• Journal of Astronomy and Space Sciences
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• 제33권4호
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• pp.323-333
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• 2016

In this study, the uncertainty requirements for orbit, attitude, and burn performance were estimated and analyzed for the execution of the $1^{st}$ lunar orbit insertion (LOI) maneuver of the Korea Pathfinder Lunar Orbiter (KPLO) mission. During the early design phase of the system, associate analysis is an essential design factor as the $1^{st}$ LOI maneuver is the largest burn that utilizes the onboard propulsion system; the success of the lunar capture is directly affected by the performance achieved. For the analysis, the spacecraft is assumed to have already approached the periselene with a hyperbolic arrival trajectory around the moon. In addition, diverse arrival conditions and mission constraints were considered, such as varying periselene approach velocity, altitude, and orbital period of the capture orbit after execution of the $1^{st}$ LOI maneuver. The current analysis assumed an impulsive LOI maneuver, and two-body equations of motion were adapted to simplify the problem for a preliminary analysis. Monte Carlo simulations were performed for the statistical analysis to analyze diverse uncertainties that might arise at the moment when the maneuver is executed. As a result, three major requirements were analyzed and estimated for the early design phase. First, the minimum requirements were estimated for the burn performance to be captured around the moon. Second, the requirements for orbit, attitude, and maneuver burn performances were simultaneously estimated and analyzed to maintain the $1^{st}$ elliptical orbit achieved around the moon within the specified orbital period. Finally, the dispersion requirements on the B-plane aiming at target points to meet the target insertion goal were analyzed and can be utilized as reference target guidelines for a mid-course correction (MCC) maneuver during the transfer. More detailed system requirements for the KPLO mission, particularly for the spacecraft bus itself and for the flight dynamics subsystem at the ground control center, are expected to be prepared and established based on the current results, including a contingency trajectory design plan.

• 한국가스학회지
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• 제19권6호
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• pp.22-27
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• 2015

최근 고고도 장기체공 무인기의 개발이 활발하게 진행되고 있는 가운데, 중량당 에너지 밀도가 높아서 왕복동 엔진의 연료로서 적합한 수소 연료를 적용하는 것이 경제성과 기술성 측면에서 유리한 것으로 검토되었다. 본 연구에서는 2.4리터급 왕복동 가솔린엔진을 수소엔진으로 개조하기 위하여 수소연료를 공급하기 위한 실험장치를 구축하고 수소연료 공급이 가능한 인젝터를 장착하였으며 범용 엔진제어기를 이용하여 엔진을 구동시킴으로써 시동 및 공회전 시의 연소 특성을 파악하였다. 안전하게 엔진 시동성을 확보하였고 공회전 상태를 유지할 수 있는 조건을 탐색하였다. 또한 공회전 상태에서 공연비와 점화 타이밍을 변경해보면서 연소 안정성을 비롯한 기본적인 연소 특성을 살펴봄으로써 향후 수소엔진을 활용한 무인기의 동력원을 개발하기 위한 기초를 마련하였다.

• Korean Journal of Geomatics
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• 제2권1호
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• pp.47-55
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• 2002

Remote sensing is the science and art of obtaining information about an object, area or phenomenon through the analysis of data acquired by a device that is not in contact with the object, area, or phenomenon under investigation./sup 1)/ EOC (Electro -Optical Camera) sensor loaded on the KOMPSAT-1 (Korea Multi- Purpose Satellite-1) performs the earth remote sensing operation. EOC can get high-resolution images of ground distance 6.6m during photographing; it is possible to get a tilt image by tilting satellite body up to 45 degrees at maximum. Accordingly, the device developed in this study enables to obtain images by photographing one pair of tilt image for the same point from two different planes. KOMPSAT-1 aims to obtain a Korean map with a scale of 1:25,000 with high resolution. The KOMPSAT-1 developed automated feature extraction system based on stereo satellite image. It overcomes the limitations of sensor and difficulties associated with preprocessing quite effectively. In case of using 6, 7 and 9 ground control points, which are evenly spread in image, with 95% of reliability for horizontal and vertical position, 3-dimensional positioning was available with accuracy of 6.0752m and 9.8274m. Therefore, less than l0m of design accuracy in KOMPSAT-1 was achieved. Also the ground position error of ortho-image, with reliability of 95%, is 17.568m. And elevation error showing 36.82m was enhanced. The reason why elevation accuracy was not good compared with the positioning accuracy used stereo image was analyzed as a problem of image matching system. Ortho-image system is advantageous if accurate altitude and production of digital elevation model are desired. The Korean map drawn on a scale of 1: 25,000 by using the new technique of KOMPSAT-1 EOC image adopted in the present study produces accurate result compared to existing mapping techniques involving high costs with less efficiency.

