• 대한산업공학회지
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• 제3권2호
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• pp.73-81
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• 1977

Mission effectiveness, which is the probability of successfully completing the assigned mission, is introduced as an appropriate measure of effectiveness for a military system. The model of mission effectiveness is developed for a system which is required to carry out various types of a mission. Each mission type is characterized by the maximum allowable time that determines the success of a given mission type. A given type of a mission is successful if and only if (i) the system is available at the start of a mission and (ii) the system completes its mission within the maximum allowable duration of time that this given mission type specifies without any failure during this period. Both analytic and simulation approaches are employed. Difficulties involved in the anayticl approach are discussed. The model is proposed as a useful tool for consistent system evaluation and optimum test design.

• 한국항공우주학회지
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• 제48권7호
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• pp.537-546
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• 2020

우주발사체 개발과정에서 설계와 프로세스의 성능지표로 활용되는 신뢰도는 발사 성공률로 유효성이 확인되고, 반복된 발사를 통해 수집된 데이터는 신뢰도 관리를 위하여 피드백 되어야 한다. 본 논문에서는 전 세계 우주발사체의 발사 이력을 조사하여 발사체 모델이나 발사 운용을 통한 기술 성숙도에 따른 발사 성공률을 비교 분석하였고, 사전정보를 반영한 사전확률분포에 발사를 통해 관측된 데이터를 업데이트하는 베이지안 기법을 적용하여 다음 발사에서 예상되는 성공률을 추정하였다. 여러 유형의 사전확률분포를 사용하여 추정한 발사 성공률과 전통적인 통계 기법을 통해 산출한 성공률을 비교 분석하여 적절한 사전분포를 설정하는 방안을 검토하였고, 베이지안 기법을 적용하여 미래의 발사 성공률을 예측하기 위해 고려할 사항들을 제시하였다.

• Journal of Astronomy and Space Sciences
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• 제37권3호
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• pp.187-197
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• 2020

In order to avoid the high cost and high risk of demonstration mission of rendezvous-docking technology, missions using nanosatellites have recently been increasing. However, there are few successful mission cases due to many limitations of nanosatellites like small size, power limitation, and limited performances of sensor, thruster, and controller. To improve the probability of rendezvous-docking mission success using nanosatellite, a rendezvous-docking phase analysis tool for nanosatellites is developed. The tool serves to analyze the relative position and attitude control of the chaser satellite at the docking phase. In this tool, the Model Predictive Controller (MPC) is implemented as a controller, and Extended Kalman Filter (EKF) is adopted as a filter for noise filtering. To verify the performance and effectiveness of the developed tool for nanosatellites, simulation study was conducted. Consequently, we confirmed that this tool can be used for the analysis of relative position and attitude control for nanosatellites in the rendezvous-docking phase.

• 산업경영시스템학회지
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• 제38권4호
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• pp.11-21
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• 2015

In order to achieve success in ground operations, searching for moving targets is one of critical factors. Usually, the system of searching for adversary ground moving targets has complex properties which includes target's moving characteristics, camouflage level, terrain, weather, available search time window, distance between target and searcher, moving speed, target's tactics, etc. The purpose of this paper is to present a practical quantitative method for effectively searching for infiltrated moving targets considering aforementioned complex properties. Based upon search theories, this paper consists of two parts. One is infiltration route analysis, through terrain and mobility analysis. The other is building dynamic probability maps through Monte Carlo simulation to determine the prioritized searching area for moving targets. This study primarily considers ground moving targets' moving pattern. These move by foot and because terrain has a great effect on the target's movement, they generally travel along a constrained path. With the ideas based on the terrain's effect, this study deliberately performed terrain and mobility analysis and built a constrained path. In addition, dynamic probability maps taking terrain condition and a target's moving speed into consideration is proposed. This analysis is considerably distinct from other existing studies using supposed transition probability for searching moving targets. A case study is performed to validate the effectiveness and usefulness of our methodology. Also, this study suggests that the proposed approach can be used for searching for infiltrated ground moving target within critical time window. The proposed method could be used not only to assist a searcher's mission planning, but also to support the tactical commander's timely decision making ability and ensure the operations' success.

