• Journal of the Korean Society for Aviation and Aeronautics
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• v.25 no.3
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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.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.14 no.2
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• pp.1-8
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• 2006

Unsteady lift measurements were carried out in order to investigate the effects of phase difference and reduced frequency of a dragonfly-type model with two pairs of wing. A load-cell was employed to measure the lift generated by a plunging motion of the dragonfly-type model with the incidence angles of 0$^{circ}$. Experimental conditions are as follows: phase differences between fore- and hind-wings are 0$^{circ}$, 90$^{circ}$, 180$^{circ}$, and 270$^{circ}$, and reduced frequencies are 0.075, 0.15 and 0.225, respectively. The freestream velocity was 143 m/sec and corresponding chord Reynolds number was $3.4{\times}10^3$. The variation of phase-averaged lift coefficients during one cycle of the wing motion is presented. Results show that the total value of the positive lift coefficient during one cycle of the wing motion is the largest at the phase difference of 90$^{circ}$, and that the maximum lift coefficient and lift coefficient per unit of time increases with reduced frequency.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.4
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• pp.8-16
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• 2009

An experimental study was carried out to investigate aerodynamic characteristics on reduced frequency of flapping wings. The half span of the wing is 28cm, and the mean chord length of wing is 10cm. In flight, the Reynolds Number range of birds is about $10^4$, and the reduced frequency during a level flight is 0.25. The experimental variables of present study were set to have similar conditions with the bird flight's one. The freestream velocities in a wind tunnel were 2.50, 3.75 and $5.00^m/s$, and the corresponding Reynolds numbers were $1.7{\times}10^4$, $2.5{\times}10^4$ and $3.3{\times}10^4$, respectively. The wing beat frequencies of an experimental model were 2, 3 and 4Hz, and the corresponding reduced frequency was decided between 0.1 and 0.5. Aerodynamic forces of an experimental flapping model were measured by using 2 axis load-cell. Inertial forces measured in a vacuum chamber were removed from measuring forces in the wind tunnel in order to acquire pure aerodynamic forces. Hall sensors and laser trigger were used to make sure the exact position of wings during the flapping motion. Results show that the ratio of downstroke in a wing beat cycle is increased as a wing beat frequency increases. The instantaneous lift coefficient is the maximum value at the end of downstroke of flapping wing model. It is found that a critical reduced frequency with large lift coefficient is existed near k=0.25.

• Journal of Aerospace System Engineering
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• v.17 no.2
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• pp.16-25
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• 2023

There are various types of foreign object debris (FOD) in the aviation industry. Tools lost by workers can act as a risk factor throughout aircraft operation, manufacturing, and maintenance fields. Accidents caused by tools lost due to workers' carelessness continue to occur throughout the aviation industry. Aviation-related institutions such as FAA and EASA have established tool control regulations and systems to prevent FOD occurrence. However, in Korea, related regulations and procedures are insufficient. A systematic and effective tool control system is required for reliable manufacturing, airworthiness, operation, and maintenance of aircraft. In this paper, tool control regulations and procedures of domestic and foreign air traffic authorities and aviation industry-related organizations were studied. A wireless communication-based tool control system was proposed based on the NAS 412's tool control regulations certified by the National Standards Association.

• Proceedings of the Korean Institute of Information and Commucation Sciences Conference
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• 2006.05a
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• pp.410-414
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• 2006

In the present, Orthogonal Frequency Division Multiple Access (OFDMA) that wireless access scheme for high speed data transmission is noticed in mobile communication market and OFDMA/TDD scheme will be used combining Time Division Duplex (TDD) scheme based on OFDMA. The Base Station's receiver synchronizes the symbol timing to anyone user's symbol and the other user's symbols have some Symbol Timing Offset (STO). Linear phase shift is occurred by each user's STO in an OFDMA symbol and the Multiple Access Interference (MAI) caused by the summation of each user's linear phase shift degrades the performance of ranging code detection. In this paper, we analyze the ranging code detection performance for each users STO in OFDMA/TDD system. Simulation results show that the more users access and mobile speed increase, the more ranging code detection performance degrades.

• Journal of Advanced Navigation Technology
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• v.9 no.1
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• pp.41-47
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• 2005

In this paper, the performances of various channel estimation schemes for DVB-H system are investigated. The linear interpolation, the second order interpolation, the cubic spline interpolation, and the time-domain interpolation, which are used in frequency domain, are chosen as the channel estimation schemes. We derived the performances of Mean Square Error (MSE), Bit Error Rate (BER), and the complexity of calculation in Rayleigh and Rician fading channel through computer simulations. From the simulation results, the cubic spline interpolation shows the best performance under high $E_b/N_0$ environments.

• Proceedings of the Korea Electromagnetic Engineering Society Conference
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• 2005.11a
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• pp.397-400
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• 2005

In this paper, folded PIFA is proposed by using folding the end point of PIFA for the automobile DMB antenna. By turning down the end point on the opposite side of shortstrip, resonance frequency is presented at not $\lambda$/4 but $\lambda$/10. So the folded PIFA has size reduction effect approximately 60 % as compared to the conventional PIFA. Also by using the parasitic patch, folded PIFA provides wide band performance. As a result, the designed antenna can be in the application of Digital Multimedia Broadcasting(180 $\sim$ 210 MHz) antenna for the automobile.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.4
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• pp.102-108
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• 2015

According to various researches, one of main causes of flight accidents is influence of human factors. It is important to collect and analyze event data in advance to minimize and prevent human errors by developing safety checklist. As a result international aviation industry developed Flight Operations Quality Assurance for commercial airliners, and, upon its proven effectiveness, it is now highly recommended to adopt for helicopter operations. Consequently, S government organization instituted Helicopter Flight Operations Quality Assurance system in 2012. Hence, this study conducted regression analysis of S organization's flight event frequency and applied ICAO SMS Matrix to categorize the severity of the events according to international standards. Based on the analysis, this research derived fundamental checklist factors for helicopter, which can be a proactive measure for safe operation.

• Journal of the Korean Society of Surveying, Geodesy, Photogrammetry and Cartography
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• v.30 no.6_2
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• pp.607-613
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• 2012

Ionospheric anomaly is one of the major error sources which deteriorate the GNSS performance. In the equatorial region, effects of the ionospheric plasma bubbles are of great interest because they are pretty common phenomena, especially in the period of the high solar activity. In order to evaluate the GNSS performance under circumstance of the bubbles, an ionospheric scintillation monitor has been developed and installed in Bangkok, Thailand. Furthermore, a model simulating the ionospheric delay and scintillation due to the bubbles has been developed. Based on these developments, the effects of the simulated plasma bubbles are analyzed and their agreement with the real observation is demonstrated. An availability degradation of the GPS ground based augmentation system (GBAS) caused by the bubbles is exampled in details. Finally, an integrated GPS/INS approach based on the Doppler frequency is proposed to remedy the deterioration.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.29 no.3
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• pp.84-99
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• 2021

Flight data from operational quality assurance programs plays a significant role in identifying factors as one of the key data in the development of proactive and preventive aviation safety management technologies based on data. The list of events in the flight quality assurance program recommended by the FAA differs from the list set and managed by airlines themselves and is based on the frequency of occurrence rather than the severity of individual events. In this work, we compared the list of FOQA events presented by the FAA with the list of some domestic airlines. We also investigate the severity priorities of events for airline captains and conduct research on how to improve the operation of the operational quality assurance program.