• 대한전기학회논문지:시스템및제어부문D
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• 제55권9호
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• pp.414-419
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• 2006

This paper presents a design of a multi-sensor data fusion filter for a Flight Test System. The multi-sensor data consist of positional information of the target from radars and a telemetry system. The data fusion filter has a structure of a federated Kalman filter and is based on the Singer dynamic target model. It consists of dedicated local filter for each sensor, generally operating in parallel, plus a master fusion filter. A fault detection and correction algorithms are included in the local filter for treating bad measurements and sensor faults. The data fusion is carried out in the fusion filter by using maximum likelihood estimation algorithm. The performance of the designed fusion filter is verified by using both simulation data and real data.

• 한국건설순환자원학회논문집
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• 제3권2호
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• pp.109-114
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• 2015

최근 CCPs를 대량 활용하는 HVFA 콘크리트에 관한 연구가 활발히 이루어지고 있다. 초기에는 주로 재료적인 분야에 대해서만 수행되어지고 있는 실정이었으나 최근 들어 HVFA 시멘트 콘크리트의 구조재료로의 적용을 위한 탄성계수, 응력-변형률 관계 및 구조 부재 거동 등에 대한 연구가 수행되고 있다. 이러한 일련의 연구 결과를 바탕으로 실물 구조 부재로의 적용성 평가를 위하여 지간길이 7.5m의 50% 다량 첨가된 플라이애시 시멘트 철근콘크리트 보 2개를 제작한 후, 휨 및 전단에 대한 구조거동 실험을 수행하여 HVFA 콘크리트의 실 구조물로의 적용성을 확인하고자 하였다. 실험결과에 의하면, HVFA 콘크리트의 응력-변형률 관계는 기존 연구 결과와 실험결과와의 다소 차이가 있지만 설계에 적용하기에는 큰 무리가 없는 것으로 나타났으며, 처짐, 변형률 등의 양상이 플라이애시를 첨가하지 않는 일반 콘크리트와 유사하게 나타나, 50% 플라이애시 시멘트 콘크리트 부재 부재의 휨 거동은 크게 차이나지 않는 것으로 나타났다. 또한 실험에서 구해진 콘크리트의 전단강도는 설계 식에서 구해진 콘크리트의 전단강도와 유사하게 나타나, 기존 설계식을 준용하여도 큰 무리가 없을 것으로 예상된다.

• 한국유체기계학회 논문집
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• 제15권4호
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• pp.27-32
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• 2012

Gas turbines for an aircraft have the start and restart capabilities within their flight envelop. It is an important item for engine qualification and substantiated with the test. Experimental investigations were carried out to find the relation between the corrected torque and the corrected rotating speed of an air turbine starter in this study. A dedicated air supply system for the air turbine starter and a special device to measure the torque and the rotating speed of the air turbine starter were developed and installed at the altitude engine test facility in Korea Aerospace Research Institute. Experimental results show that the relations between the corrected torque and the corrected rotating speed of the air turbine starter are linear and the inlet temperature and pressure conditions for the air turbine starter were found out to provide minimum required torque for the engine qualification test at various altitude. The start and restart tests for the currently developing engine were successfully performed using this experimental results.

• 방사성폐기물학회지
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• 제2권1호
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• pp.23-34
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• 2004

To validate the previous conceptual design of cover system, construction of the engineered barrier test facility is completed and the performance tests of the disposal cover system are conducted. The disposal test facility is composed of the multi-purpose working space, the six test cells and the disposal information space for the PR center. The dedicated detection system measures the water content, the temperature, the matric potential of each cover layer and the accumulated water volume of lateral drainage. Short-term experiments on the disposal cover layer using the artificial rainfall system are implemented. The sand drainage layer shows the satisfactory performance as intended in the design stage. The artificial rainfall does not affect the temperature of cover layers. It is investigated that high water infiltration of the artificial rainfall changes the matric potential in each cover layer. This facility is expected to increase the public information about the national radioactive waste disposal program and the effort for the safety of the planned disposal facility.

• 한국산업융합학회 논문집
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• 제25권2_2호
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• pp.309-314
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• 2022

The bonding strength [ISO22674] test was conducted by firing a dedicated ceramic powder on the surface of the dental titanium material treated with micro-arc oxidation. In the test group, an average result value of 34.34 MPa was obtained, and in the control group, a result value of 21.53 MPa was obtained. The bonding strength of the test group was higher than that of the control group by 12.81 MPa, resulting in a 37% improvement in durability of the dental artificial tooth ceramic restoration.

• 한국산학기술학회논문지
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• 제19권6호
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• pp.104-109
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• 2018

일반적으로 변속기 전체에 대한 내구시험을 통하여 파킹 락 기어의 내구성을 평가한다. 파킹 락 기어 부품 하나의 내구시험에 대한 시험 기준은 부재한 상황이다. 따라서 본 연구에서는 파킹 락 기어의 내구시험 기준을 자체적으로 설정하여, 내구 성능시험을 수행하였다. 파킹 락 기어의 항복응력을 구하기 위해 정적 파단 시험을 수행하였고, 항복응력의 60%를 내구시험 조건으로 설정하였다. 설정된 시험조건으로 100만회의 반복내구 성능시험을 수행하였다. 또한, 내구 성능시험을 수행하기 위하여, 전용 지그를 제작하였다. 제작된 지그가 정적 파단시험에서 파손되어, 파손된 지그에 대한 유한요소해석을 수행하고 설계를 변경하였다. 수정한 지그를 제작하여 자체적으로 설정한 시험기준으로 내구 성능시험을 수행한 결과, 파킹 락 기어는 본 조건에 충족하였다. 본 연구에서 수행된 시험과 해석을 통하여 파킹 락 기어의 성능 및 내구 한계에 대한 기초 데이터를 확보하였고, 이러한 기초 데이터는 파킹 락 기어의 설계와 개발에 중요한 기초 자료로 활용될 것으로 사료된다.

