• Journal of Astronomy and Space Sciences
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• 제17권2호
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• pp.285-294
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• 2000

The post-launch mission analysis of the KOMPSAT-1 spacecraft was carried out. The injection accuracy of the Taurus launch vehicle was analyzed by comparison of the target and the realized orbit parameters. The tracking station contact analysis was also performed based on the state vectors applied at the day of launch. The offset angles between the predicted orbit and realized orbit were calculated for various tracking stations. The injection orbit parameters of the KOMPSAT-1 were analyzed for the possible options in Launch and Early Orbit Phase(LEOP) operations. Variations of the Local Time of Ascending Node(LTAN) were also obtained.

• 시스템엔지니어링학술지
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• 제10권2호
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• pp.89-95
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• 2014

In recent years, the United States have been several major failures of launch. As a result of these failures, activity of mission assurance valued. Mission assurance is defined as the application of systems engineering process towards the goal of achieving mission success. Therefore, mission assurance perform independent technical assessments throughout the concept and requirements definition, design, development, production, test, deployment, and operations phases. Space system program was emphasized the importance of the system engineering for that required huge cost and long term development. For this reason, independent review and verification of mission assurance is essential. Mission assurance gives us confidence to proceed with launch and best opportunity for mission success. In this study, framework of mission assurance is proposed by foreign case analysis.

• Journal of Astronomy and Space Sciences
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• 제41권1호
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• pp.43-60
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• 2024

Korea Pathfinder Lunar Orbiter (KPLO) is South Korea's first space exploration mission, developed by the Korea Aerospace Research Institute. It aims to develop technologies for lunar exploration, explore lunar science, and test new technologies. KPLO was launched on August 5, 2022, by a Falcon-9 launch vehicle from cape canaveral space force station (CCSFS) in the United States and placed on a ballistic lunar transfer (BLT) trajectory. A total of four trajectory correction maneuvers were performed during the approximately 4.5-month trans-lunar cruise phase to reach the Moon. Starting with the first lunar orbit insertion (LOI) maneuver on December 16, the spacecraft performed a total of three maneuvers before arriving at the lunar mission orbit, at an altitude of 100 kilometers, on December 27, 2022. After entering lunar orbit, the commissioning phase validated the operation of the mission mode, in which the payload is oriented toward the center of the Moon. After completing about one month of commissioning, normal mission operations began, and each payload successfully performed its planned mission. All of the spacecraft operations that KPLO performs from launch to normal operations were designed through the system operations design process. This includes operations that are automatically initiated post-separation from the launch vehicle, as well as those in lunar transfer orbit and lunar mission orbit. Key operational procedures such as the spacecraft's initial checkout, trajectory correction maneuvers, LOI, and commissioning were developed during the early operation preparation phase. These procedures were executed effectively during both the early and normal operation phases. The successful execution of these operations confirms the robust verification of the system operation.

• 대한임베디드공학회논문지
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• 제12권5호
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• pp.287-293
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• 2017

The naval unmanned surface vehicle (USV) conducts the surveillance operations, based on the mission plan set by the user. For setting the mission planning, the user needs to analyze the suitability of the operation for the mission planning. In this paper, we proposed a simulation program that estimates the probability of detecting targets of the mission planning in the analysis. In the simulation analysis, we design the USV's maneuvering characteristics, radar detection operational performance equipped on the USV, and targets infiltrating into surveillance area in the simulation experiment scenario. Based on the simulation results, we evaluated the mission planning suitability and find a mission planning solution recursively.

• Journal of Astronomy and Space Sciences
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• 제26권4호
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• pp.635-642
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• 2009

This paper describes the Flight Dynamics Automation (FDA) system for COMS Flight Dynamics System (FDS) and its test result in terms of the performance of the automation jobs. FDA controls the flight dynamics functions such as orbit determination, orbit prediction, event prediction, and fuel accounting. The designed FDA is independent from the specific characteristics which are defined by spacecraft manufacturer or specific satellite missions. Therefore, FDA could easily links its autonomous job control functions to any satellite mission control system with some interface modification. By adding autonomous system along with flight dynamics system, it decreases the operator's tedious and repeated jobs but increase the usability and reliability of the system. Therefore, FDA is used to improve the completeness of whole mission control system's quality. The FDA is applied to the real flight dynamics system of a geostationary satellite, COMS and the experimental test is performed. The experimental result shows the stability and reliability of the mission control operations through the automatic job control.

• 한국항공우주학회지
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• 제30권1호
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• pp.147-154
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• 2002

발사체의 발사 시험과 운용에 있어, 예기치 못한 로켓의 오작동으로 인한 인명과 재산의 피해를 예방 또는 최소화하기 위하여 비행안전 시스템은 매우 중요한 역할을 한다. KSR-Ⅲ 발사시 처음으로 운용될 비행안전 시스템은 비행안전 디스플레이 시스템과 비행종단 시스템으로 나뉘어진다. 발사 후 비행중인 로켓의 여러 비행상태와 예상낙하점등은 실시간으로 디스플레이 시스템을 통하여 관찰되며, 로켓이 안전영역을 벗어나거나 로켓의 추적이 불가능하게 될 경우 비행종단시스템은 로켓의 비행을 즉시 중단시키는 역할을 한다. 본 논문에서는 비행안전 시스템 구현에 관하여 수행된 실시간 비행안전 디스플레이 시스템과 비행종단시스템의 개발에 관하여 기술하고 있다.

• 한국경영과학회:학술대회논문집
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• 한국경영과학회/대한산업공학회 1999년도 춘계공동학술대회:정보화시대의 지식경영
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• pp.89-90
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• 1999

• 한국국방경영분석학회지
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• 제37권1호
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• pp.119-128
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• 2011

이 연구는 무인항공기 체계운용 효과도를 고려한 임무분석연구를 다룬다. 이 임무분석절차는 (1) 기본 MANA 모델 시나리오 생성, (2) 실험계획에 의한 입력변수조합 설계, (3) 기본 MANA 모델 시나리오와 설계된 입력변수조합과의 연결, (4) Data Farming 및 일괄처리에 의한 모델 수행, (5) 모델 수행결과의 통계분석 등 5단계로 이루어진다. 임무분석결과로 독립변수의 종속변수(운용 효과도)에 영향을 마치는 정도는 식별거리, 탐지 폭, 비행고도, 비행속도, 센서 개구각, 식별확률 순으로 작아지고, 기준 시나리오를 개선된 시나리오로 변경하여 운용할 경우 운용효과가 10.2% 증가할 수 있음을 제시한다.

• 한국국방경영분석학회지
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• 제30권1호
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• pp.153-167
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• 2004

This study focuses on building the wartime air operation model to evaluate the airfield capability. There are some uncertainties in the process of air operation such as mission flying time, turn around time, mission damage or kill rate, weather condition, and so on. Airplanes, on the way to the airbase after completing mission flight, may have been in queue on the holding point due to the unusable condition of airfield. And then, they may sometimes need to go other airbases due to the shortage of fuel. Under those uncertainties, this model is to evaluate the airfield capability in the wartime air operation using simulation.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.300-303
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• 2004

KOMPSAT-2 satellite mission operations and control system has been developed by ETRI. The system functional architecture, analysis and design, implementation, and tests are presented in this paper.