• Proceedings of the Korea Information Processing Society Conference
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• 2008.05a
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• pp.378-381
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• 2008

최근 정형 검증 분야에서 만족가능성 처리기를 사용한 연구가 많아지면서 이를 적용한 사례들이 많이 나타나고 있다. 만족가능성 처리기를 사용하기 위해서는 검증 되어야 할 시스템을 CNF식으로 변환해야 한다. 우리는 루빅 큐브를 만족가능성 처리기를 통해 풀어보기 위해 이를 CNF식으로 변환해 보았다. 루빅 큐브는 정육면체로 이루어진 퍼즐의 일종으로 모든 면이 각각 한가지 색으로만 채워져야 하는 문제이다. 우리는 본 논문에서 만족가능성 처리기를 사용한 사례 중에 아직 적용한적이 없는 루빅 큐브를 CNF식으로 변환해 풀었음을 보여준다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.9
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• pp.802-808
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• 2014

MEMS based solid propellant thruster researched for the purpose of an academic research will be verified at space environment through CubeSat program. For this, the temperature of the MEMS thruster should be within allowable operating temperature range by proper thermal control to prevent the ignition failure caused by ignition time delay and to guarantee the structural safety of the MEMS thruster in the low temperature. In this study, we proposed an effective thermal control strategy, that is to use micro-igniter as a heater and temperature sensor for active thermal control instead of using additional heater. The effectiveness of the strategy has been verified through on-orbit thermal analysis of CubeSats with MEMS thruster.

• Journal of Aerospace System Engineering
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• v.12 no.5
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• pp.69-75
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• 2018

In this study, we proposed a nylon wire cutting-type solar panel separation mechanism for CubeSat applications using spring-loaded pogo-pins, which has been widely used as temporary electrical interface between two separate electronics. The mechanism proposed in this study has great advantages of higher holding capability, ability to constrain along in-plane and out-of-plane directions of solar panels, simplicity in tightening of nylon wire and synchronous separation of multiple panels. In addition, the pogo-pins used for the proposed mechanism act as electrical power interface, separation status switch and separation spring. In this study, the functionality of the proposed mechanism was validated through the separation tests with various number of nylon wire windings.

• Journal of Space Technology and Applications
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• v.3 no.4
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• pp.355-372
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• 2023

As the need for low-cost, high-efficiency cubesats develops in the new space age, commercial paradigms are shifting in the private sector. This paper examines the challenges of launching and operating both domestic and foreign cubesats, and proposes practical solutions to ensure the robustness and reliability of the satellites from a practical perspective. In particular, the paper deals with checkpoints that are easy to miss, focusing on key events that can occur from the satellite deployment process through normal mode to mission mode in the operation scenario. Although the contents presented in this paper may not be technically applicable to all cubesat systems due to the different nature of each satellite bus system, they will be of some help during satellite assembly, integration and testing.

• Journal of Astronomy and Space Sciences
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• v.37 no.2
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• pp.117-129
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• 2020

In a Satellite communication system, a link budget analysis is the detailed investigation of signal gains and losses moving through a channel from a sender to receiver. It inspects the fading of passed on data signal waves due to the process of spreading or propagation, including transmitter and receiver antenna gains, feeder cables, and related losses. The extent of the proposed tool is to make an effective, efficient, and user-friendly approach to calculate link budget analysis. It is also related to the satellite communication correlation framework by building up a graphical interface link analysis tool utilizing STK^® software with the interface of C# programming. It provides better kinds of graphical display techniques, exporting and importing data files, printing link information, access data, azimuth-elevation-range (AER), and simulation is also possible at once. The components of the link budget analysis tool include transmitter gain, effective isotropic radiated power (EIRP), free space loss, propagation loss, frequency Doppler shift, flux density, link margin, elevation plot, etc. This tool can be useful for amateur users (e.g., CubeSat developers in the universities) or nanosat developers who may not know about the RF communication system of the satellite and the orbital mechanics (e.g., orbit propagators) principle used in the satellite link analysis.

• The Bulletin of The Korean Astronomical Society
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• v.39 no.2
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• pp.108.2-108.2
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• 2014

과거 달 탐사 미션으로 달에는 global magnetic fields는 존재하지 않고 표면에 국부적으로 자기장이 존재함이 확인되었다. 그러나 이렇게 측정된 자기장 데이터는 일정 고도 (> 20 km) 이상에서 측정되었기 때문에, 지표에 비해 그 세기가 매우 약해 자기장의 형태와 분포를 연구하는데 한계가 있다. 보다 자세한 연구를 위해서는 표면에서부터 다양한 고도에 이르는 위치에서 측정된 자기장 데이터가 필요하며, 이는 달 표토의 자화나 Swirl 형성 메커니즘을 이해하는데 중요한 정보이다. 따라서 본 연구에서는 큐브위성을 이용하여 저궤도부터 지표까지의 자기장을 측정하는 방안을 소개한다. 큐브위성은 달 궤도 모선에서 사출되어 자기이상 지역 표면에 충돌하는 임무를 가진다. 자력계는 모선과 큐브위성에 각각 탑재되어 자기장을 측정하며, 모선으로 부터 사출된 큐브위성은 충돌 직전까지 자기장을 측정하고 모선에 습득한 데이터를 실시간으로 전송한다. 이렇게 측정된 자기장 데이터는 모선의 궤도부터 표면에 이르기까지 여러 고도에서 측정되었기 때문에 자기이상 지역의 자기장 구조를 파악하는데 중요한 자료로 활용할 수 있다. 이에 본 연구에서는 달의 자기이상 지역과 큐브위성 임무 설계에 대하여 기술하였다.

