• 한국항공우주학회지
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• 제42권2호
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• pp.181-190
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• 2014

무인항공기(UAV)를 이용하여 효율적인 감시정찰을 수행하기 위해서는 센서의 고성능, 다중화와 함께 운용상황에 맞는 최적화된 비행경로계획이 요구된다. 이뿐만 아니라 시스템 개발 또는 임무운용 전 임무 효용성 평가, 평시와 전시에 빠른 작전 결정을 위해서는 임무를 가시화할 수 있는 가시화 도구가 필요하다. 본 연구에서는 STK(Systems Tool Kit)와 MATLAB을 통합한 임무 가시화 및 분석 도구를 개발하고 이를 통하여 UAV 감시정보정찰(ISR; Intelligence, Surveillance and Reconnaissance) 임무분석을 수행하였다. 개발된 임무분석 도구에는 비행최적화 뿐만 아니라 장애물 회피 알고리즘, FoM(Figure of Merit) 분석 알고리즘이 적용되어 최적의 임무계획이 가능하도록 하였다.

• 로봇학회논문지
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• 제10권1호
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• pp.24-32
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• 2015

This paper introduces a graphical user interface design that is aimed to apply to the surveillance and security robot, which is the pilot program for the army unmanned light combat vehicle. It is essential to consider the activities of robot users under the changing security environment in order to design the efficient graphical user interface between user and robot to accomplish the designated mission. The proposed design approach firstly identifies the user activities to accomplish the mission in the standardized scenarios of military surveillance and security operation and then develops the hierarchy of the interface elements that are required to execute the tasks in the surveillance and security scenarios. The developed graphical user interface includes input control component, navigation component, information display component, and accordion and verified by the potential users from the various skilled levels with the military background. The assessment said that the newly developed user interface includes all the critical elements to execute the mission and is simpler and more intuitive compared to the legacy interface design that was more focused on the technical and functional information and informative to the system developing engineers rather than field users.

• Journal of Astronomy and Space Sciences
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• 제15권2호
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• pp.459-473
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• 1998

인공위성이 더욱 복잡해 감에 따라 예측할 수 없는 실패의 발생은 설계의 부적당성, 경험 부족, 문제인식 부족, 빈약한 품질제어 능력, 부적당한 시험 또는 작업자의 실수 등 때문에 늘어나고 이들은 위성의 임무 수명을 단축시킬 수 있다. 본 고에서는 위성의 일반적인 실패유형과 임무수명 인자에 대해 검토하고, 지구 및 해양관측 임무를 갖고 있는 태양동기 저궤도위성인 다목적 실용위성에 대한 임무수명인자를 조사하고 실제 예상되는 위성의 임무수명을 예측하였다. 임무수명의 예측 시 랜덤하게 발생하는 실패에 의한 수명의 중단은 예측할 수 없는 것이기 때문에, 여기서는 주로 예측이 가능한 마모에 의한 대표적인 임무수명 인자 예를 들어, 전력 버짓, 추진제 버짓, 배터리 충 방전 사이클, 복사환경의 영향, 탑재체의 신뢰도, 단일 점 실패, 위성 여유 분을 등을 조사하고 개략적인 수명을 예측하였다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.305-308
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• 2005

The COMS, Korea's first geostationary multipurpose satellite program will accommodate 3 kind of payloads; Ka-Band communication transponder, GOCI (Geostationary Ocean Color Imager), and MI (Meteorological Imager). MI raw data will be transferred to ground station via L-band link. The ground station will perform image data processing for raw data, generate them into the LRIT/HRIT format, the user dissemination data recommended by the CGMS. The LRIT/HRIT are disseminated via satellite to user stations. This paper shows the COMS LRIT data generation procedure based on COMS LRIT specification and its verification results using the LRIT user station.

• 한국군사과학기술학회지
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• 제12권2호
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• pp.248-257
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• 2009

The aim of this paper is to propose fighter aircraft's mission severity model which can be used as one of key factors for designing a structure and determining design life of KF-X. The mission severity is a quantitative data of flight loads and expressed by Nz(Vertical Load Factor) exceedances or occurrences. The severities of the flight loads depended on the circumstances of the countries which operate fighter aircraft. In this paper we have studied on Nz occurrences/exceedances of ROKAF fighter aircraft to generate mission severity model for the KF-X. The analyses of flight data were accomplished by using the Matlab.

