• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.97-97
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• 2003

아리랑위성 1호는 1999년 12월 21일 발사되어 3년의 설계 임무 수명을 성공적으로 완료하였으며 현재 위성체의 특이한 이상 상태 없이 안정적으로 연장 운영되고 있다. 위성이 성공적으로 임무를 수행하기 위해서는 태양전지 및 배터리 등의 기능이 적절하게 유지되어야 한다. 위성의 전력을 생산하는 태양 전지는 여러 가지 복사 및 운영중의 온도차와 같은 우주환경 등에 의해서 서서히 성능이 감소하게 되고, 배터리 또한 온도상승 등으로 인해서 성능이 감소하게 된다. 또한 위성의 궤도평면과 태양 벡터 사이의 각으로 정의되는 베타각($\beta$)에 의해서 식기간의 변화 및 온도 변화로 인해서 전력계에도 변화가 발생한다. 본 논문에서는 정상운영 초기부터 현재까지 실제 운영 궤도상에서 얻어진 원격계측자료(Telemetry)를 이용하여 전력계의 주요 부분 변화를 살펴보았다.

• Journal of the Korean Society for Precision Engineering
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• v.25 no.3
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• pp.50-55
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• 2008

In this paper, we propose a new shape compensation scheme to make up for the difference in groove radius between the formed tools and the machined bearing raceways, which inherently takes place during machining the ball bearing raceways by the turning process using conventional formed tools. The associated conventional methods of the formed tool design and its modification such as a simple depth compensation method and a graphical compensation method are introduced and the latter, which has been known to be the better of the two, is experimentally investigated in detail to reveal its drawback. The algorithm is given and it is applied to develop a formed tool design program. The program developed by the presented approach is successfully applied to design the formed turning tool for the bearing raceways.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.4
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• pp.306-314
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• 2018

A two-axis gimbal-type X-band antenna for CAS(Compact Advanced Satellite) transmits large amount of image data to ground station regardless of satellite attitude and orbital motion. This antenna mounted on the external surface of the satellite is directly exposed to the extreme space with thermal environment during the orbital operation. Therefore, a proper thermal design is needed to maintain the antenna itself as well as other main components within allowable temperature range. In this study, the thermal design effectiveness of two-axis gimbal X-band antenna was verified through the thermal analysis. In addition, required power and duty cycle of heater were estimated through the thermal analysis under conditions of system level thermal vacuum test and on-orbit thermal environment. The thermal analysis results indicated that all the main components of X-band antenna satisfy the allowable temperature requirement.

• Bulletin of the Korean Space Science Society
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• 2005.04a
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• pp.129-132
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• 2005

This paper describes BAUSAT-2 orbital thermal analysis and preliminary design of thermal control subsystem. To design thermal control subsystem of HAUSAT-2, we have considered active & passive thermal control method based on basic theory and themal equilibrium equation. Using this result, suitable thermal control method and material have been selected. We have designed thermal control subsystem based on analysis of HAUSAT-2's thermal environments on sun synchronous orbit with altitude 650km, inclination $98^{\circ}$ and thermal distribution and range expectation of each HAUSAT-2's surface. Thermal analysis consists of system level, box level and board level analysis. We have completed system level and box level analysis. Till now, board level analysis of main heat dissipation board in progress. Thermal control subsystem has designed according to thermal analysis result. This design is to maintain all of the HAUSAT-2 components within the allowable temperature limits. In future, STM

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.5
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• pp.386-392
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• 2017

This paper considers the analysis of the flight performance reserve, which is required propellant to compensate various launch vehicle performance deviations, to inject the payload of a 3-staged launch vehicle to a circular sun synchronous orbit at a height of 700 km. The various error sources, which affect the orbit injection accuracy, and their uncertainty are defined first. Then the sensitivity analysis, which has the advantage that each error source effect can be investigated independently, is performed for the extreme ${\pm}3{\sigma}$ conditions of the launch vehicle performance errors. Monte carlo simulations are also conducted to compute the propellant reserve, which can consider the combined effects of each error source. Finally the obtained flight performance reserves by the two approaches are compared and it is confirmed that they show similar results.

