• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.188.1-188.1
• /
• 2012

인공위성에 사용되는 배터리 기술은 1960년대 최초로 사용된 니켈 카드뮴(NiCd)을 시작으로 발전하기 시작해서 현재는 리튬-이온(Li-Ion)에 이르렀다. 리튬-이온 배터리는 높은 Energy Density(작은 크기와 무게), 낮은 자가 방전율을 가짐과 동시에 메모리 효과가 거의 없다는 장점이 있다. 하지만 리튬-이온 배터리 팩의 성능(Voltage, Capacity, Lifetime)은 사용된 Cell간 특성차이(State of Charge, Total Capacity Difference, Internal Impedance)에 의해 제한된다. 일반적으로 배터리는 원하는 전압과 용량을 확보하기 위해 직렬-병렬 혹은 병렬-직렬 구조를 가지는 팩 형태로 제작 된다. Cell간 특성차이가 존재하는 상태에서 배터리 팩을 사용할 경우 특정 Cell의 과충전 및 과방전이 발생하며 이로 인해 수명이 단축될 수 있고 심한 경우 폭발이 발생할 수 도 있다. 또한 Cell간 특성차이는 배터리팩의 사용가능 용량을 제한하는 효과를 가져 온다. 본 논문에서는 Battery 팩을 구성하는 Cell들에 특성 차이가 존재할 경우 발생할 수 있는 Battery 팩의 수명 단축 및 용량 감소 Mechanism에 대해서 고찰한다. 또한 Cell간 특성차이를 극복하기 위해 실제 위성 운용에 적용될 수 있는 배터리팩의 Balancing 방안과 함께 위성에 장착을 위해 보관중인 4p12s Battery의 Balancing 방안에 대해 고찰하고 Balancing 전후의 Cell간 특성(Voltage Dispersion) 차이 측정결과를 보인다. 이렇게 본 논문에서 소개한 리튬-이온 배터리의 전반적인 Balancing 방안은 추후 인공위성에 적용되는 리튬-이온 배터리의 운용 및 보관에 Guide Line을 제시할 것이라고 판단한다.

• Journal of Satellite, Information and Communications
• /
• v.5 no.1
• /
• pp.48-53
• /
• 2010

COMS (Communication, Ocean and Meteorological Satellite), which will be launched in June 23rd, 2010 and located on geostationary orbit at the latitude of $128.2^{\circ}E$, is a multi-function satellite for communications, ocean observation, and meteorology. In order to operate Ka-band communication payload effectively, which is one of the three payloads for COMS, the Transponder Monitoring and Control (TMC) system are necessary in ground systems. In this paper, the concepts and design of the TMC system for COMS Ka-band payload are described.

• Bulletin of the Korean Space Science Society
• /
• 2003.10a
• /
• pp.55-55
• /
• 2003

과학위성 1호 발사 후 지상국에서 위성을 제어하기 위해서는 여러 대의 위성제어용 컴퓨터에서의 명령들을 과학위성 1호가 올바로 수신할 수 있도록 해야 하고, 마찬가지로 과학위성 1호에서 오는 정보들을 원하는 위성제어용 컴퓨터로 알맞게 입력되도록 해야한다. 지상국에서 이러한 역할을 하는 것이 바로 GSC (Ground Station Controller)이다. GSC를 과학위성 1호 운용하는 데 적합하게 만들기 위해 위성에서 사용되는 Modem과 동일한 성능의 Modem을 장착하였고 통신신호 제어를 위한 TNC(Terminal Node Controller)가 내장이 되어있다 이러한 GSC는 여러 위성제어용 컴퓨터의 명령을 TNC가 받아서 통신 신호를 제어한 후 원하는 Modem으로 거치도록 하고 그에 따른 Audio 출력 신호의 증폭률을 가변시킬 수 있다. 본 연구에서는 과학위성 1호 관제를 위한 GSC의 구조, Spec 및 연구 개발 내용을 소개한다.

• Proceedings of the KIPE Conference
• /
• 2000.07a
• /
• pp.443-447
• /
• 2000

본 논문에서는 과학위성 1호의 전력계 설계에 대해서 서술한다 과학위성 1호의 전력계는 크게 Power stage와 Control stage로 나누어지는데 Power stage 는 200[Watt] Buck으로 구성되어 있으며 Control stage는 Hardware 제어기인 최대전력 추적기와 배터리 전압제어기 Software control을 위한 베터리 전류제어기와 직접 듀티제어기로 이루어져 각 동작모드에 따라서 적절한 제어기를 선택할 수 있게 되어있다. 따라서 신뢰성 있는 제어와 정밀제어를 선택적으로 정할 수 있기 때문에 위성의 운용면에서 용이성을 제공해 준다.

