• Journal of the Korean Society for Aviation and Aeronautics
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• v.31 no.4
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• pp.1-6
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• 2023

EBT has designed and implemented a training program that relies on evidence from events such as Flight Operation Quality Assurance (FOQA), accidents, and incidents specific to each airline. The goal is to enhance the overall skills of the flight crew. This involves assessing the capabilities of individual crew members and, based on the findings, providing additional training to address any shortcomings. To create a training program aligned with the objectives of EBT, this study focused on analyzing data from hard landing incidents in domestic airlines obtained through FOQA events. A practical EBT training program was then developed, specifically targeting adverse weather conditions. The program evaluates landing capabilities, and the results guide the supplementation of any deficiencies in the landing skills of each flight crew member, ultimately aiming to enhance their confidence.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.3
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• pp.173-180
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• 2022

The operation and transportation environment for an unmanned aerial vehicle will be completely different from those for the conventional air and ground transportation. The requirement for a traffic management system for its safe operation has been emerging. Accordingly, investigation is being conducted to analyze the danger that unmanned aerial vehicle may encounter during the flight and to provide the countermeasure by the simulation. When the drones operate in an urban environment, they may be affected by the wind around the building. Thus it is essential to predict the influence of the gust and analyze the resulting risk. In this paper, a method for evaluating the safety for a flight mission under the gust is suggested. By using the precise 6-degree-of-freedom flight simulation that is capable of simulating the gust condition, possible deviation from the pre-planned flight path in terms of the attitude orientation will be predicted. A method of quantifying the probability of the flight mission failure will also be presented.

• Journal of Advanced Navigation Technology
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• v.26 no.5
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• pp.249-260
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• 2022

Student pilots receiving flight education are inexperienced in piloting and situation judgment skills and are greatly affected by various factors such as psychological, physical, and environmental factors. In particular, one of the most influential factors in the flight education of student pilots is the weather conditions. Unlike large aircraft used in the air transportation business, small aircraft used for flight education have a great impact on education, such as flight restrictions depending on weather conditions, psychological pressure in severe weather, and deterioration of student skills. Therefore, in this study, the meteorological characteristics of meteorological factors that have a great influence on small aircraft were analyzed. As a result of the analysis, an efficient and safe training operation method was suggested to a professional pilot aviation training organization through the adjustment of the training period for the season, the increase in aircraft operation rate, and a safe solo flight plan considering the weather.

• International Journal of Aeronautical and Space Sciences
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• v.17 no.1
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• pp.120-131
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• 2016

The full results of troubleshooting process related to the flight control system of a tilt-rotor type UAV in the flight tests are described. Flight tests were conducted in helicopter, conversion, and airplane modes. The vehicle was flown using automatic functions, which include speed-hold, altitude-hold, heading-hold, guidance modes, as well as automatic take-off and landing. Many unexpected problems occurred during the envelope expansion tests which were mostly under those automatic functions. The anomalies in helicopter mode include vortex ring state (VRS), long delay in the automatic take-off, and the initial overshoot in the automatic landing. In contrast, the anomalies in conversion mode are untrimmed AOS oscillation and the calibration errors of the air data sensors. The problems of low damping in rotor speed and roll rate responses are found in airplane mode. Once all of the known problems had been solved, the vehicle in airplane mode gradually reached the maximum design speed of 440km/h at the operation altitude of 3km. This paper also presents a comprehensive detailing of the control systems of the tilt-rotor unmanned air vehicle (UAV).

