• Journal of the Korean Society for Aviation and Aeronautics
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• v.23 no.1
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• pp.67-73
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• 2015

The previous limited authority system capable of implementing attitude command response type and translational command response type by operating SAS actuator has the problem of early saturation of SAS actuator since SAS actuator should compensate the mechanical linkage displacement caused by control sick movement. In this paper, a limited authority system where flight control computer receives the command from the control stick which is not connected to the mechanical linkage is described. In this system the compensation by the SAS actuator is not necessary and SAS actuator saturate later. SAS actuator saturation problem can be further relaxed by using the trim actuator. This new limited authority system is applied to BO-105 model, simulation is performed for the doublet input and pirouette maneuver is also simulated and analyzed.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2013.06a
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• pp.488-490
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• 2013

2013년 11월 27일 구성된 제주 민군복합형 관광미항 크루즈 선박조종 시뮬레이션 시현 TF팀은 2013. 1. 17~18일 한국해양과학기술원에서 3차원 다기능 선박조종시뮬레이터(Full Mission Ship-Handling Simulator)을 이용하여 도선사 4명이 주, 야간 및 입선, 출선자세 접안 16개 시나리오를 가지고 시뮬레이션을 실시하였으며, 평가 기법은 "해사안전법"의 해상교통안전진단 시행지침(국토해양부 고시 제2012-129호(2012.3.21.), 해상교통시스템 적정성 평가(선박조종시뮬레이션, 통항안전성 및 접 이안안전성 평가)를 준용하였다. 시뮬레이션 평가 결과 근접도에 따른 충돌[침범] 확률이 $10^{-4}$미만이고, 운항자[주관적] 평가의 결과가 평균 -2.0 이하로 해상교통환경 변화에 따른 통항안전성 및 접이안 안전성 확보가 가능하다고 평가되었다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2004.11a
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• pp.33-39
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• 2004

A ship runs with various modes of motion due to waves. Among the modes, roll mainly influences on the safety of cargos and crew's fatigue. Therefore a ship equipped with anti-rolling devices are on an increasing trend. In this research, we developed a free running model ship to evaluate the performances of fin stabilizer and moving weight stabilizer. Also those performance tests were carried out through the proposed test procedure.

• Proceedings of the Korean Association of Geographic Inforamtion Studies Conference
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• 2009.04a
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• pp.321-322
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• 2009

항공기에 장착되어 1개 지점을 수직 및 경사각도로 5면에서 촬영하는 항공용 다각촬영 카메라를 비롯한 항공용 멀티센서는 항공기라는 공간상의 제약으로 인해 다양한 각도로 센서를 고정하기에 어려움이 있다. 또한 항공기 운항 중 기류변화등으로 인해 촬영예상 지역을 벗어나 촬영되기 쉽다. 이에 항공용 센서의 자세를 연직방향으로 유지 시켜주는 기존 항공용 마운트를 활용할 수 있으면서, 다양한 각도로 센서를 고정할 수 있는 장치를 개발하였다.

• Bulletin of the Society of Naval Architects of Korea
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• v.32 no.1
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• pp.21-27
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• 1995

초고속선에 관련된 점성유동은 저한성능 향상과 운항자세 제어를 위해 사용되는 다양한 선체부 가물의 저항 예측과 초고속선에 많이 사용되는 물분사 추진장치 입구 형상의 설계 그리고 임펠 러에 이르는 덕트 유동의 예측을 중심으로 관심을 받아왔다. 본 소고에서는 통상적인 선박의 경우와는 구별되는 초고속선 고유의 점성유동 특성에 관하여 간략히 논의하기로 하고 내용을 크게 선체-부가물 점성유동과 물분사 추진장치에 관련되어 있는 덕트유동으로 나누어 기술하 였다.

