• Fire Science and Engineering
• /
• v.18 no.3
• /
• pp.103-107
• /
• 2004

Recently. the spark and the overheat due to in the conductor breaks have been the major causes of electrical fire in low voltage wiring. Also, because in these cases the current is a surge one, the losses and faults of a communication, a home appliances, a computer and a measuring instrument may occur. Especially, in such cases, we are very difficult to detect the condition of the conductor breaks. In this paper, we have developed an auxiliary control device, the electrical fire prevention control device (EFPCD), of an earth leakage breaker (ELB). And we can prevent the electrical fire caused by the spark and the overheat occurring in the conductor breaks with the EFPCD.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.2 no.3
• /
• pp.80-89
• /
• 1998

Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.158.1-158.1
• /
• 2012

위성비행소프트웨어는 위성의 하드웨어와 임무 탑재체 및 서브시스템이 통합되어 궤도상에서 위성임무를 수행할 수 있도록 원격명령 및 측정데이터의 처리, 자세 및 궤도제어, 열제어, 전력제어 등의 기능을 수행한다. 위성비행소프트웨어의 개발과 같이 규모가 큰 소프트웨어는 여러 개발자가 참여해야 하고 각각의 개발자들이 작성 코드를 통합하여 빌드하고 문제 발생 시 대처하기 위하여 세부적인 설계 및 개발내용을 단계별로 문서화하는 작업이 수반되어야 한다. 기존의 위성비행소프트웨어 개발과정에서는 이러한 문서들 중 전체 위성비행소프트웨어의 단위 코드별 입출력, 수행기능 등의 상세 설계 내용을 기록하는 SDD(Software Design Description)는 개발자가 작성한 코드를 기반으로 수작업을 통하여 작성되었다. 이러한 작성방식은 작성자의 입력오류가 발생할 수도 있으며 소프트웨어 개발과 별도로 수작업이 요구되어 문서작성에 소요되는 시간적 손해가 발생하게 된다. 유럽에서는 이러한 문제점을 보완하기 위하여 C, C++, C#, JAVA, VHDL 등 다양한 언어를 사용하는 소프트웨어 개발에 적용 가능한 자동적 문서작성 도구인 Doxygen이 널리 활용되고 있다. Doxygen은 PDF, HTML, Latex, RTF 등 다양한 출력 포맷도 지원한다. 본 논문에서는 Doxygen을 활용하여 위성비행소프트웨어 개발문서의 작성 시 소요시간을 단축하고 소스코드로부터 해당 설계 내용을 추출하여 자동적으로 문서를 작성할 수 있는 방안에 대하여 소개한다.

• Journal of the Korean Institute of Illuminating and Electrical Installation Engineers
• /
• v.18 no.6
• /
• pp.128-135
• /
• 2004

The author present a modified multi-loop algorithm including feedforward for controlling a 55kW step down chopper in the power supply of Maglev. The control law for the duty cycle consists of three terms. The first is the feedforward term. which compensates for variations in the input voltaga. The second term consists of the difference between the slowly moving inductor current and output current. The third term consists of proportional and integral terms involving the perturbation in the output voltage. This perturvation is derived by subtracting the desired output voltage from the actual output voltage. The proportional and integral action stabilizes the system and minimizes output voltage error. In order to verify the validity of the proposed multi-loop controller, simulation study was tried using Matlab simulink

• Journal of the Korean Society of Propulsion Engineers
• /
• v.4 no.4
• /
• pp.107-113
• /
• 2000

Design configuration and performance requirements for KOMPSAT-1 propulsion system were described. Operational results of the propulsion system obtained through the satellite Launch and Early Operation Phase were scrutinized. Performance characteristics of the thrusters which are employed for spacecraft attitude control and the corresponding propellant depletion rate were analysed according to satellite operation modes. Additionally, propellant leakproof and thermal control capability were checked out from the view point of system verification. Propellant depletion rates calculated by PVT method in $\Delta$V maneuvering and each attitude control mode produce the very meaningful results for the prediction of total propellant consumption up to the end of satellite mission life.

• Proceedings of the Korean Institute of Communication Sciences Conference
• /
• 1994.06a
• /
• pp.418-421
• /
• 1994

• Magazine of the Korea Concrete Institute
• /
• v.13 no.6
• /
• pp.60-66
• /
• 2001

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2003.10a
• /
• pp.261-261
• /
• 2003

• Proceedings of the Korean Society of Precision Engineering Conference
• /
• 2003.10a
• /
• pp.110-110
• /
• 2003

• Proceedings of the Korean Vacuum Society Conference
• /
• 2002.06a
• /
• pp.113-113
• /
• 2002