• 한국항공우주학회지
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• 제48권10호
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• pp.791-799
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• 2020

2019년 10월 발사된 Northrop Grumman사의 MEV-1(Mission Extenstion Vehicle)은 세계 최초의 무인임무로서 궤도상 유지보수(On-Orbit Servicing)가 실질적으로 가능함을 보였다. 물론 궤도상 유지보수 임무는 수십 년 전부터 제안된 개념으로 운영 중인 위성에 대한 궤도수정 및 유지, 추진제/장비 보급 및 업그레이드, 수리, 궤도상 조립 및 제작, 우주잔해 처리 등 다양한 임무개념으로 발전되고 있으며, 이번 MEV-1 임무의 성공으로 향후 세계적으로 정부기관 및 민간분야 위성사업에서의 시장이 확대될 것으로 예상된다. 궤도상 유지보수 임무는 임무의 특성상 기본적으로 고효율의 전기추진시스템의 활용은 필수적이다. 본 연구에서는 전기추진시스템 중 홀추력기를 활용한 간단한 궤도상 유지보수 임무에 대한 임무해석 내용을 소개하고자 한다. 임무사례로서 정지궤도위성의 수명연장 임무에 대해 다양한 홀추력기 설계변수조합에 대한 설계공간탐색을 수행하고, 설계공간분석 및 최적화를 통해 고려하는 임무에 적합한 홀추력기의 설계 및 운용 파라미터를 제안함과 동시에 임무성능을 도출하였다. 추가적으로 현재 궤도상 유지보수 임무해석 시 개선점과 홀추력기를 활용한 우주임무해석에서의 발전방향을 고찰하였다.

• International Journal of Aeronautical and Space Sciences
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• 제14권2호
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• pp.162-171
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• 2013

A general purpose aircraft mission performance analysis program has been developed. The program can be used in design mode or in analysis mode. Fuel weight for a given mission profile can be estimated when the design mode is chosen, while mission time or mission range for a given fuel can be estimated when the analysis mode is chosen. The mission analysis program is written with JAVA and includes GUI(Graphic User Interface) for users' conveniences. With a proper combination of databases for propulsion, aerodynamics and weight, the program can be configured to compute the performance of any type of aircraft. The program is validated by comparing its results with the results of a well known performance analysis program by ADD(Agency for Defense Development).

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 1995년도 한국우주과학회보 제4권1호
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• pp.40-40
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• 1995

No Abstract. See Full-text

• International Journal of Aerospace System Engineering
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• 제3권2호
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• pp.31-37
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• 2016

STEP Cube Lab (Cube Laboratory for Space Technology Experimental Project) is a 1U standardized pico-class satellite. Its main mission objective is an on-orbit verification of five fundamental core space technologies. For assuring a successful missions of the STEP Cube Lab with five payloads, electrical power subsystem (EPS) shall sufficiently provide an electrical power to payloads and bus systems of the satellite during an entire mission life. In this study, a design process of EPS system was introduced including power budget analysis considering a mission orbit and various mission modes of the satellite. In conclusion, adequate EPS hardware in compliance with design requirements were selected. The effectiveness and mission capability of EPS architecture design were confirmed through an energy balance analysis (EBA).

• 한국마린엔지니어링학회:학술대회논문집
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• 한국마린엔지니어링학회 2001년도 추계학술대회 논문집(Proceeding of the KOSME 2001 Autumn Annual Meeting)
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• pp.125-129
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• 2001

A Software development of space launch vehicle danamics and control simulation is presented in this study. The Dynamics for a two body problem including pertubations for various effect show on this paper. Mission analysis for space launch vehicle is included rendezvous mission. The software develpoment is intended to maintain generality to the extent possible through objected approach for future modification and expansion. This result shows various pertubation effect is also important.

• Journal of Astronomy and Space Sciences
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• 제36권2호
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• pp.69-74
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• 2019

Spacecraft requires sufficient power in orbit to perform its mission. So as to comply with system requirements, the sufficient power should be made by a solar cell array by photovoltaic power conversion. A life time of space program depends on its mission considering parts reliability and parts grade. Based on the mission life time, power equipment might be designed to meet specifications. In outer space, solar cell array might generate the dc power by photovoltaic conversion effects and GaInP/GaAs/Ge solar cells are used in this study. Space programs that require more than five years should select parts for high reliability applications. Therefore, reliability analysis for high reliability applications should be performed to check its fulfilment of the requirements. This program should also require more five years for its mission and we performed its analysis using parts count method (PCM) for its reliability. Finally, we performed reliability analysis and obtained quantitative figures found out 99.9%. In this study, we presented the reliability analysis of the 300 W GaInP/GaAs/Ge solar cell array.

• Journal of Astronomy and Space Sciences
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• 제17권2호
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• pp.309-316
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• 2000

KOMPSAT-2 will carry MSC(Multi-Spectral Camera) which provides 1m resolution panchromatic and 4m resolution multi-spectral images at the altitude of 685km sun-synchronous mission orbit. The mission operation of KOMSPAT-2 is to provide the earth observation using MSC with nadir pointing. KOMPSAT-2 will also have the capability of roll/pitch tilt maneuver using reaction wheel of satellite as required. In order to protect MSC from thermal distortion as well as direct sunlight, MSC shall be operated within the constraint of sun incidence angle. It is expected that the sunlight will not violate the constraint of sun incidence angle for normal mission operations without roll/pitch maneuver. However, during roll/pitch tilt operations, optical module of MSC may be damaged by the sunlight. This study analyzed sun incidence angle of payload using KOMPSAT-2 AOCS (Attitude and Orbit Control Subsystem) Design and Performance Analysis Soft ware for KOMPSAT-2 normal mission operations.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 1993년도 한국우주과학회보 제2권2호
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• pp.12-12
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• 1993

95년 발사 예정인 무궁화위성의 궤도전이에 필요한 조정 파라미터를 계산하기 위해 원지점 모터 점화 계획 S/W를 만들어서 결과에 대해 분석해 보았다. S/W는 Mission analysis mode와 Insert mode로 구성되는데, Mission analysis mode에서는 표류궤도를 얻기 위한 점화 파라미터를 구하는 것이고, Insert mode에서는 점화 파라미터를 이용해 표류궤도를 구하는 것이다.

• Advances in aircraft and spacecraft science
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• 제7권3호
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• pp.271-290
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• 2020

The paper describes the analysis of deployment strategies and trajectories design suitable for executing the inspection of an operative spacecraft in orbit through re-usable CubeSats. Similar missions have been though indeed, and one mission recently flew from the International Space Station. However, it is important to underline that the inspection of an operative spacecraft in orbit features some peculiar characteristics which have not been demonstrated by any mission flown to date. The most critical aspects of the CubeSat inspection mission stem from safety issues and technology availability in the following areas: trajectory design and motion control of the inspector relative to the target, communications architecture, deployment and retrieval of the inspector, and observation needs. The objectives of the present study are 1) the identification of requirements applicable to the deployment of a nanosatellite from the mother-craft, which is also the subject of the inspection, and 2) the identification of solutions for the trajectories to be flown along the mission phases. The mission for the in-situ observation of Space Rider is proposed as reference case, but the conclusions are applicable to other targets such as the ISS, and they might also be useful for missions targeted at debris inspection.

• 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.