• 한국정보통신학회논문지
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• 제17권2호
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• pp.355-362
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• 2013

TOF(Time-Of-Flight) 센서에 의해 획득된 정보로부터 3차원 깊이 영상(depth image)을 추출하기 위한 위상 연산기의 하드웨어 구현을 기술한다. 설계된 위상 연산기는 CORDIC(COordinate Rotation DIgital Computer) 알고리듬의 vectoring mode를 이용하여 arctangent 연산을 수행하며, 처리량을 증가시키기 위해 pipelined 구조를 적용하였다. 고정 소수점 MATLAB 모델링과 시뮬레이션을 통해 최적 비트 수와 반복 횟수를 결정하였다. 설계된 위상 연산기는 MATLAB/Simulink와 FPGA 연동을 통해 하드웨어 동작을 검증하였으며, TSMC 0.18-${\mu}m$ CMOS 셀 라이브러리로 합성하여 약 16,000 게이트로 구현되었고, 200MHz@1.8V로 동작하여 9.6 Gbps의 연산 성능을 갖는 것으로 평가되었다.

• 한국압력기기공학회 논문집
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• 제10권1호
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• pp.15-19
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• 2014

A Failure or degradation of reactor upper head penetration is a recurring problem due to long term operation at nuclear power plants. And a flaw in the reactor upper head penetration has caused unplanned plant shutdown for repair as well as high economic impact on the plants. Consequently, a detection of flaws is of the utmost importance. Prior to the replacement of reactor upper head penetration, some utilities have repaired the flaws of reactor upper head penetration generated by overlay weld. Until now, only the base metal in reactor upper head penetration has been inspected according to 10 CFR 50.55a and ASME code case N-729-1. Accordingly, it is difficult to detect manufacturing defects and repair defects in overlay weld. This paper presents a case study on the application of Time of Flight Diffraction technique for reactor head penetration mockup with artificial flaws in overlay weld. This study offers a way to understand the flaws detected in reactor upper head penetration overlay weld.

• 한국항공운항학회지
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• 제15권4호
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• pp.24-32
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• 2007

In this study, computational structural vibration analyses of a smart unmanned aerial vehicle (SUAV) with tilt-rotors due to dynamic hub loads have been conducted considering detailed supporting structures of installed equipments. Three-dimensional dynamic finite element model has been constructed for different fuel conditions and tilting angles corresponding to helicopter, transition and airplane flight modes. Practical computational procedure for modal transient response analysis is successfully established. Also, dynamic loads generated by rotating blades and wakes in the transient and forward flight conditions are calculated by unsteady computational fluid dynamics technique with sliding mesh concept. As the results of present study, transient structural displacements and accelerations of the vibration sensitive equipments are presented in detail. In addition, vibration characteristics of structures and installed equipments of which safe operation is normally limited by the vibration environment specifications are physically investigated for different flight conditions.

• 한국항공운항학회지
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• 제25권3호
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• pp.74-80
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• 2017

As for A rotary wing aircraft, the configuration change about split yaw swaged rod was executed to improve hit treat capability for dealing with a long rod. The purpose of this study was to analyze if or not the quality of the split yaw swaged rod was obtained, and so the flight safety was ensured or not. Buckling analysis, Coupling Thread Strength Analysis, Thermal Stress analysis and Rod Natural Frequency Analysis were executed for structural analysis. The results of the analysis were presented that the split rod had the sufficient margin of safety and so there were no anomalies in the limit load and no failures in the ultimate load. And there were no resonances in result of natural frequency analysis. In conclusion, this study showed that the split yaw swaged rod had structural safety, so flight safety of rotary wing aircraft was secured and there was no problem in aircraft operation. It is certain that the technology of splitting the yaw swage rod will contribute to the operational Safety of the rotary wing aircraft in the future.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 춘계학술대회논문집
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• pp.546-551
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• 2001

Space Test Department at KARI(Korea Aerospace Research Institute) plans to carry out the GVT(Ground Vibration Test) for the KSR(Korea Sounding Rocket)-III FM(Flight Model) which is being developed by Space Technology R＆D Division. KSR-III will be an intermediate to the launch vehicle capable of carrying satellites to their orbits. GVT offers very important information to predict the behavior of KSR in its operation, and to develop the flight control and aerodynamic analysis. For development of test facilities, testing and analysis methods which can be used for the future test, Space Test Department has performed the GVT with KSR-II PFM(Proto-Flight Model) at Satellite Integration ＆ Test Center of KARl This paper discusses the procedures, techniques and the results of it. In this test, to simulate free-free condition, test object hung in the air by 4 bungee cords specially devised. The GVT was carried out using pure random excitation technique with MIMO(Multi-Input-Multi-Output) method with three electromagnetic shakers, and poly-reference parameter estimation was used to identify the modal parameters. As the result of the test, 11 mode shapes and modal parameters below 200㎐ were identified and compared with analytical results.

