitative effect of geometry was estimated. The characteristic of HTPB/AP solid propellant was investigated to measure the homing velocity. A combustion chamber was fabricated by means of anisotropic etching of photosensitive glass. Finally, micro solid propellant thrusters having various geometries were fabricated and tested.

• Journal of the Korean Society of Propulsion Engineers
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• v.9 no.4
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• pp.112-120
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• 2005

The solid propellants have been most widely used for the military rockets or missiles all over the world and the efforts have been focused on the enhancement of propellant performance up to 1980s. lately in company with the distinguished development in the intelligence and communication technology, the more accurate guidance as well as maneuverability has been required in the military weapon system. To meet the requirements such as a high maneuverability, insensitiveness, or stealth of missile, the researches have been doing to develop the solid propellants which have a quality of ultra-fast burning rate, insensitiveness, low signature or the like.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.17 no.9
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• pp.431-439
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• 2016

Urban regeneration projects involve various stakeholders, which result in decision making processes that require long periods of time and cause many conflicts. This study aims to identify important factors in decision making for promoting an urban regeneration project. The analysis results utilizing AHP are as follows: Firstly, the analysis results identify the main considerations in the process of promoting urban regeneration projects as residents' opinion(0.393), involvement of local government(0.231), opinions of related experts(0.206) and master plan(0.169). Secondly, the key drivers of stakeholders' qualitative decision making were found to include sustainability(0.325), economic feasibility(0.277), ease of project implementation(0.232) and equity(0.166). Lastly, meaningful differences in the relative importance of key aspects of decision making were identified when respondents were grouped according to being aware or not aware of the urban regeneration project, as well as living on or living off the project site. The results of this study can be used to implement successful urban regeneration projects in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.6-6
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• 2000

국가우주개발 중장기 계획에 의거, 독자 인공위성 발사체 개발에 필요한 필수기술을 확보하기 위하여 액체추진제 로켓엔진의 개발에 대한 필요성이 대두되었으며, 이에 따라 한국항공우주연구소는 과학로켓 3호(KSR-III)에 적용하기 위한 액체추진기관을 개발하고 있다. 이러한 목적으로 kerosine/LOx를 사용하며 13톤급의 추력을 낼 수 있는 시제엔진이 설계, 제작되었으며 이 엔진에 대한 연소시험이 실시되었다. 본 연구에서는 액체추진기관 시험을 위한 일련의 진행사항, 시험방법을 소개하며, 시험을 통하여 획득한 정특성 자료 및 동특성 자료에 대하여 분석하였다.(중략)