• Journal of the Korean Society of Propulsion Engineers
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• v.4 no.3
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• pp.29-37
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• 2000

Because the previous design procedure for the composite wind turbine blade structure using trial and error method takes long time, a improved design procedure by using the program based on classical laminate theory was proposed to reduce the inefficient element. According to the improved design procedure, limitation of strains, stresses and displacements specified by international standard specification IEC1400-1 for the composite wind turbine blade were applied to sizing the structural configuration by using the rule of mixture and the principal stress design technique with a simplified turbine blade. Structural safety for strength and buckling stability was confirmed by the developed analysis program based on the laminate theory to minimize the design procedure. After modifying the preliminary design result with additional structural components such as skin, foam sandwich and mounting joints, stresses, strains, displacements, natural frequency, buckling load and fatigue life were analyzed by the finite element method. Finally these results were confirmed by comparing with IEC1400-1 specification.

• Journal of Advanced Navigation Technology
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• v.27 no.1
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• pp.50-56
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• 2023

INS(Inertial Navigation System) calculates navigation information using a vehicle's acceleration and angular velocity without the outside information. However, when navigation is performed for a long time, navigation error gradually diverges and the performance decreases. To enhance INS's performance, the rotation of inertial measurement unit is developed to compensate error sources of inertial sensors, which is called RINS(Rotational Inertial Navigation System). This paper analyzes the influence of several errors for dual-axis RINS and the shows the results using simulation.

• Proceedings of the Korean Information Science Society Conference
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• 2004.10c
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• pp.508-510
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• 2004

저궤도 위성은 고도가 낮아 하루에도 지구주위를 여러 번 회전해야 하고 주로 극궤도로 운영되므로 지상국과 접촉할 수 있는 시간에 상당한 제약을 가진다. 따라서 저궤도 위성의 경우 대부분의 시간을 지상의 모니터링이나 제어 없이 스스로 임무수행에 필요한 기능을 유지하면서 위성에서 생성되는 각종 데이터를 저장해 두었다가 다음 번 지상과의 접촉에서 위성의 실시간 상태정보 및 저장된 데이터들을 지상으로 송신하고 수행해야 할 임무를 지상명령으로 수신하는 과정을 통해서 운명된다. 본 논문은 국내 대표적인 저궤도 위성인 다목적실용위성 2호의 비행소프트웨어에서 위성의 실시간 상태정보 및 대용량 메모리에 저장된 데이터를 지상으로 전송하기 위한 전송제어 소프트웨어 및 전송 제어절차에 대해서 서술하였다.

• Journal of the Korean Institute of Telematics and Electronics
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• v.12 no.5
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• pp.6-11
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• 1975

반복형 그래이 부호 중 14진 및 16진 부호용 디지트 절차(digit sequence 또는 DS)의 여러가지 특성에 관하여 논하였으며 그것들을 통일적으로 기적할 수 있는 PDS는 각각 31종 및 11종이 있다는 것을 명백히 하였다. 그리고 이 PDS들에 회전변환과 순렬변환을 실시하여 얻을 수 있는 DS의 총수와 각종 특수 DS의 성질에 관하여도 논하였으며 대칭형 DS를 이용한 14진 및 16진 GC Counter를 설계하여 그것들의 동작을 실험에 의하여 확인하였다. Investigations on some characteristics of Tetra-Decimal and Hexa-Decimal recycling Gray co de (GC)-digit sequence(DS) are carried out, and, 31 and 11 kinds of prime digit sequence(PDS) are proposed respectively. From these PDS, by means of rotational conversion and permutational conversion, the numbers of all DS are obtained, and also the characteristics of some special DS are studied. Tetra Decimal and Hexa-decimal GC counters are designed using symmetrical DS, and, their operations are experimentally verified.

