• 한국추진공학회지
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• 제17권4호
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• pp.49-55
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• 2013

한국항공우주연구원 (이하 항우연)에서 개발중인 중형 전기동력 무인기 EAV2의 추진시스템에 대한 비행시험결과에 대하여 기술 하였다. EAV2는 날개 길이 6.9 m, 무게 18 kg의 저속 장기 체공형 무인기이다. 전기 동력원으로는 태양전지, 연료전지, 배터리의 세 가지를 동시에 사용한다. EAV2는 2012년 6월에 22시간 이상 체공 비행에 성공하였다. 시험 결과, 전기추진 시스템은 비행 중 일어나는 여러 상황에서 필요한 동력을 성공적으로 공급하였으며, 각 동력원들은 설계된 목적에 부합하게 작동되었다.

• 한국가시화정보학회지
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• 제2권2호
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• pp.58-65
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• 2004

The purpose of this visualization study is to investigate the effect of reduced frequency qualitatively by examining wake patterns for dragonfly flight motion. Dragonflies have two pairs of wing (a forewing and hindwing) and flight is achieved by a pitching and plunging, so it makes a separation over the wings. The separation affects the wake pattern and changed wake pattern has an influence on lift, drag, and propulsion. This experiment was conducted by using a smoke wire technique and a camera fixed above the test section used to take a photograph of the wake. An electronic device is mounted below the test section to find the exact mean positional angle of the wing. The reduced frequency in the experiment is 0.15, 0.3 and 0.45. Results show that reduced frequency is closely related to the wake pattern that determines flight efficiency.

• 전기학회논문지
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• 제64권7호
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• pp.1074-1080
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• 2015

In the last decades, the increasing interest in unmanned aerial vehicle(UAV) for military, surveillance, and rescue applications made necessary the development of flight control theory and body structure more and more efficient and fast. In this paper, we describe the design and performance of a prototype hexarotor UAV platform featuring an inertial measurement unit(IMU) based autonomous-flying for use in bluetooth communication environments. The proposed system comprises the construction of the test hexarotor platform, the implementation of an IMU, dynamic modeling and simulation in the hexarotor helicopter. Furthermore, the hexarotor helicopter with implemented IMU is connected with a micro controller unit(ARM-cortex) board. The P-PD control algorithm was used to control the hexarotor. We used the Matlab software to help us to tune the P-PD control parameters for quick response and minimizing the fluctuation. The control simulation and experiment on the real system are implemented in the test platform, evaluated and compared against each other.

• 대한기계학회:학술대회논문집
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• 대한기계학회 2008년도 추계학술대회A
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• pp.1566-1569
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• 2008

The flow visualization is conducted in order to investigate an unsteady flight characteristic of a model dragonfly. The flapping wings are analyzed using smoke-wire and high speed camera. The results of this experiment show that three mechanisms and high incidence angle of the wings are responsible for the lift. The leading edge vortex, which is induced by the rapid acceleration of the wing at the beginning of a stroke, causes the lift enhancement. The delayed stall during the stroke and the fast supination and pronation of the wing near the end of each stroke are also responsible for the lift generation.

• Wind and Structures
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• 제22권1호
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• pp.17-41
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• 2016

To address the uncertainty of the flight trajectories caused by the turbulence and gustiness of the wind field over the roof and in the wake of a building, a 3-D probabilistic trajectory model of flat-type wind-borne debris is developed in this study. The core of this methodology is a 6 degree-of-freedom deterministic model, derived from the governing equations of motion of the debris, and a Monte Carlo simulation engine used to account for the uncertainty resulting from vertical and lateral gust wind velocity components. The influence of several parameters, including initial wind speed, time step, gust sampling frequency, number of Monte Carlo simulations, and the extreme gust factor, on the accuracy of the proposed model is examined. For the purpose of validation and calibration, the simulated results from the 3-D probabilistic trajectory model are compared against the available wind tunnel test data. Results show that the maximum relative error between the simulated and wind tunnel test results of the average longitudinal position is about 20%, implying that the probabilistic model provides a reliable and effective means to predict the 3-D flight of the plate-type wind-borne debris.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 추계학술발표대회 논문집
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• pp.179-184
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• 2005

In the present study, conceptual design of the main wing for 20 seats WIG{wing in Ground Effect) flight vehicle, which will be a high speed maritime transportation system for the next generation, was performed. The high stiffness and strength Carbon-Epoxy material was used for the major structure and the skin-spar with a foam sandwich structural type was adopted for improvement of lightness and structural stability. As a design procedure for this study, firstly the design load was estimated with maximum flight load, and then flanges of the front and the rear spar from major bending load and the skin structure and the webs of the spars were preliminarily sized using the netting rules and the rule of mixture. In order to investigate the structural safety and stability, stress analysis was performed by Finite Element Codes such as NASTRAN/PA TRAN[6] and NISA II [7]. From the stress analysis results, it was confirmed that the upper skin structure between the front spar and rear spar was very unstable for the buckling. Therefore in order to solve this problem, a middle spar and the foam sandwich structure at the upper skin and the web were added. After design modification, even thought the designed wing weight was a little bit heavier than the target wing weight, the structural safety and stability of the final design feature was confirmed. Moreover, in order to fix the wing structure at the fuselage, the insert bolt type structure with six high strength bolts was adopted for easy assembly and removal.