• 한국항공운항학회지
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• 제17권3호
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• pp.40-50
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• 2009

Avionics system's function for an air transport mission is analysed. The starting point for designing a Avionics system is a clear understanding of the mission requirements and the requirement allocation by the top level aircraft system. Therefore, the analysis begins by making a top-down analysis to the aircraft missions. The baseline mission is divided into segments, and each segment is subjected to a detailed analysis to establish the requirements for the Avionics system. Special attention is given to capture the key aspects of interfaces, and to incorporate them into the design.

• 대한원격탐사학회지
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• 제19권1호
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• pp.37-42
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• 2003

Recently, KARI implemented the receiving and processing system for MODIS sensor data from NASA EOS satellites (TERRA and AQUA). This paper shows the development strategy considered, system requirement derived, system design, characteristic and test results of processing system. System operation concept and sample image are also provided. Implemented system was proven to be fully operational through lots of pass operations activities from RF signal reception to level-1 processing.

• 천문학회보
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• 제39권2호
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• pp.110.1-110.1
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• 2014

The optics of Space telescope is one of the major parts of space mission used for imaging observation of astronomical targets and the Earth. These kinds of space mission have a bulky and complex opto-mechanics with a long optical tube, but there are attempts have been made to observe a target with a small satellite in many ways. In this paper, we describe an optical design of a reflecting telescope for use in a CubeSat mission. For this design, we adopt the off-axis segmented method of astronomical observation techniques based on the Ritchey-Chr$\acute{e}$tien type telescope. The primary mirror shape is a rectangle with dimensions of $8cm{\times}8cm$, and a secondary mirror has dimensions of $2.4cm{\times}4.1cm$. The focal ratio is 3 which can obtain a $0.3{\times}0.2$ degree diagonal angle in a $1280{\times}800$ CMOS color image sensor with a pixel size of $3{\mu}m{\times}3{\mu}m$. This optical design can capture a ${\sim}4km{\times}{\sim}2.3km$ area of the earth's surface at 700 km altitude operation. Based on this conceptual design, we will keep trying to study more for astronomical observation with Attitude control system.

• 항공우주산업기술동향
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• 제8권1호
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• pp.62-76
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• 2010

본 논문에서는 최근에 다른 나라에서 진행된 무인 달 착륙선의 설계에 대한 사례 조사를 수행하고 이를 통하여 무인 달 착륙선의 설계 동향을 파악하였다. 무인 달 착륙선으로는 일본의 SELENE-2, 유럽의 LEDA와 MoonNEXT, 미국의 모듈형 소형 우주선을 이용한 달 탐사, 그리고 미국이 제안한 국제 달 탐사 네트워크의 미국 노드인 Anchor Nodes의 임무 수행을 위하여 설계된 달 착륙선 등을 조사의 대상으로 하였다. 각 조사 대상의 착륙선에 대하여 임무 요구 조건을 확인하고, 임무 설계의 내용을 조사하였다. 또한 달 표면에 안전하게 착륙하기 위한 유도제어의 방법, 센서의 구성, 임무 요구 사양을 만족하기 위하여 선정한 센서 및 구동기의 성능 사양 등을 분석하였다.

• Journal of the Optical Society of Korea
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• 제17권6호
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• pp.533-537
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• 2013

Space telescope optics is one of the major parts of any space mission used to observe astronomical targets or the Earth. This kind of space mission typically involves bulky and complex opto-mechanics with a long optical tube, but attempts have been made to observe a target with a small satellite. In this paper, we describe the optical design of a reflecting telescope for use in a CubeSat mission. For this design we adopt the off-axis segmented method for astronomical observation techniques based on a Ritchey-Chr$\acute{e}$tien type telescope. The primary mirror shape is a rectangle with dimensions of $8cm{\times}8cm$, and the secondary mirror has dimensions of $2.4cm{\times}4.1cm$. The focal ratio is 3 which can yield a 0.383 degree diagonal angle in a $1280{\times}800$ CMOS color image sensor with a pixel size of $3{\mu}m{\times}3{\mu}m$. This optical design can capture a ${\sim}4km{\times}{\sim}2.3km$ area of the earth's surface at 700 km altitude operation.