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.23 no.2
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• pp.137-145
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• 2005

In this paper, we investigate the accuracy of various sensor models developed for linear pushbroom satellite images. We define the accuracy of a sensor model in two aspects: the accuracy of bundle adjustments and the accuracy of estimating exterior orientation parameters. The first accuracy has been analyzed and reported frequently whereas the second accuracy has somewhat been neglected. We argue that the second accuracy is as important as the first one. The second accuracy describes a model's ability to predict satellite orbit and attitude, which has many direct and indirect applications. Analysis was carried out on the traditional collinearity-based sensor models and orbit-based sensor models. Collinearity-based models were originally developed for aerial photos and modified for linear pushbroom-type satellite images. Orbit-based models have been used within satellite communities for satellite control and orbit determination. Models were tested with two Kompsat-1 EOC scenes and GPS-driven control points. Test results showed that orbit-based models produced better estimation of exterior orientation parameters while maintained comparable accuracy on bundle adjustments.

• The Bulletin of The Korean Astronomical Society
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• v.30 no.2
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• pp.72.1-72.1
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• 2005

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.66-72
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• 2014

This paper introduces an asynchronous multiple radar fusion algorithm for space object tracking. To estimate orbital motion of space object, a multiple radar scenario which jointly measures single object with different sampling time indices is described. STK/ODTK is utilized to determine realization of orbital motion and joint coverage of multiple radars. Then, asynchronous fusion algorithm is adapted to enhance the estimation performance of orbital motion during which multiple radars measure the same time instances. Monte-Carlo simulation results demonstrate that the proposed asynchronous multi-sensor fusion scheme better than single linearized Kalman filter in an aspect of root mean square error.

• Journal of the Korean Institute of Gas
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• v.12 no.4
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• pp.8-13
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• 2008

The stray current interference problem could induce the corrosion of near-by structure and rail itself. Many efforts has been concentrated on the reduction of the interference. In this work the influences of separation distance, soil resistivity, pipe coating resistance, leak resistance of rail were studied using the numerical analysis methods. These analysis could be used to estimate the sensitivity of each variables in the study of the mitigation method and their numerical analysis.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.1
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• pp.55.1-55.1
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• 2012

2010년과 2011년의 관측시즌에 총 23일의 BVR 측광 관측을 통하여 처음으로 얻은 2세트의 BVR 광도 곡선을 분석하였다. 새로운 두 세트의 BVR 광도곡선은 제1식과 제2식의 깊이가 거의 비슷하지만, 식바깥 부분에서 관측 시즌에 따라 서로 다른 모양의 잘 발달된 파형 모양을 보인다. 이는 BD And가 흑점이 활동이 매우 심한 짧은 주기의 RS CVn형 식쌍성임을 나타내는 것이다. 우리의 극심시각을 포함한 모든 극심시각을 분석하여 BD And의 공전주기가 규칙적으로 변하는 것을 발견하였다. 이 변화를 보이지 않는 제3천체에 의한 광시간 효과로 가정하여, 궤도이심율이 0.83이며, 9.15년의 주기를 가진 광시간 궤도를 결정하였다. Wilson-Devinney 쌍성 모형을 이용하여 흑점과 제3광도를 고려한 두 세트의 광도곡선 해를 산출하였고, BD And의 절대량을 구하였다. 식바깥의 파형 모양의 변화는 주성의 표면에 매우 큰 두 개의 흑점과 그 위치와 이동으로 잘 설명되며, 전체 광도의 약 15%에 해당되는 제3광도가 검출되었다. 주기연구에서 구한 제3천체의 궤도요소와 제3광도의 결합으로 제3천체의 질량과 궤도경사각을 유추하였다. BD And의 성분별의 평균 나이가 등연령 곡선으로부터 태양과 비슷한 4.6${\times}$109년으로 산출되었다. BD And를 포함하여 현재까지 알려진 짧은 주기의 RS CVn형 쌍성들의 H-R도가 항성진화 경로와 함께 제시되며, 그 천체물리학적 의미를 살펴본다.