• The Bulletin of The Korean Astronomical Society
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• v.42 no.1
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• pp.40.2-40.2
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• 2017

인공위성을 이용한 우주망원경 및 우주탐사장비는 천문학 및 우주과학 연구에 매우 중요한 관측 장비로서 지상에서 불가능한 다양한 파장대에서 관측을 수행하고 있다. 이러한 우주망원경의 경우 개발기간과 비용 또한 상대적으로 매우 큰 규모를 가지고 있다. 또한 장시간의 관측을 위한 관측위성의 운영 신뢰도 확보와 결과 활용을 위해 많은 연구 인력이 투입되는 거대 연구개발 사업이다. 그러나 최근에는 초소형 인공위성을 이용하여 여러 우주관측 및 실험이 수행되고 있다. 큐브위성으로 명명되어 있는 초소형 인공위성은 크기와 전력의 제한은 있지만 상대적으로 단기간의 개발일정과 저비용으로 전 세계적으로 폭발적인 성장을 하고 있는 관측기술이다. 경희대학교에서는 CINEMA라는 2개의 큐브위성을 개발 운영하였고, SIGMA 라는 큐브위성을 개발하여 발사를 기다리고 있다. 또한 향 후 광학관측을 위한 초소형 인공위성을 기획하고 있다. 국내에서는 천문우주용으로 제작되는 위성이외에도 다양한 기술검증용 위성이 10여기 이상 제작되고 있는 상황이다. 이에 초소형인공위성의 동향과 향 후 천문우주 관측에 활용 할 수 있는 방안에 대하여 논의 하였다.

• Journal of Astronomy and Space Sciences
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• v.38 no.3
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• pp.165-173
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• 2021

Apophis is a near-Earth object with a diameter of approximately 340 m, which will come closer to the Earth than a geostationary orbit in 2029, offering a unique opportunity for characterizing the object during the upcoming encounter. Therefore, Korea Astronomy and Space Science Institute has a plan to propose a space mission to explore the Apophis asteroid using scientific instruments such as a laser altimeter. In this study, we evaluate the performance metrics of a laser altimeter using a pseudorandom noise modulation technique for the Apophis mission, in terms of detection probability and ranging accuracy. The closed-form expression of detection probability is provided using the cross correlation between the received pulse trains and pseudo-random binary sequence. And the new ranging accuracy model using Gaussian error propagation is also derived by considering the sampling rate. The operation range is significantly limited by thermal noise rather than background noise, owing to not only the low power laser but also the avalanche photodiode in the analog mode operation. However, it is demonstrated from the numerical simulation that the laser altimeter can achieve the ranging performance required for a proximity operation mode, which employs commercially available components onboard CubeSat-scale satellites for optical communications.

• Journal of Astronomy and Space Sciences
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• v.39 no.3
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• pp.109-116
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• 2022

The small-scale magnetospheric and ionospheric plasma experiment (SNIPE) is a mission initiated by the Korea Astronomy and Space Science Institute (KASI) in 2017 and comprises four 6U-sized nano-satellites (Korea Astronomy and Space Science Institute Satellite-1, KASISat-1) flying in formations. The main goal of the SNIPE mission is to investigate the space environment in low Earth orbit at 500-km. Because Iridium & GPS Board (IGB) is installed on the KASISat-1, a communication simulation is required to analyze the contact number and the duration. In this study, communication simulations between the Iridium satellite network and KASISat-1 are performed using STK Pro (System Tool Kit Pro Ver 11.2) from the AGI (Analytical Graphics, Inc.). The contact number and durations were analyzed by each orbit and date. The analysis shows that the average access number per day is 38.714 times, with an average of 2.533 times per orbit for a week. Furthermore, on average, the Iridium satellite communication is linked for 70.597 min daily. Moreover, 4.625 min is the average duration of an individual orbit.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.2
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• pp.172-180
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• 2016

A cubesat classified as a pico-satellite typically uses commercial-grade components that satisfy the vibration and thermal environmental specifications and goes into mission orbit even after undergoing minimum environment tests due to their lower cost and short development period. However, its reliability exposed to the physical environment such as on-orbit thermal vacuum for long periods cannot be assured under minimum tests criterion. In this paper, we have analysed the reliability and life prediction of the failure mechanisms of the cubesat mission board during its service life under the launch and on-orbit environment by using the sherlock software which has been widely used in automobile fields to predict the reliability of electronic devices.