• 한국임상수의학회지
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• 제36권1호
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• pp.23-29
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• 2019

While research findings suggest that the highly pathogenic avian influenza (HPAI) is the leading cause of economic loss in Korean poultry industry with an estimated cumulative impact of $909 million since 2003, identifying the environmental and anthropogenic risk factors involved remains a challenge. The objective of this study was to identify areas at high risk for potential HPAI outbreaks according to the likelihood of HPAI virus detection in wild birds. This study integrates spatial information regarding HPAI surveillance with relevant demographic and environmental factors collected between 2003 and 2018. The Maximum Entropy (Maxent) species distribution modeling with presence-only data was used to model the spatial risk of HPAI virus. We used historical data on HPAI occurrence in wild birds during the period 2003-2018, collected by the National Quarantine Inspection Agency of Korea. The database contains a total of 1,065 HPAI cases (farms) tied to 168 unique locations for wild birds. Among the environmental variables, the most effective predictors of the potential distribution of HPAI in wild birds were (in order of importance) altitude, number of HPAI outbreaks at farm-level, daily amount of manure processed and number of wild birds migrated into Korea. The area under the receiver operating characteristic curve for the 10 Maxent replicate runs of the model with twelve variables was 0.855 with a standard deviation of 0.012 which indicates that the model performance was excellent. Results revealed that geographic area at risk of HPAI is heterogeneously distributed throughout the country with higher likelihood in the west and coastal areas. The results may help biosecurity authority to design risk-based surveillance and implementation of control interventions optimized for the areas at highest risk of HPAI outbreak potentials.

• Advances in aircraft and spacecraft science
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• 제6권2호
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• pp.117-144
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• 2019

High Altitude and Long Endurance (HALE) aircraft are capable of providing intelligence, surveillance and reconnaissance (ISR) capabilities over vast geographic areas when equipped with advanced sensor packages. As their use becomes more widespread, the demand for additional range, endurance and payload capability will increase and designers are exploring non-conventional configurations to meet the increasing demands. One such configuration is the joined-wing concept. A joined-wing aircraft is one that typically connects a front and aft wings in a diamond shaped planform. One such example is the Boeing SensorCraft configuration. While the joined-wing configuration offers potential benefits regarding aerodynamic efficiency, structural weight, and sensing capabilities, structural design requires careful consideration of elastic buckling resulting from the aft wing supporting, in compression, part of the forward wing structural loading. It has been shown already that this is a nonlinear phenomenon, involving geometric nonlinearities and follower forces that tend to flatten the entire configuration, leading to structural overload due to the loss of the aft wing's ability to support the forward wing load. Severe gusts are likely to be the critical design condition, with flight control system interaction in the form of Gust Load Alleviation (GLA) playing a key role in minimizing the structural loads. The University of Victoria Center for Aerospace Research (UVic-CfAR) has built a 3-meter span scaled and flexible wing UAV based on the Boeing SensorCraft design. The goal is to validate the nonlinear structural behavior in flight. The main objective of this research work is to perform Ground Vibration Tests (GVT) to characterize the dynamic properties of the scaled flight vehicle. Results from the experimental tests are used to characterize the modal dynamics of the aircraft, and to validate the numerical models. The GVT results are an important step towards a safe flight test program.

• 한국추진공학회지
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• 제23권1호
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• pp.124-131
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• 2019

가스터빈엔진 고도시험설비 운용특성탐색 및 설비튜닝 연구와 유량/추력 측정방안 검증을 위한 엔진 시뮬레이션덕트 설계 연구를 수행하였다. 설비 운용특성 검증은 배압/추력 제어가 필요하므로 Spikecone type의 가변노즐을 적용하였으며, 유량검증용 ISO 쵸킹노즐의 추가장착이 가능토록 설계하였다. 시뮬레이션덕트 주유로 면적은 1D Sizing으로 결정하고, 노즐면적변화에 따른 시뮬레이션덕트 내부 유동특성은 1D/CFD 해석으로 조사하였으며, 해석결과로부터 설비운용특성 탐색 및 유량/추력 검증시험을 위한 공기공급부 시험조건을 도출하였다. Spike 노즐 구동부는 시험 전운용 구간에서 공력하중조건을 견디도록 모터, 리니어 볼스크류 등의 부품모델을 선정하였으며, 시험 시 10 mm/s의 이송속도가 가능하도록 설계하였다.

