• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.5
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• pp.141-151
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• 2018

A trajectory analysis program was developed to predict KSLV-II (Korea Space Launch Vehicle-II) performance with the reducing weight. The program estimates the LEO (Low Earth Orbit) / SSO (Sun-Synchronous Orbit) injection performance, which is determined as payload weight for the orbits, with decreasing the structural ratio or increasing rocket engine power. It is expected that the KSLV-II can transport up to 4.5 tons, 3 tons of space payloads at LEO, SSO with a reduced structural ratio by 60% of the original. It also shows that the KSLV-II can transport up to 3.65 tons at SSO by applying advanced engines of 90 tonf, 10 tonf class with the reduced structure.

• Aerospace Engineering and Technology
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• v.4 no.2
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• pp.94-100
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• 2005

The geostationary satellite propulsion system has thermistors which can measure liquid propellant temperature at tanks, pipes and etc. In the satellite propulsion system with several tanks, the propellant in the tanks is moved by temperature change and this temperature pattern is constant. In this paper, the temperature change pattern of KOREASAT 1 propulsion system is compared and the prediction study of pressurant inflow using temperature change of geostationary satellite propulsion system is described.

• Journal of the Korean Society for Railway
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• v.5 no.1
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• pp.48-54
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• 2002

This research estimated decreased vibration level as quantitative according to change of track system on Seoul Subway Line No. 1 from existing ballasted track system(Pandrol type clip) to concrete track system(Youbgdan type isolation rubber clip). Following change to concrete system, vibration level at tunnel floor decreased between 4-8dB(V). Vibration equations suggested in this paper consider the velocity of train and can estimate quantitative vibration response. These are divided by ultimate limit state($\beta$=0), serviceability limit state($\beta$=1.28) and safety state($\beta$=3), respectively. The reliability index, $\beta$=0, means 50％ data line obtained by least squares best-fit line. The reliability index $\beta$=1.28 and 3 represent boundaries below 90％ and 99.9％ respectively.

• Proceedings of the Korea Inteligent Information System Society Conference
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• 2007.11a
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• pp.324-328
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• 2007

본 논문은 감시정찰 센서네트워크에서 센서노드의 주요 기능인 표적의 탐지 및 식별을 위한 알고리즘을 제안한다. 감시정찰 센서네트워크에서 각 센서노드는 노드의 크기 및 센서, 프로세서, 네트워크, 전원 등의 자원의 제약이 있기 때문에 침입하는 적의 탐지 및 종류 식별을 위해서는 효율적인 알고리즘의 선정과 최적화가 요구된다. 본 논문에서는 음향, 진동, PIR, 자기 센서 등을 이용하여 사람, 차량 및 궤도 차량의 침입을 탐지하기 위한 적응 임계값 알고리즘과 그 종류를 식별하기 위한 최대우도추정 기법, k-최근접 이웃 추정 기법에 기반한 표적의 탐지 및 식별 알고리즘을 제안한다. 실험결과 음향 및 진동 센서에 의한 차량의 탐지, PIR 센서에 의한 사람의 탐지가 가능함을 확인할 수 있었으며 주파수 특징점을 이용하여 차량과 궤도차량의 종류식별이 가능함을 확인할 수 있었다.

• Bulletin of the Korean Space Science Society
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• 2000.10a
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• pp.28-28
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• 2000

• Bulletin of the Korean Space Science Society
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• 2008.04a
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• pp.25.4-25.4
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• 2008

• Proceedings of the KSR Conference
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• 2006.05b
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• pp.415-422
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• 2006

• Journal of Advanced Navigation Technology
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• v.12 no.4
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• pp.295-303
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• 2008

Malfunction of satellite launch vehicles with high speed and long range can be a major concern for operations. Flight safety system that monitor the trajectory and identify any failure of the launch vehicles. Tracking filters for the flight safety systems are different from common tracking filters since filter reliability is more emphasized than accuracy. Reliable estimation of instantaneous impact points requires reliable velocity estimates as well as reliable position estimates. A fusion filter for a flight safety system was developed with the tracking sensor models for the Korea Satellite Launch Vehicle I. The fusion filter performances were evaluated by analyzing the trajectory and instantaneous impact point estimates.

• Journal of Aerospace System Engineering
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• v.16 no.6
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• pp.90-98
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• 2022

The output of an infrared (IR) sensor mounted on an EO/IR payload is known to change during a mission period in an orbital environment. As it is required to calibrate the output of the IR sensor periodically to obtain high-quality images, an on-board black body system is mounted on the payload. All systems operating in the space environment require performance tests on ground to verify the target performance in the orbital environment. Therefore, it is also required to test the black body system to verify the performance of the surface temperature uniformity and the estimated representative temperature error within the target temperature range in the operating environment. In this study, calibration of the estimated representative temperature error and verification of the thermal performance of the black body system were conducted by performed a performance test in the thermal vacuum chamber applying deep space radiation cooling effect of an orbital environment.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.12
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• pp.1116-1123
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• 2015

The lifetime of a geostationary satellite depends on the residual propellant amount and therefore the precise residual propellant gauging is very important for the mitigation of economic loss arised from premature removal of satellite from its orbit, satellites replacement planning, slot management and so on. In this paper, the thermal mass method and its uncertainty are described. The residual propellant analysis of a geostationary satellite is simulated based on the KOREASAT data and the uncertainty of thermal mass method is calculated by using the Monte Carlo method. The results of this study show the importance parameter of estimation residual propellant using the thermal mass method.