• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.12
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• pp.971-980
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• 2021

Recently popularized drone technologies have revealed that low-cost small unmanned aerial vehicles(UAVs) can be a significant threat to prevailing power by operating in group or in swarms. Researchers in many countries have tried to utilize integrated swarm unmanned aerial system(SUAS) in the battlefield. Agency for Defense Development also identified four core technologies in developing SUAS: swarm control, swarm network, swarm information, and swarm collaboration, and the authors started researches on swarm control and network technologies in order to be able to operate vehicle platforms as the first stage. This paper introduces design and integration of SUAS consisting of small fixed-wing UAVs, swarm control and network algorithms, a ground control system, and a launcher, with which swarm control and network technologies have been verified by flight tests. 19 fixed-wing UAVs succeeded in swarm flight in the final flight test for the first time as a domestic research.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.40 no.9
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• pp.760-770
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• 2012

In order to provide precision approach service based on GBAS, air navigation service providers should validate the GBAS system performance against international standard requirements and receive approval. The GBAS manufacturer should define integrity threat, analyze the integrity monitors and evaluate performance of the implemented monitors to verify integrity performance which is critical to the aircraft safety. This paper describes a statistical test result to evaluate performance of the code carrier divergence monitors implemented in KARI Integrity Monitor System software. The paper introduces analysis and test procedure which is developed for the performance evaluation and describes the analysis, the test scenario generation and the test results. The results show that the implemented monitors can detect the expected minimum detectable errors with satisfying the probability of missed detection requirements.

• 대한예방의학회:학술대회논문집
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• 1998.10b
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• pp.227-228
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• 1998

• Applied Chemistry for Engineering
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• v.27 no.1
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• pp.39-44
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• 2016

This study was to investigate the characteristics of combustion toxic gases of pinus rigida specimens treated with chemical additives such as pyrophosphoric acid (PP)/ammonuium ion ($NH_4{^+}$), methylenepiperazinomethyl-bis-phosphonic acid (PIPEABP) and $PIPEABP/NH_4{^+}$. Each pinus rigida plates was painted in three times with 15 wt% of each chemical additives in the aqueous solution. After drying these specimens at room temperature, the production of combustion gases and smoke was examined by the cone calorimeter (ISO 5660-1). As a result, the peak mass loss rate time (PMLR time) treated with chemicals was delayed upto 10.5~47.4% compared to that of using untreated specimen. In addition, the peak production of carbon monoxide ($CO\;_{peak}$) of 32.1~71.4% and total smoke release rate (TSRR) of 15.6~43.6% for test pieces treated with the chemical additive were higher than that of using the virgin plate. In particular, for the specimens treated with the chemical additive, the rate of smoke release (RSR) 29.4~41.5% was obtained higher than that of untreated plate except the specimen treated with $PP/4NH_4{^+}$. It can thus be concluded that the treatment using the chemical additive could partially increase the combustion-retardation properties of the species when compared to those of the virgin plate.

• Journal of Advanced Navigation Technology
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• v.19 no.4
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• pp.288-298
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• 2015

For the commercialization of unmanned aircraft, we must validate the safety of the air/ground collision alert systems (CAS). The validation procedure of CAS requires the flight test which is not only expensive but also dangerous. To alleviate this problem, we need the simulation based validation process for the CAS. We developed an integrated UAV simulation (IUS) environment which interconnect the flight simulator, the Matlab/Simulink, and a target avionics simulation model. We developed the collision warning module of the TCAS and tested using IUS and flight encounter models. Using IUS, we can evaluate the performance and reliability of a target avionic system at the preliminary design stage of a development life cycle.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2021.11a
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• pp.136-138
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• 2021

본 논문은 경남무인선박 규제자유특구 혁신사업육성 실증 사업의 일환으로 선박해양플랜트연구소(KRISO) 주관으로 수행한 연구 개발 사업의 실증 시험 수행 및 성과에 관련된 내용임. 선박해양플랜트연구소 무인선 아라곤2호와 3호에 적용한 원격관제 시스템의 고도화 및 성능개선 관련 연구개발 수행 중이다.

• Proceedings of the Korea Committee for Ocean Resources and Engineering Conference
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• 2004.05a
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• pp.54-54
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• 2004

• Korean Journal of Acupuncture
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• v.25 no.3
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• pp.43-51
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• 2008

배경 : 최근까지 이루어진 천식의 침치료 무작위 대조군 연구들에 의한 결과는 뚜렷한 효과를 보여주지 못하고 있다. 이러한 요인의 하나로 적절한 피험자 수를 정하기 위한 예비 임상시험의 부재가 거론되고 있다. 따라서 천식에 대한 침치료의 본 임상시험에 앞서 이의 실행 가능성 및 규모를 예측하는 예비임상시험이 필요한 상황이다. 목적 : 예비임상시험을 통해 서양의학적 치료를 받고 있는 천식환자들에 대한 침치료의 부가적 효과를 검증하기 위한 본 임상시험의 실현 가능성을 예측하기 위함. 방법 : 본 시험은 무작위 단일 맹검 대조군 평행 설계 예비 임상시험이다. 1차 평가변수는 최대 호기량 검사기로 집에서 아침, 저녁으로 매일 측정한 수치로 구해진 최대 호기 유속 일중 변동률의 1주간 평균치 변화이며 2차 평가변수는 의료기관에서 시행하는 폐기능 검사, 기준시점 호흡곤란 지수, 호흡곤란 변화에 대한 지수, 천식환자들의 삶의 질 평가를 위한 설문 등이다. 피험자 수는 총 45명으로 선정 및 제외기준을 통해서 참여하게 되며 1주간의 최대 호기 유속 기저치 평가 기간을 거친 후 진짜침 처치 군, 가짜침 처치 군, 대기군 세 군에 각각 무작위로 15명씩 할당된다. 모든 피험자에게 기존의 천식관련 약물의 사용을 허용하며, 진짜침 처치군 및 가짜침 처치군은 주 3회 4주간 해당 처치를 받고 2주 후에 각 평가 항목에 대하여 추적, 관찰하게 된다. 대기군은 기존의 천식관리를 유지하면서 2주마다 방문하여 총 6주간 평가를 받고 진짜침 처치를 4주간 받게 된다. 고찰 : 본 연구는 국내에서 최초로 이루어지는 천식에 대한 침 무작위 대조군 예비 임상시험으로 향후 적절한 피험자 수와 실행가능성을 예측할 수 있으리라 기대된다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.784-788
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• 2011

Wind tunnel test on 20" class propellers are carried out at KARI's low speed wind tunnel (LSWT). The test was done to select most efficient propeller for middle size electric propulsion UAV of KARI. The propellers are commercially available 20" class folding type propellers made of carbon fiber composite material. As the result, 21"${\times}$15.5" propeller was selected whose efficiency is 66% at cruise condition.

• Aerospace Engineering and Technology
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• v.3 no.1
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• pp.27-34
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• 2004

Tail-wing, gondola and thrust motor mount(EMS) were built by carbon/glass fiber composites. Structural strength & stiffness was verified by specimen tests. Static strength tests for each structural components were conducted separately. Boundary conditions are specially designed for each components to simulate exact joint conditions. Tests shows no detriment deformation at 100% DLL and no failure at 150% DLL.