• 한국항공우주학회지
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• 제36권4호
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• pp.393-398
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• 2008

본 논문에서는 소형 인공위성에 탑재 가능한 GPS/INS 항법 컴퓨터의 구조를 제안한다. GPS/INS 항법 시스템을 소형 인공위성에 적용하기 위해서는 우선 우주의 방사능, 미세 중력, 진공 상태 등의 극한 환경을 고려해야 한다. 또한 소형 인공위성에서 GPS/INS 항법 시스템의 궁극적인 목표는 소형 인공위성의 편대 비행이므로 실시간 처리 능력이 필요하다. 제작된 항법 보드에는 우주환경에 대한 헤리티지가 있는 PowerPC계열의 MPC860T와 KAUSAT-2의 환경시험에서 우주환경에 대한 검증을 마친 ATmega128을 사용하였다. 항법 알고리즘은 MPC860T에 포팅된 VxWorks 환경에서 동작하도록 구현하였다.

• 디자인융복합연구
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• 제16권6호
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• pp.59-74
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• 2017

루이스 설리번은 "형태는 기능을 따른다"라고 주장했다. 기능이라는 것은 사용자가 제품이나 공간을 사용함에 있어서 가장 원초적으로 필요한 요소 중에 하나이며, 공간 및 건축 분야에서의 "기능"은 그것의 형태를 결정하는 가장 중요한 요소의 의미를 가지고 있다. 이렇게 "기능주의"의 관점에서 기능주의가 추구하는 중요한 요소들이 어떻게 그것의 형태와 관계를 갖는 지를 확인하기 위해서 토요 이토의 작품을 선정하였다. 1970년 초반에서 현재까지 진행된 그의 작품 중에서 공간 및 건축의 구조, 재질 및 공간의 형식을 쉽게 파악할 수 있도록 소규모의 주거 공간 프로젝트를 선정하여 분석하였다. 공간 및 건축의 구조와 표피를 재질의 특성으로 분류하고 공간의 개방성의 강도에 따른 분류를 진행하였다. 결과적으로 기능을 추구하는 공간 및 건축은 기능이라는 요소를 부각하기 위해서 전체적인 장식을 배제하고 그 기능의 효율성을 최대한으로 추구할 수 있는 방법을 사용하였다. 이토 토요의 소규모 주거 공간에서 발견되는 특징은 형태의 정형화 및 단순화, 공간의 개방성, 각 요소의 다목적성 활용성으로 정의할 수 있다.

• 한국감성과학회:학술대회논문집
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• 한국감성과학회 2008년도 추계학술대회
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• pp.151-154
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• 2008

The purpose of this research project is to provide information on emotional design and designs a kind of shoe storage for small space. Through researching the activities of target user and analyzing the present market, we get the clear understanding of direction for storage design, and create a new domain of for storages, with its added value and competition too. This will satisfy demand of consumers and benefit for enterprise.

• 한국항공우주학회지
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• 제42권4호
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• pp.351-359
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• 2014

본 논문에서는 저궤도 소형인공위성에서 위성의 각 부에 전원을 공급하기 위한 리튬이온 배터리 시스템의 신뢰성 확보를 위해 수행한 우주인증시험들의 결과를 나타내었다. 리튬이온 배터리 시스템의 신뢰성을 검증하기 위하여 구조해적, 성능시험, 우주 및 발사환경에서의 환경시험 등을 수행하였다. 모든 해석 및 시험 결과가 요구조건에 만족함을 보임으로써 리튬이온 배터리를 적용한 소형인공위성의 신뢰성을 검증하고 제고할 수 있었다.

• Journal of Astronomy and Space Sciences
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• 제34권1호
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• pp.31-35
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• 2017

Optical observation is one of the most common techniques used for characterizing the physical properties of unknown objects and debris in space. This research presents measurements and properties of the new object 96019 from ground-based optical methods. Optical observations of this small object were performed using a charge-coupled device (CCD) camera and the Santel-500 telescope at the Zvenigorod Observatory. The orbital elements and physical properties of this object, such as area-to-mass ratio, have been determined. The results show that this small object has a low area-to-mass ratio, between 0.009 and $0.12m^2/kg$. The light curve of object 96019 is given: Over the time intervals, variations in brightness are analyzed and the maximum brightness was found to be 12.4 magnitudes. The observational results show that, this object brightens by about three magnitudes over a time span of three minutes. Based on these observations, the characteristics and physical properties of this object are discussed.

• 한국농촌건축학회논문집
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• 제9권2호
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• pp.87-94
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• 2007

The recent change of social environment has influence on the configuration of space for the community social welfare center. And so the relation of space and the service function required the change of spatial configuration. The social welfare center fills the role of family welfare, domiciliary care, community service etc. In such sense, this research explore the conditions of spatial configuration for the community welfare service unit of social welfare center in small city. For this study, it was investigated the space role and service function, the service program, the usage characteristics, the room satisfaction of social workers. In sum, the useful data were collected, analyzed, and colligated by case study. It could be used in the basic design criteria of community service unit for the social welfare center in small city.

• Journal of Astronomy and Space Sciences
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• 제22권1호
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• pp.35-46
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• 2005

This paper addresses the design and analysis results of a 2-axes magnetometer for attitude determination of small satellite. A low-cost and efficient 2-axes fluxgate magnetometer was selected as the most suitable attitude sensor for LEO microsatellites which require a low-to-medium level pointing accuracy. An optimization trade-off study has been performed for the development of 2-axes fluxgate magnetometer. All the relevant parameters such as permeability, demagnetization factor, coil diameter, core thickness, and number of coil turns were considered for the sizing of a small satellite magnetometer. The magnetometer which is designed, manufactured, and tested in-house as described in this paper satisfies linearity requirement for determining attitude position of small satellites. On the basis of magnetometer which is designed in Space System Research Lab. (SSRL), commercial magnetometer will be developed.

• Journal of Astronomy and Space Sciences
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• 제22권1호
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• pp.47-58
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• 2005

This paper addresses development of the ultra-light analog sun sensors for small satellite applications. The sun sensor is suitable for attitude determination for small satellite because of its small, light, low-cost, and low power consumption characteristics. The sun sensor is designed, manufactured and characteristic-tested with the target requirements of ${\pm}60^{\circ}$ FOV (Field of View) and pointing accuracy of ${\pm}2^{\circ}$. Since the sun sensor has nonlinear characteristics between output measurement voltage and incident angle of sunlight, a higher order calibration equation is required for error correction. The error was calculated by using a polynomial calibration equation that was computed by the least square method obtained from the measured voltages vs. angles characteristics. Finally, the accuracies of 1-axis and 2-axes sun sensors, which consist of 2 detectors, are compared.

• 한국디자인학회:학술대회논문집
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• 한국디자인학회 2002년도 가을학술발표대회 디자인학 연구
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• pp.98-99
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• 2002

• Journal of Astronomy and Space Sciences
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• 제39권3호
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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.