• Journal of Welding and Joining
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• 제33권5호
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• pp.9-13
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• 2015

Nickel alloy, especially Alloy 625, is used widely in industrial applications such as aerospace, chemical, petrochemical and marine applications due to their good mechanical properties, excellent fabricability, weldability and good corrosion resistance. Especially, it is obviously applied in FPSO's moon pool structure and caisson tubular of CPF under seawater environment. Recently, UNS S32654 was developed to substitute alloy 625 because of high cost price. In this study, mechanical properties and corrossive properties of UNS S32654 are reviewed and proposed its applications.

• 전자통신동향분석
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• 제33권6호
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• pp.1-11
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• 2018

Several industrial applications such as space exploration, aerospace, automotive, the downhole oil and gas industry, and geothermal power plants require specific electronic systems under extremely high temperatures. For the majority of such applications, silicon-based technologies (bulk silicon, silicon-on-insulator) are limited by their maximum operating temperature. Silicon carbide (SiC) has been recognized as one of the prime candidates for providing the desired semiconductor in extremely high-temperature applications. In addition, it has become particularly interesting owing to a Si-compatible process technology for dedicated devices and integrated circuits. This paper briefly introduces a variety of SiC-based integrated circuits for use under extremely high temperatures and covers the technology trend of SiC CMOS devices and processes including the useful implementation of SiC ICs.

• 대한기계학회논문집B
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• 제37권4호
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• pp.313-322
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• 2013

배터리는 최근 여러 분야에서 중요한 에너지원 역할을 하고 있는데, 사용 중 충방전을 거듭하면 용량이 점차 저하되며 초기 대비 80% 이하로 떨어지면 고장으로 간주되므로, 이를 예측하기 위한 수명 예측 기법이 활발히 개발되고 있다. 본 연구에서는 사용중인 배터리에 대해 충전곡선 기울기를 이용하여 배터리의 용량을 평가하고 이를 바탕으로 잔존수명을 예측하는 새로운 방법을 제안하였다. 이 과정에서 발생하는 여러 불확실성을 고려하기 위해 베이지안 접근법에 기반한 파티클 필터 방법을 활용하였고 그 결과 잔존수명을 확률분포로 구하였다. 개발된 방법을 미국 NASA Ames 연구소와 본 연구실에서 직접 수행한 배터리 충방전 시험 데이터에 대해 각각 적용한 결과 충전곡선 기울기가 용량 열화를 잘 나타내며 파티클 필터로 예측된 잔존수명 신뢰구간은 실제 수명을 잘 포함함을 확인할 수 있었다.

• 한국분말야금학회:학술대회논문집
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• 한국분말야금학회 2006년도 Extended Abstracts of 2006 POWDER METALLURGY World Congress Part 1
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• pp.317-317
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• 2006

• 한국고분자학회지:고분자과학과기술
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• 제22권3호
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• pp.230-236
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• 2011

• International Journal of Aeronautical and Space Sciences
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• 제15권4호
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• pp.345-355
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• 2014

This paper focuses on aerodynamic and inertial modeling of the propeller for its applications in flight dynamics analyses of a propeller-driven airplane. Unsteady aerodynamic and inertial loads generated by the propeller are formulated using the blade element method, where the local velocity and acceleration vectors for each blade element are obtained from exact kinematic relations for general maneuvering conditions. Vortex theory is applied to obtain the flow velocities induced by the propeller wake, which are used in the computation of the aerodynamic forces and moments generated by the propeller and other aerodynamic surfaces. The vortex lattice method is adopted to obtain the induced velocity over the wing and empennage components and the related influence coefficients are computed, taking into account the propeller induced velocities by tracing the wake trajectory trailing from each of the propeller blades. Aerodynamic forces and moments of the fuselage and other aerodynamic surfaces are computed by using the wind tunnel database and applying strip theory to incorporate viscous flow effects. The propeller models proposed in this paper are applied to predict isolated propeller performances under steady flight conditions. Trimmed level forward and turn flights are analyzed to investigate the effects of the propeller on the flight characteristics of a propeller-driven light-sports airplane. Flight test results for a series of maneuvering flights using a scaled model are employed to run the flight dynamic analysis program for the proposed propeller models. The simulations are compared with the flight test results to validate the usefulness of the approach. The resultant good correlations between the two data sets shows the propeller models proposed in this paper can predict flight characteristics with good accuracy.