• 한국항공우주학회지
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• 제50권7호
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• pp.489-496
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• 2022

본 논문에서는 한국항공대학교에서 설계 및 개발한 태양광 무인기인 KAU-SPUAV의 시스템을 소개하고 비행시험을 통하여 성능을 검증하였다. 두 가지 버전의 태양광 무인기의 제원과 전장 구성 그리고 지상 관제 시스템을 소개하였다. 제시한 시스템으로 전파맵 구축, 제주도 해안선 일주 그리고 장기 체공 비행의 세 가지 임무 비행을 수행하였다. 각 임무는 태양광 무인기의 특성을 이용하는 비행으로서 주로 장시간 및 장거리 임무로 구성되었다. 본 연구를 통하여 태양광 무인기의 장기체공 능력을 이용해 다양한 임무에 사용될 수 있음을 보였다. 비행 시험 결과를 기반으로 시스템 추가 개선을 통하여 성능 향상을 도모할 수 있음을 확인하였다.

• 한국전자통신학회논문지
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• 제17권5호
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• pp.767-774
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• 2022

본 논문에서는 우리나라에서 운용 중인 4개 제조사 윈드프로파일러의 성능 평가 및 품질관리의 방향성을 제시하기 위해 원시 스펙트럼 자료를 분석하였다. 계절별로 평균한 스펙트럼의 프로파일과 파워 스펙트럼 밀도(PSD, Power Spectrum Density)로 산출한 4가지 통계값(최소, 평균, 중앙, 최댓값)의 프로파일을 활용하였다. 스펙트럼 자료의 품질은 LAP-3000이 가장 우수하였고, YKJ3, PCL-1300, CLC-11-H가 뒤를 이었다. 철원과 추풍령에 설치된 PCL-1300은 지형과 비기상 신호로 인한 스펙트럼의 변동성이 커서 지형 클러터 제거와 이동평균, 멀티피크 등의 신호처리 과정이 요구되었다. 군산과 파주에 설치된 CLC-11-H는 직류 치우침과 전파거리 접힘 현상이 발견되어 직류 치우침 제거와 관측 유효 고도 제한이 선행될 필요가 있다.

• 우주기술과 응용
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• 제2권2호
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• pp.121-136
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• 2022

선박 통신에 있어서 선박자동식별시스템(automatic identification system)은 연안 해역의 선박 운항 모니터링, 선박 간의 항해 안전을 위한 정보 교환뿐만 아니라 해상관제 수단에도 필요하다. 그러나 이는 대략 160 MHz의 very high frequency (VHF) 대역을 사용함과 동시에 지구의 곡률로 인해 통신 거리의 한계가 존재한다. 이를 인공위성을 통해 해결하고 있지만, 저궤도의 초소형 위성에 대해서는 아직 많은 작업이 이루어지지 않았다. 본 논문에서는 소프트웨어 정의 라디오(SDR)를 활용하여 초소형위성용 선박정보수집장치의 수신시험을 증명하였다. R820T2 SDR을 활용하여 부산항에 정박해 있는 선박으로부터 AIS(automatic identification system) 데이터를 수집하였고, Adalm-Pluto와 매트랩 시뮬링크를 활용하여 이를 송신할 수 있는 환경을 구축하였다. 또한 감쇠기를 활용하여 위성까지 신호세기가 약해지는 과정을 모사하였다. 일련의 과정을 통해 AIS 탑재체에서 AIS 데이터의 수신 성공 여부를 시연하였다.

• Wind and Structures
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• 제38권2호
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• pp.129-146
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• 2024

Aiming at the problem of non-stationary wind field simulation of downbursts, a non-stationary down-burst generation system was designed by adding a nozzle and program control valve to the inlet of the original wall jet model. The computational fluid dynamics (CFD) method was used to simulate the downburst. Firstly, the two-dimensional (2D) model was used to study the outflow situation, and the database of working conditions was formed. Then the combined superposition of working conditions was carried out to simulate the full-scale measured downburst. The three-dimensional (3D) large eddy simulation (LES) was used for further verification based on this superposition condition. Finally, the wind tunnel test is used to further verify. The results show that after the valve is opened, the wind ve-locity at low altitude increases rapidly, then stays stable, and the wind velocity at each point fluctuates. The velocity of the 2D model matches the wind velocity trend of the measured downburst well. The 3D model matches the measured downburst flow in terms of wind velocity and pulsation characteris-tics. The time-varying mean wind velocity of the wind tunnel test is in better agreement with the meas-ured time-varying mean wind velocity of the downburst. The power spectrum of fluctuating wind ve-locity at different vertical heights for the test condition also agrees well with the von Karman spectrum, and conforms to the "-5/3" law. The vertical profile of the maximum time-varying average wind veloci-ty obtained from the test shows the basic characteristics of the typical wind profile of the downburst. The effectiveness of the downburst generation system is verified.