• Journal of Astronomy and Space Sciences
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• 제35권3호
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• pp.119-131
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• 2018

In spite of a short history of only 30 years in space development, Korea has achieved outstanding space development capabilities, and became the $11^{th}$ member of the "Space Club" in 2013 by launching its own satellites with its own launch vehicle from a local space center. With the successful development and operation of more than 10 earth-orbiting satellites since 1999, Korea is now rapidly expanding its own aspirations to outer space exploration. Unlike earth-orbiting missions, planetary missions are more demanding of well-rounded technological capabilities, specifically trajectory design, analysis, and navigation. Because of the importance of relevant technologies, the Korean astronautical society devoted significant efforts to secure these basic technologies from the early 2000s. This paper revisits the numerous efforts conducted to date, specifically regarding flight dynamics and navigation technology, to prepare for future upcoming planetary missions in Korea. However, sustained efforts are still required to realize such challenging planetary missions, and efforts to date will significantly advance the relevant Korean technological capabilities.

• 한국군사과학기술학회지
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• 제14권3호
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• pp.405-413
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• 2011

Defense Systems Test Center in ADD supports increasingly various missile test requirements such as higher altitude event, multi target operation and low-altitude, high velocity target tracking. In this paper, we have proposed the development of instrumentation radar tracking status simulator based on virtual reality. This simulator can predict the tracking status and risk of failure using several modeling algorithms. It consists of target model, radar model, environment model and several algorithms includes the multipath interference effects. Simulation results show that the predict tracking status and signal are similar to the test results of the live flight test. This simulator predicts and analyze all of the status and critical parameters such as the optimal site location, servo response, optimal flight trajectory, LOS(Line of Sight). This simulator provides the mission plan with a powerful M&S tool to rehearse and analyze instrumentation tracking radar measurement plan for live flight test at DSTC(Defense Systems Test Center).

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2013년도 추계학술대회
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• pp.350-353
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• 2013

본 논문에서는 TOF(Time-Of-Flight) 센서에 의해 얻어진 정보로부터 3차원 깊이 영상(depth image)을 추출하기 위한 위상 연산기의 하드웨어 구현을 제안한다. 설계된 위상 연산기는 DCORDIC(Differential COordinate Rotation DIgital Computer) 알고리듬의 vectoring mode를 이용하여 Arctangent 연산을 수행하며, 처리량과 속도를 늘리기 위해 redundant binary 수체계와 pipelined 구조를 적용하였다. 제안된 알고리듬은 고정 소수점 MATLAB 시뮬레이션을 통해 검증하고 최적 데이터 비트 수 및 반복 횟수를 결정하였다. 설계된 위상 연산기는 MATLAB/Simulink와 FPGA 연동을 통해 가상의 3차원 데이터 복원 동작을 검증하였으며, 469 MHz의 클록 주파수로 동작하여 7.5 Gbps의 성능을 갖는 것으로 평가되었다.

• 한국항공운항학회지
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• 제27권4호
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• pp.1-8
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• 2019

Recently, development of long endurance electric powered airplane has been conducted worldwidely. Light structural weight of a main wing with sufficient structural integrity is essential for long endurance flight. Since a main wing with a slender spar can occur catastrophic fracture under the flight, it is important to establish a design and verification method for both the weight reduction and structural integrity. In this paper, structural design and analysis of the main wing of HALE UAV with tubular spar reinforced with a bulkhead were introduced. The static strength test of the main wing was performed to verify structural integrity under the static load. Then, the experimental result was compared with an analytical result from a finite element analysis. It was concluded that the developed light weight main wing would have sufficient structural integrity under the flight operation.

• 한국항공운항학회지
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• 제17권2호
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• pp.62-67
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• 2009

LOSA is a flight safety program that analyses human errors in normal operations. Trained pilot observers monitor the normal flights at the observer seat. LOSA is a proactive non jeopardy data collection tool using threat and error management(TEM) as a framework. With the analysis of crew behaviors through LOSA with The LOSA collaborative(TLC), the airlines can identify the behaviors of the crew during normal operations. The major objective of LOSA is to measure how the crew manage threats, errors and undesired aircraft deviations in the cockpit on day to day operations. The airlines are able to set up effective TEM training with practical six generation Crew recourse management(CRM) with data of error from LOSA instead of theoretical CRM courses. The Airlines can use TEM as an integral part of a Safety Management System(SMS) and uses monitoring and cross-checking skills in the flight operations to manage threats and errors effectively when we know the errors we make in the cockpit on daily operation. The result of LOSA indicates that the error detection rate should be enhanced since around the half of the errors went undetected. The areas which should be focused for enhancing the error detection are monitor, cross-check, the management of workload, automation and taxiway/ runway to manage errors effectively.