• International Journal of Aeronautical and Space Sciences
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• 제15권4호
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• pp.356-365
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• 2014

This paper is the second in a series and aims to build a high-fidelity mathematical model for a propeller-driven airplane using the propeller's aerodynamics and inertial models, as developed in the first paper. It focuses on aerodynamic models for the fuselage, the main wing, and the stabilizers under the influence of the wake trailed from the propeller. For this, application of the vortex lattice method is proposed to reflect the propeller's wake effect on those aerodynamic surfaces. By considering the maneuvering flight states and the flow field generated by the propeller wake, the induced velocity at any point on the aerodynamic surfaces can be computed for general flight conditions. Thus, strip theory is well suited to predict the distribution of air loads over wing components and the viscous flow effect can be duly considered using the 2D aerodynamic coefficients for the airfoils used in each wing. These approaches are implemented in building a high-fidelity mathematical model for a propeller-driven airplane. Flight dynamic analysis modules for the trim, linearization, and simulation analyses were developed using the proposed techniques. The flight test results for a series of maneuvering flights with a scaled model were used for comparison with those obtained using the flight dynamics analysis modules to validate the usefulness of the present approaches. The resulting good correlations between the two data sets demonstrate that the flight characteristics of the propeller-driven airplane can be analyzed effectively through the integrated framework with the propeller and airframe aerodynamic models proposed in this study.

• 한국태양에너지학회:학술대회논문집
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• 한국태양에너지학회 2008년도 추계학술발표대회 논문집
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• pp.226-231
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• 2008

The heat transfer characteristics of a solar high-temperature receiver with heat pipes was investigated by numerical simulation. The concentration ratio of the solar receiver ranges 1000 and the concentrated heat is required to be transported to a certain distance for specific applications. This study deals with internal geometry variation of a solar receiver incorporating high-temperature heat pipe. The isothermal characteristics in the receiver section is of major concern. The diameter of the solar thermal receiver was 120 mm and the length was 400 mm. The angle of receiver end wall was varied between $0^{\circ}$ and $45^{\circ}$. The wall thickness of the heat pipe channel was 4mm and 48 axial channels of the same dimensions were attached to the outer wall of the receiver with even spacing in the circumferential direction. The channels are changed to high-temperature sodium heat pipes. Commercial softwares were employed to deal with the radiative heat transfer inside the receiver cavity and the conduction heat transfer along the channels. The numerical results are compared and analyzed from the view Point of high-temperature solar receiver.

• 우주기술과 응용
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• 제3권3호
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• pp.280-300
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• 2023

본 논문은 한국항공우주연구원에서 운영 중인 우주물체 충돌위험 관리시스템의 개발 및 운영 현황을 포함하고 있다. 현재 저궤도위성 6기, 정지궤도위성 3기에 대해 24시간 충돌위험을 모니터링하고 있으며, 필요 시 충돌회피기동을 통해 충돌위험을 완화하여 안전하고 안정적으로 운영하고 있다. 2007년 중국의 자국위성 요격실험 이후 본격적으로 우주물체와 운영위성 간 충돌위험을 모니터링하고 있으며, 신속하고 효율적으로 상황에 대처하기 위해 다양한 충돌위험 관리시스템을 개발해왔다. 본 논문에서는 2007년 이후 현재까지 개발된 우주물체 충돌위험 관리시스템에 대한 소개, 현재 지구주변의 인공우주물체 현황, 현재 운영 중인 시스템에 대해 기술하였으며, 나아가 앞으로의 전망과 향후 계획에 대해 소개하였다.

• 항공우주시스템공학회지
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• 제17권6호
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• pp.100-107
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• 2023

영구자석 동기전동기의 권선 개방 고장은 권선이 끊어지거나 인버터 스위치의 고장으로 발생한다. 권선 개방 고장이 발생하면 전동기에 토크리플과 진동이 발생하게 되며, 영구자석 동기전동기를 작동기로 사용하는 항공기 등을 포함하는 운행체의 안전성에 치명적인 영향을 미치게 된다. 따라서 신속한 고장 검출 및 분류가 필수적이다. 본 논문에서는 영구자석 동기전동기의 권선 개방 고장의 검출과 고장 위치 파악을 위한 분류 기법을 제안한다. 제안된 기법은 확장칼만필터를 통해 고장을 검출 후 다중모델 필터를 통해 고장을 분류한다.