• The Journal of the Korea Contents Association
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• v.19 no.11
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• pp.365-374
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• 2019

Loss of Control in Flight(LOC-I) due to aircraft upset attitude has the highest air accident rate, and International Aviation Institute such as ICAO and FAA recommended flight crew to operate aircraft safely through UPRT(Upset Prevention & Recovery Training) program. ICAO has selected Loss of Control(LOC) as key safety indicator, and recommended to respond using TEM(Threat and Error Management). However there are not much specific treats and errors classified for UPRT programs using real TEM based on evidences. This study intends to consider the importance of UPRT through the introduction of UPRT and accident analysis using TEM. Typical upset accidents were classified to common threats as IFR, inadequate training, Automation surprise, and inexperienced copilots. The common errors were cross-check, speed and altitude deviation, callouts, communication, thrust and stall action fail. The undesired aircraft states were inadequate automation mode, Deviation of speed and vertical, stall, and crash. These suggest areas to improve UPRT.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.10 no.1
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• pp.35-44
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• 2002

Inertial Navigation System(INS) has been used in the field of air navigation for a long time but is not popular in general aviation due to high price. Recently low-price GPS is available but vulnerable to radio interference. As an alternative on these problems, GPS/INS integrated navigation system has been considered. GPS/INS is capable of implementing navigation with low-price inertial sensors but its accuracy is dependent upon how much drift of INS may be calibrated by using GPS. In order to apply GPS/INS to air navigation, it must be investigated how long drift of INS in case of no GPS aiding will be bounded within requirements for safe flight. From the above motivation, the flight test for GPS/INS navigation system was conducted in order to make sense its performance in air navigation and its result was shown.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.26 no.2
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• pp.76-82
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• 2018

A test simulator is needed to develop a fuel quantity measurement system that takes into account the roll and pitch motion of the aircraft. In this paper, we develop a test simulator that consists of attitude simulation equipment, fueling equipment, and data storage equipment. The attitude simulation equipment simulates the aircraft attitude. It is manufactured to operate pitch angle and roll angle movement. The fueling equipment supplies fuel to the supplementary fuel tank. The data storage equipment collects and stores the measured data. We also develop an automation software that operates the test simulator and collects data automatically. The test simulator has been automated to prevent testers from being exposed to toxic fuel. Through automation software, the collection period is reduced by one quarter compared to manual collection. The developed fuel quantity measurement system is verified through the test simulator.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.20 no.2
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• pp.18-25
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• 2012

The availability of the GPS signal has been expanded greatly in the field of society overall through the development and construction of the GNSS(Global Navigation Satellite System). Furthermore, in the military, aviation and field of space, the GPS signal is applied widely through the combination of INS consisting of gyroscope and accelerometer, IMU, AHRS with the addition of magnetic sensor. Particularly, the performance of these equipments or sensors is very important with GPS and PAR(Precision Approach Radar) in the flight control of the aircraft. This paper deals with MATLAB simulation and ROLSO(Reduced Order Luenberger State Observer) design to reduce the load of system and realize the stable lateral direction approach control in an appropriate time for reduction of the horizontal error which is importantly considered while an aircraft lands instead of the FOLSO(Full Order Luenberger State Observer) using all measurement values. Consequently, ROLSO is expected to be used for the aircraft's attitude control in the aircraft landing causing the burden to the pilots.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.31 no.2
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• pp.18-24
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• 2023

According to the results of a survey by Boeing, LOC-I (Loss of Control in Flight) was the highest in the number of deaths by fatality accident category in the past 10 years from 2012 to 2021, and the number of deaths worldwide due to LOC-I accidents was 757. It turned out to be the biggest cause of aircraft fatalities, with a figure close to twice the sum of UNK (Unknown or Undetermined), which is the 2nd place, and CFIT (Controlled Flight Into or Toward Terrain), which is the 3rd place. This study set six scenarios related to spatial disorientation that may occur during sensory-dependent flight targeting student pilots and instructor pilots at domestic designated specialized educational institutions using flight simulation training equipment, and in each scenario, the pilot's. The need for SDRT (Spatial Disorientation Recovery Training) is verified by analyzing the flight experience and recovery ability by qualification, and SDRT is repeatedly performed to verify and present the training cycle and time.