• Journal of Advanced Navigation Technology
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• v.4 no.1
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• pp.11-22
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• 2000

Instrument flight simulators are used for training the interpretation and operation techniques for all kinds of aircraft instruments, cockpit procedures, etc., in order that pilots cope with the situations which can be occurred in actual flight. However, the simulators developed so far are concerned about operating in same environment to actual aircraft. And little researches concentrate on developing systematic training system for basic tasks and takeoff-landing procedures, and automatic evaluation methods on the training results. Therefore, in this paper, we propose implementation and evaluation methods for flight tasks such as tasks in flight, takeoff-landing procedures and course flight.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.11
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• pp.968-973
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• 2014

Optionally Piloted Vehicle is one of the UAV development technology and method, which can provide the economic and efficient unmanned system. Existing manned aircraft is evaluated through much flight operations and it can supply the reliable aircraft platform, engine and subsystems for operation. In addition, OPV can be operated both manned and unmanned vehicle to satisfy the mission requirement. under the certain flight conditions. This paper describes main development procedures for automatic flight control system of OPV and summarizes the technical issues and results.

• Journal of Institute of Control, Robotics and Systems
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• v.14 no.7
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• pp.629-634
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• 2008

This paper presents the flight test procedure and the results for the airspeed indicator calibration of a light airplane the name of ChangGong-91, which is the first type certified aircraft from Korean Ministry of Construction and Transportation, as a part of the flight test validation to get the certification. The flight tests for airspeed position error calibrations are conducted using tower fly by method in order to calibrate swivel head testboom which is attached to the right wing tip of the airplane. Also system to system method is applied in order to calibrate the airspeed indicator of the cockpit. The flight test is conducted at the basis of the 'Korean Airworthiness Standard' which is the regulation of Korean Ministry of Construction and Transportation. The airspeed error range for the testboom and the airspeed indicator are determined to $-0.75{\sim}+0.75$ knot and to $-4.0{\sim}+2.0$ knots, respectively. The calibration results are applied to ChangGong-91 Flight Operation Manual.

• Journal of Korean Society for Quality Management
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• v.49 no.3
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• pp.255-268
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• 2021

Purpose: We sought to understand why a high-speed rotating projectile featuring a fuze-and-body assembly sometimes exhibited airburst, and we intended to improve the flight stability by eliminating airburst. Methods: We performed characteristic factor analysis, structural mechanics modeling, and dynamic modeling and simulation; and we scheduled firing tests to discover the cause of airburst. We used a step-by-step procedure to analyze the reliability function for selecting the bonding force standard that prevents airburst. Results: The 00MM high-speed rotating projectile features a fuze bonded to a body assembly; the bonding sometimes can break on firing. The resulting contact force, vibration and roll damping during flight generated yaw. Flight became unstable; fuze operation triggered an airburst. Our reliability test improved the bonding force standard (the force was increased). When the bonding force was at least the minimum required, a firing test revealed that airburst/flight instability disappeared. Conclusion: Analysis and identification of the causes of flight instability and airburst render military training safer and enhance combat power. Ammunition must perform as designed. Our method can be used to set standards that improve the performances of similar types of ammunition.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.29 no.3
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• pp.76-83
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• 2021

The importance of human factors has been emphasized for pilots because most of aviation accidents have been caused by the human factors of pilots. Human factors issues such as fatigue affecting flight safety are needed to be educated to student pilots who have less experience in flight training. In order to prevent aviation accidents caused by human factors, the management of stress, fatigue, and obsessive-compulsive disorder which increase psychological harmful factors of student pilots, is essential for aviation safety. The management of fatigue is required as a part of safety management system following the guidance of leading aviation authorities. The purpose of this article was to investigate the factors of fatigue at each stage by classifying it into before, during, and after flight training to manage the fatigue of students pilots. Then, the factors of relatively high fatigue were analyzed by using the AHP process to provide factors related fatigue affecting pilot training.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.46 no.11
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• pp.961-968
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• 2018

Airborne display systems provide pilots with a variety of information needed to operate aircraft. Software faults in the display system can seriously affect the operation of the aircraft, because it can provide inaccurate information to the pilot. Therefore, the software faults are identified and eliminated through ground testing and flight testing. This paper presents an analysis tool called FDR (flight data replay) for flight test of airborne display software. This tool works in real time with the mission computer of aircraft. Also, the tool reproduces the functional error conditions that appear in the display systems by applying flight test data to the display software.