• Journal of the Korean Institute of Gas
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• v.21 no.4
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• pp.16-20
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• 2017

Current maintenance system are unable to suggest solid basis of maintenance for roating and static equipment. When a filure occurs, replacement or repair without proper process of failure cause analysis would often result in even greater risk. Therefore in this study, a procedure of Reliability Centred Maintenance is develped in order to perform maintenance in preventive mainer (PM), and to effectively manage risk of any equipment based on failure types and respective rates of failure. Ultimately an equipment with higher risk will be monitored which will lead to effectively prevent and manage any major accident.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2002.05a
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• pp.574-577
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• 2002

In this paper, we propose a new symbol time synchronization scheme suitable for the OFDM system with an interpolator. The proposed performs the following three steps. In the first step, the coarse symbol time synchronization is achieved by continuously measuring the average power of the received envelope signal. Based on this average power, the detection possibility for the symbol time synchronization is determined. If the signal is sufficient for synchronization, we next perform a relatively accurate symbol time synchronization by measuring the correlation a short training signal and the received envelope signal. Finally, an additional frequency synchronization is performed with a long training signal to correct symbol synchronization errors caused by the phase rotation. From the simulation results, one can see that the proposed synchronization scheme provides a good synchronization performance over frequency selective channels.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2018.11a
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• pp.71-77
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• 2018

선미도등대의 등명기는 1940년에 제작되어 역사적인 가치가 뛰어난 등명기이나, 수은조식 회전 장치의 노후로 수은이 장기간 누출되어 근무자의 중금속 중독이 우려되므로 이를 회수하여 적법한 절차에 의하여 처리하고, 노후 된 회전장치 및 전구교환기, 균열이 발생한 프리즘 렌즈(보호대 포함)를 보수, 복원, 개량하여 등명기의 역사적인 가치를 보존함은 물론 항로표지로서의 기능 유지에 만전을 기하고자 선미도등대 등명기 정비사업을 실시하였다. 본 논문은 동 사업의 준비단계부터 최종준공까지의 추진방안 및 결과 등 주요사항들을 고찰하고 공유하여 향후 역사적인 등명기의 보존 및 개선 사업 추진에 있어 참고가 되고자 한다.

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.1-6
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• 2020

The flaw tolerance evaluation requirement prescribed in Federal Aviation Regulation (FAR) §29.571 Amendment 55 was established in 2012. As a result, there are not many datas of flaw tolerance evaluation. This paper introduces the series of processes and evaluation methods carried out for certification based on the flaw tolerance evaluation. An initial flaws were artificially formed on the main rotor actuator and then the damage tolerance test was performed, which was twice life time of design requirements, to demonstrate that the main rotor actuator of the rotorcraft is sufficiently capable of flaw tolerance.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.4
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• pp.259-267
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• 2022

The existing method of deriving the fail-safe design requirements for the domestic developed rotary-wing aircraft system may miss the factors that cause critical system function failures, when being applied to the latest integrated avionics system. It is because the existing method analyzes the severity effect of the failures caused by a single item. To solve the issue, we present a systematic analysis procedure for deriving fail-safe design requirements of system architecture by utilizing functional hazard assessment and development assurance level analysis of SAE ARP4754A, international standard for complex system development. To demonstrate that our proposed procedure can be a solution for the aforementioned issue, we set up experimental environments that include common factors that can cause critical function failures of a system, and we conducted a cross-validation with the existing method. As a result, we showed that the proposed procedure can identify the potential critical common factors that the existing method have missed, and that the proposed procedure can derive fail-safe design requirements to control the common factors.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.5
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• pp.391-398
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• 2016

This study focused on the aerodynamic loads of the horizontal axis wind turbine blade due to the normal turbulence inflow condition. Normal turbulence model (NTM) includes the variations of wind speed and direction, and it is characterized by turbulence intensity and standard deviation of flow fluctuation. IEC61400-1 recommends the fatigue analysis for the NTM and the normal wind profile (NWP) conditions. The aerodynamic loads are obtained at the blade hub and the low speed drive shaft for MW class horizontal axis wind turbine which is designed by using aerodynamically optimized procedure. The 6-components of aerodynamic loads are investigated between numerical results and load components analysis. From the calculated results the maximum amplitudes of oscillated thrust and torque for LSS with turbulent inflow condition are about 5~8 times larger than those with no turbulent inflow condition. It turns out that the aerodynamic load analysis with normal turbulence model is essential for structural design of the wind turbine blade.