• 항공우주시스템공학회지
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• 제9권2호
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• pp.25-33
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• 2015

Global market of unmanned aircraft(UA) is rapidly expending based on the versatile and efficient utility of the UA. Domestically many industries, universities and research institutes are trying to do research and development of the UA in various angle of aspect. In spite of these effort, all the participants of research and development of the UA has been suffering the difficulty of acquiring the airspace around vicinity of Goheung airfield for the flight test of UA. Although the current procedure of execution of the flight test of UA is set after acquiring the airspace by applying the NOTAM(Notice To Air Man) to the Ministry of Land, Infrastructure and Transport(MLIT) at least 7 days before the flight test and commencing with the publication of the NOTAM by MLIT, if the flight test is carried out as planned, changing or reapplying the NOTAM expends mort time and makes difficulty often. Therefore it is needed that a restricted airspace for the flight test of UA is established and make all the executioner of flight test uses the exclusive airspace without limitation. This research proposes the restricted airspace with short term and long term establish requirement of airspace separately. The short term requirement has been established with the airspace of 10 nm radius and 8,000 ft altitude in which the requirements of flight test can be carried out more than 90% without needs of supplement of the additional airspace. The long term has been established within the airspace of 30 nm radius which is the maximum Radio Line Of Sight(RLOS) and 8,000 ft altitude with exclusion of current air way, airport control area, approaching corridor to the airport, existing restricted area(RA) and Military Operating Area(MOA) for the purpose of minimizing inconvenience of the other airspace user. Once establishing the exclusive airspace for the flight test of UA, research and development of industries, universities and research institutes will be more vigorous and contributes to the national economy.

• Structural Monitoring and Maintenance
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• 제7권4호
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• pp.319-344
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• 2020

Inverse analysis of non-linear reinforced concrete bridge pier using recursive Gaussian filtering for in-situ condition assessment is the main theme of this work. For this purpose, minimum variance unbiased estimation using unscented sigma points is adopted here. The uniqueness of this inverse analysis lies in its approach for strain based updating of engineering demand parameters, where appropriate bound and constrained conditions are introduced to ensure numerical stability and convergence. In this analysis, seismic input is also identified, which is an added advantage for the structures having no dedicated sensors for earthquake measurement. First, the proposed strategy is tested with a simulated example whose hysteretic properties are obtained from the slow-cyclic test of a frame to investigate its efficiency and accuracy. Finally, the experimental test data of a full-scale bridge pier is used to study its in-situ condition in terms of Park & Ang damage index. Overall the study shows the ability of the augmented minimum variance unbiased estimation based recursive time-marching algorithm for non-linear system identification with the aim to estimate the engineering damage parameters that are the fundamental information necessary for any future decision making for retrofitting/rehabilitation.

• 드라이브 ㆍ 컨트롤
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• 제15권3호
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• pp.14-20
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• 2018

Wet clutches in an automatic transmission enable the transmission of the engine power by the frictional torque experienced and noted between disk and plates. Since the clutch frictional torque considerably affects the shift quality of an automatic transmission as well as the durability of the machinery, its friction characteristics must be carefully examined to meet the design requirements. The SAE No. 2 friction test machine is a well-known standard to evaluate mainly the friction characteristics of plate clutches along with the required automatic transmission fluids. This paper reviews the experimental analysis of the wet clutch friction characteristics by using the exclusively developed clutch test machine which is capable of controlling the clutch test procedure, in accordance with the applicable test standard and processing of the experimental data automatically. As the clutch test machine is designed for the accommodation of dual clutches which is applied to the real transmission, it can evaluate not only the clutch friction characteristics, but also an actuation performance of a measured clutch piston. In respect to friction characteristics involving dynamic friction coefficients, the energy absorbed in a clutch disk and the recorded temperatures of clutch plates during braking actions and procedures are also investigated. Additionally, the change of friction coefficients by the use of the repeated clutch application is also observed with the endurance test functions of an accurately calibrated and dedicated clutch test machine.

• Advances in aircraft and spacecraft science
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• 제9권3호
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• pp.195-215
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• 2022

The increasing interest in CubeSat platforms ant their capability of enlarging the frontier of possible missions impose technology improvements. Miniaturized electrical propulsion (EP) systems enable new mission for multi-unit CubeSats (6U+). While electric propulsion systems have achieved important level of knowledge at equipment level, the investigation of the mutual impact between EP system and CubeSat technology at system level can provide a decisive improvement for both the technologies. The interaction between CubeSat and EP system should be assessed in terms of electromagnetic emissions (both radiated and conducted), thermal gradients, high electrical power management, surface chemical deposition, and quick and reliable data exchanges. This paper shows how a versatile CubeSat Test Platform (CTP), together with standardized procedures and specialized facilities enable the acquisition fundamental and unprecedented information. Measurements can be taken both by specific ground support equipment placed inside the vacuum facility and by dedicated sensors and subsystems installed on the CTP, providing a completely new set of data never obtained before. CTP is constituted of a 6U primary structure hosting the EP system, representative CubeSat avionics and batteries. For the first test campaign, CTP hosts the ambipolar plasma propulsion system, called Regulus and developed by T4I. After the integration and the functional test in laboratory environment, CTP + Regulus performed a Test campaign in relevant environment in the vacuum chamber at CISAS, University of Padua. This paper is focused on the test campaign description and the main results achieved at different power levels for different duration of the firings.