• Journal of Advanced Navigation Technology
• /
• v.15 no.3
• /
• pp.343-348
• /
• 2011

In this paper, we propose the construction and reconstruction method of satellite radio interferer search system to deal with the keen competition among nations to acquire the limited satellite sources. To construct the satellite interferer search system, whole TLS system construction, part of TLS system construction, and domestic system construction methods are proposed. After that characteristics, advantages, and disadvantages of the system are analyzed when these proposed systems are constructed. In addition, database problems are analyzed in case of the reliability of the operating database, the convergence management between database management systems, and public database service then the solution are proposed.

• Aerospace Engineering and Technology
• /
• v.9 no.2
• /
• pp.176-184
• /
• 2010

The power simulator for a LEO satellite is a useful tool to analyze mission validity and energy balance for various mission scenarios by estimating power generation, power consumption, depth of discharge, bus voltage, charging/discharging current, etc. In this paper, it is described the calculation algorithm of the solar array (SA) power, the satellite load power and the battery modeling method to develop a satellite power simulation. To simulate the SA power generation, three different operation modes (DET, MPPT, CV) of SAR (Solar Array Regulator) are considered with a SA model. The satellite load power is estimated using the satellite unit power database, the unit on/off configuration at some satellite operation modes. The bus voltage and battery charging/discharging current at the specific DoD (Depth of Discharge) are calculated based on the battery characteristics. By this satellite power simulator, it can be conveniently analyzed the energy balance and the validity of a planned mission of a LEO satellite.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
• /
• v.19 no.6
• /
• pp.663-668
• /
• 2008

Recently, World Radio Conference(WRC)-2007 approved the ultrawide bandwidth of 500 MHz for the use of spaceborne synthetic aperture radar in X-band for the EESS(Earth Exploration Satellite Service) in order to improve the SAR imaging resolution. It is concerned about the interference impact from the spaceborne SAR that may cause to most of ground radars due to the extended ultra wideband. In this paper, in order to predict the interference impact of the ground-based radar from the spaceborne radar, radar interference model is presented using radar characteristic parameters by taking into account the operating environments of the spaceborne and ground based radar in the time, space, and spectrum domains. Using the spaceborne SAR model of TerraSAR-X and ground radar model of meteorological radar recommended by ITU-R, the interference impact was assessed through the computer simulation to see the possible interference impact of the ground based radar operating in the Korean peninsula.

• Aerospace Engineering and Technology
• /
• v.1 no.2
• /
• pp.132-140
• /
• 2002

By utilizing OSMI (Ocean Scanning Multi-spectral Imager) onboard KOMPSAT-1, the moon can be imaged. Because the moon has no atmosphere and reflects sun lights at a constant rate, it can be the radiance source for calibration of OSMI. But there are a lot of risks which made KOMPSAT-1 enter into safe-hold mode. So planning the imaging of the moon with OSMI should be determined seriously with consideration to information on KOMPSAT-1 operation, the moon, the sun, etc. But it takes a long time for determining the imaging time of the moon using MCE(Mission Control Element) simulator and there are operational problems to be solved. In this paper, fast simulator for determining imaging time for the moon with OSMI has been developed. The proper timeline for imaging the moon and the position of the moon image in OSMI image coordinates and the phase of the moon are determined. STK was used for acquiring information on KOMPSAT-1, the moon, the sun and the characteristitcs of OSMI are considered. As a result, we can determine imaging time of the moon with OSMI much faster and efficiently.

• Journal of Satellite, Information and Communications
• /
• v.12 no.2
• /
• pp.21-27
• /
• 2017

The combat systems in Korea navy have been operating some kinds of tactical data link systems such as Link-11, ISDL and JTDLS. Each tactical data link system has the ability to transmit and receive tactical information like track, engagement, weapon information by using unique message of theirs. And each unique message has their own format. But a number of tactical data link system make combat effectiveness worse because their major functions are duplicated unnecessarily. So, many advanced countries are trying to make united data link system. Similarly, the combat systems in Korea navy will operate C4I data link system, and it is combined version current ISDL, KNCCS and JTDLS data link system. In this paper, we consider the development current tactical data link systems in Korea navy. Also, compare the characteristics between I-message used in ISDL and Host-Interface message used in C4I. From these results, we analyze advanced points about C4I data link system.

• Korean Journal of Remote Sensing
• /
• v.16 no.3
• /
• pp.261-279
• /
• 2000

Today, the development of spaceborne Earth remote sensing is characterised by the increasing number and various types of remote sensing satellites, which are being operated in the low altitude and geostationary orbits with the help of rapid development of modern space technologies. It is believed that around 15 countries have programs to own their spaceborne Earth remote sensing systems, and the number of systems will be reached to some tens until the end of 2000 years. It is expected that Korean remote sensing satellites will be launched in sequence according to the national space program. The befinits will be magnificient because of the wide range of application area. Application of remote sensing information to the social infra implies that the potential customers can access the information, mission and the characteristics of the operation, and it is necessary to be supplied more information about systems and mission areas to our domestic users for proper applications. In this review we will survey the applications of the information acquired by the systems of USA, Russia and other countries. In this review we will discussed withing general application area, missions and systems.