• 한국기후변화학회지
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• 제5권1호
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• pp.61-70
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• 2014

최근 3년간 항공부문 온실가스 배출량은 연평균 5.7%씩 증가하고 있으며, 국민 소득수준 향상과 국제선 노선 확장 등 저비용 항공사의 성장가속화로 인해 운항 수요가 빠르게 증가하고 있어 항공부문 온실가스 배출량은 지속적으로 증가할 전망이다. 본 연구에서는 국적 A항공사의 2011년도 비행 데이터(FOQA)를 활용하여 비행단계별 연료소비 패턴과 Tier 3a급 온실가스 배출량을 산정하였으며, Tier 2 산정 방법 결과와 비교하였다. 대상 항공기는 보잉계열의 B737-600, B737-700, B737-800이었으며, 국내 노선은 김포-제주, 국제 노선은 인천-나리타를 주요 노선으로 선정하였다. 분석결과, 1회당 총 연료소비량은 김포-제주는 2,298~2,405 kg이고, 비행단계별로는 순항 78% 차지하였으며, 인천-나리타는 4,763~6,291 kg으로 순항 시 87% 차지하였다. 또한, B737-700의 경우, 1회당 평균 분당 연료소비량은 이륙단계에서 순항단계보다 2.6~3.0배 더 많이 소모되는 것으로 나타났다. 한편, Tier 3a급 배출량은 김포-제주는 1회당 평균 7톤, 인천-나리타 1회당 평균 16톤 발생되는 것으로 나타났으며, Tier 3a 방법이 Tier 2보다 2.7% 더 작게 산정된 것으로 나타났다. 이와 같은 통계는 항공기 운항절차별 감축 수단 이행 시 연료절감량과 감축량을 산출하는데 있어 중요한 기초자료로 활용되리라 판단된다.

• 로봇학회논문지
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• 제16권2호
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• pp.155-163
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• 2021

In this paper, we propose a four 2-link robotic leg landing system that is used for leveling the bottom of the landing system, even when the quadcopter posture is changed. The case of conventional skid type landing gear has a risk when the quadcopter lands on a moving vehicle because the skid type landing gear is tilted to the landing site at this situation. To solve this problem, it is necessary to level the bottom of the landing system when the quadcopter posture is changed in the flight. Therefore, the proposed landing system used a four 2-link robotic leg with leveling method. The leveling method was derived from the method of determining a plane. The superiority of the proposed system was verified with 6-axis stewart platform and real flight experiment, and it shows feasibility of leveling method and proposed landing system.

• Mass Spectrometry Letters
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• 제12권1호
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• pp.26-30
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• 2021

The impurity concentration is a crucial parameter for semiconductor thin films. Evaluating the impurity distribution in silicon thin film is another challenge. In this study, we have investigated the doping concentration of boron in silicon thin film using time of flight secondary ion mass spectrometry in dynamic mode of operation. Boron doped silicon film was grown on i) p-type silicon wafer and ii) borosilicate glass using hot wire chemical vapor deposition technique for possible applications in optoelectronic devices. Using well-tuned SIMS measurement recipe, we have detected the boron counts 101~104 along with the silicon matrix element. The secondary ion beam sputtering area, sputtering duration and mass analyser analysing duration were used as key variables for the tuning of the recipe. The quantitative analysis of counts to concentration conversion was done following standard relative sensitivity factor. The concentration of boron in silicon was determined 1017~1021 atoms/㎤. The technique will be useful for evaluating distributions of various dopants (arsenic, phosphorous, bismuth etc.) in silicon thin film efficiently.

• 항공우주기술
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• 제3권2호
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• pp.197-207
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• 2004

현재 개발중인 스마트 무인기는 일반적인 헬리콥터와 같이 수직이착륙이 가능할 뿐만 아니라 고정익기와 같이 고속의 비행이 가능함을 목표로 하고 있다. 그러므로 흡기구는 여러 비행조건에서 엔진이 제 효율을 낼 수 있도록 충분한 공기를 흡입하루 수 있어야 함은 물론이고 비행체의 운행속도에 따라서도 그 효율이 어느 이상 저하되지 않도록 설계되어야 한다. 본 논문에서는 고속 비행체에 적합한 pitot 형태와 엔진 특성에 따른 플레넘 챔버를 장착한 흡기구를 설계하였다. 그리고 CFD-ACE를 이용하여 설계된 흡기구의 성능 해석을 수행하였으며 엔진 내부에서의 swirl과 distortion을 조사하고 압력손실에 대해서 연구하였다.