• 한국항공우주학회지
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• 제43권6호
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• pp.488-496
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• 2015

본 연구에서는 각각 다른 목적지에서 다수의 임무를 수행해야하는 복수 무인항공기(Unmanned Aerial Vehicle, UAVs)의 경로를 결정할 때, 무인항공기의 생존가능성을 고려하여 경로를 결정하는 프레임워크를 제안하였다. 본 라우팅 문제는 무인항공기 안전과 임무 완료시간 간의 trade-off 를 나타내는 비용 매트릭스를 이용한 차량경로문제(Vehicle Routing Problem, VRP)로 정의할 수 있다. 특정위치에서 무인항공기의 위험 레벨은 감지될 확률과 격추될 확률을 고려하여 모델링 하였고, 위협 레벨과 비행거리를 고려한 두 지역간의 최소비용경로는 육각형격자(Hexagonal cells)에서 Dijkstra 알고리듬을 사용하여 결정하였다. 또한, 지속적으로 다수의 적을 감시 정찰하는 임무를 수행하는 복수 무인항공기의 최적경로를 결정하는 case study를 수행하였으며, 그 결과를 논의하였다.

• 항공우주기술
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• 제13권1호
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• pp.166-173
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• 2014

최근 쿼드콥터에 대한 관심이 증가하면서 방송에서 군에 이르기까지 다양한 분야에서 활용되고 있다. 특히 다수의 쿼드콥터를 동시에 제어하는 군집 비행 연구는 중요 임무 수행 성공 확률을 높일 수 있고, 예술과 융합되어 군무를 수행하는 등 다양한 응용에 활용될 수 있다. 본 논문에서는 AR.Drone을 활용하여 실내에서 모션 캡쳐 기반으로 다수의 비행체가 서로의 위치를 파악하고, 시나리오에 맞춰 정해진 임무를 수행하기 위해 개발된 군집 비행 시스템을 소개한다.

• 한국군사과학기술학회지
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• 제7권3호
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• pp.59-68
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• 2004

Unmanned surface vehicles(USVs) have been developed for special operations in foreign navies. These will be employed to conduct critical missions including inspection, coast guard, ISR, fire protection, precision strike, mine interception warfare and antisubmarine warfare. It is also known the USVs will be deployed at the front line of the network-centric warfare to replace the manned naval operations. The unmanned operation can, thus, minimize unnecessary risk to personnel and enhance the success probability for the imposed mission. In this research, the USVs which are under operation and development in foreign navies are investigated. Based on this, an USV with $7\~10m$ of length and 10ton of weight for the Korean Navy which can be deployed near the Northern Limit Line(NLL), is proposed.

• 시스템엔지니어링학술지
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• 제10권2호
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• pp.71-79
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• 2014

To enhance success probability of a system development project, its overall risk level should be minimized through systematically managing schedules, costs, and technical performances. However, Attempts to manage technical performance compared to numerous efforts to control costs and schedules in such projects are deficient. Particularly, a space launch vehicle, a large complex system, development project is much less likely to meet its technical performance objectives due to its technological difficulty, along with schedule delay and cost overrun. The technical performance management (TPM) is a method for tracking and managing technical progress in order to achieve technical performance targets within schedule and budget. In this paper, we investigate applications of the TPM in several space launch vehicle development projects. Then we propose and validate the TPM process to achieve a successful mission in such projects.

• 제어로봇시스템학회논문지
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• 제21권9호
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• pp.888-897
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• 2015

A flight capability to take a terrain following flight near the ground is required to reduce the probability that a fighter aircraft can be detected by foe's radar fence in the battlefield. The success rate for mission flight has increased by adopting TFS (Terrain Following System) to enable the modern advanced fighter to fly safely near the ground at the low altitude. This system has applied to the state-of-the-art fighter and bomber, such as B-1, F-111, F-16 E/F and F-15, since the research begins from 1960's. In this paper, the terrain following system and GCAS (Ground Collision Avoidance System) was developed, based on a digital database with UTAS's TERPRROM (TERrain PROfile Matching) equipment. This system calculates the relative location of the aircraft in the terrain database by using the aircraft status information provided by the radar altimeter and the INS (Inertial Navigation System), based on the digital terrain database loaded previously in the DTC (Data Transfer Cartridge), and figures out terrain features around. And, the system is a manual terrain following system which makes a steering command cue refer to flight path marker, on the HUD (Head Up Display), for vertical acceleration essential for terrain following flight and enables a pilot to follow it. The cue is based on the recognized terrain features and TCH (Target Clearance Height) set by a pilot in advance. The developed terrain following system was verified in the real-time pilot evaluation in FA-50 HQS (Handling Quality Simulator) environment.