• Journal of the Korea Academia-Industrial cooperation Society
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• v.18 no.3
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• pp.640-646
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• 2017

A GEN TEST of the auxiliary power unit of a T-50 series aircraft is performed as part of the operational test of its emergency power system on the ground before flight. At this time, the auxiliary power unit should be automatically turned off via the response signal of the ECU when power is not normally supplied to the emergency power system. If the correct operation of the emergency power system cannot be confirmed on the ground, it is not possible to proceed with the flight. This kind of defect is a major factor causing the operation rate of the aircraft to be decreased. The defect code identified by the ECU was confirmed as a defect in the inverter. However, the same defect was found after replacing the inverter. This report presents an improved method of identifying the cause of the defect by analyzing the response characteristics of the ECU and emergency power system and allows the ECU to be recognized as the cause of the defect if the inverter does not generate a voltage within a certain time. Also, the application of the improved method confirmed that it can satisfy the output request time of the emergency power system and effectively prevent the auto-shutdown of the auxiliary power unit.

• Journal of Korea Multimedia Society
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• v.20 no.3
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• pp.437-445
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• 2017

Necessity of security reinforcement has been increased these days. As a result, surveillance systems using CCTV and the patrol system by person have been applied to security zone. However, CCTV has a blind spot and CCTV itself cannot handle emergency situation. Patrol system by person is economically expensive. To overcome these disadvantages, this paper presents an image-based surveillance system using unmanned aircraft. As a default, unmanned aircraft traces lines installed on ground which represents path for patrolling. If the aircraft detects objects, then it keeps a constant distance between object without missing the object in the image. Simulation results show that the proposed system can be operated even with unmanned aircraft with low specification.

• Nuclear Engineering and Technology
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• v.55 no.3
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• pp.1052-1060
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• 2023

The airborne radiation monitoring has been used in geophysics for more than forty years and now it also has its important role in emergency monitoring. The aircraft background and the cosmic gamma-rays contribute to the measured gamma spectrum on the aircraft board. This adverse effect should be eliminated before the data processing. The paper describes two semiparametric methods to estimate the full spectrum aircraft background and cosmic gamma-ray contribution from spectra measured at altitudes where terrestrial contribution is negligible. The methods only assume to know possible peak positions in spectra and their full width at half maximum, that can be easily obtained e.g. from terrestrial measurement. The methods were applied to real experimental data acquired on Mi-17 and Bell 412 helicopter boards. The IRIS airborne gamma-ray spectrometer, with 4×4 L NaI(Tl) crystals, produced by Pico Envirotec Inc., Canada, was used on helicopters' boards. To obtain valid estimate of the aircraft background and the cosmic contribution, the measurements over sea and large water areas were carried out. However, the satisfactory results over inland were also achieved comparing with those acquired over large water areas.

• Journal of the Korean Society of Safety
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• v.28 no.3
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• pp.29-32
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• 2013

An aircraft made an emergency landing through the loss of capability controlling steering. A torsion link which is a part of steering apparatus has been adrift from the steering system and the bolt connected to the steering link has fractured. At the same time, the FLIR(Forward Looking Infrared Radar) mounted in front of the steering link has been also damaged. In the early of this investigation, we considered the failure of the FLIR had occurred first, that FLIR hit the steering link and finally the bolt fractured. The fractured section of the bolt has shown a beach mark and a dimple mark as well. The outside of the bolt has shown a large deformation by a heavy load. As a result, we have found out what the cause of the heavy load and the fractures for bolt, link and FLIR have occurred in what order.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.908-911
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• 2011

Aircraft Auxiliary Power Unit can start and operate using not only main fuel(JP-8) but also specified emergency fuels for emergency operation. In oder to verify emergency fuel requirement, emergency fuel test using commercial diesel fuel was performed. Changes in specific fuel consumption due to use of diesel fuel are 3.5%~7.8%, which satisfied requirement. Diesel fuel showed similar starting characteristic to the JP-8. The specific fuel consumption of diesel increased by 2.0%~3.4% compared with that of JP-8.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.12 no.9
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• pp.4075-4082
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• 2011

In the event of the emergency patient care, cabin crew must take the charge of the first responder quickly. The basic emergency treatment knowledge of the cabin crew consisted of 80.5%~97.8% when the emergency scene showed up in the passenger and the types of emergency care with that the cabin crew could cope were bleeding control, fever, seizures, myocardial infarction, airway management, and partial airway obstruction management. Considering these cares, the improper emergency types revealed approximately 3.2%~20.0%. In airway obstruction there was followed by loss of consciousness and this led to cardiac arrest. In case of cardiac arrest, the cabin crew must know how to check breathing and to use the automated external defibrillator(AED). The life-threatening cardiac arrest can happen to any passenger in any time, so the cabin crew should meet with the emergency accident and apply the AED to the cardiac arrest victim.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.17 no.3
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• pp.32-39
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• 2009

Due to the lack of navigable airspace caused by worldwide air traffic increases, air traffic control(ATC) services are becoming more complex, which results in the increase of aircraft accidents. To cope with these challenges, major aviation institutes abroad are actively conducting research regarding the human factors affecting controllers but as of late, no such specialized activities have been found in Korea. Due to the dynamic attributes of ATC operations, management of controller's situation awareness(SA) and workload, and knowledge on the impact of abnormal aircraft to controllers are very important. Furthermore, using actual flight data of each country will lead to valuable results, because individually, it has different airspace characteristics and air traffic volumes. This study assumed that air traffic difficulties would affect the controller's SA and workload. To testify the above hypothesis, the abnormal air traffic situations are simulated by using ATC simulator. The findings indicated that the effect of traffic situations containing abnormal aircraft on the controller's SA and workload, it led to demand increase and supply decrease in SA, and increased mental demand, temporal demand, effort and mean workload score in the workload.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.198-200
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• 2017

An Auxiliary Power Unit (APU) is a small gas turbine engine that is mounted on an aircraft and serves to supply energy for ground and air starting of the main engine. APU also supplies emergency and auxiliary power for the aircraft. APU for aircraft is simple and compact in structure, but because it is mounted on manned aircraft, high reliability is required, so it must be proved its reliability through qualification procedure. The Korea Aerospace Research Institute and Hanwha Techwin successfully completed the design / analysis, fabrication, assembly, development test and certification test of APU for helicopter based on accumulated domestic R & D capability and experience from 2007 to 2012. In this paper, the development and certification process of auxiliary power unit for helicopter is summarized.

• Journal of the Korea Society of Computer and Information
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• v.24 no.2
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• pp.111-118
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• 2019

Recent trends in modern warfare are increasing in importance for air warfare, information warfare, and warfare. The technology of the weapon system software is rapidly developing, and the silent information war to hack it is still going on. Currently, the FA-50 aircraft has a function that can be initialized by a simple switch operation to protect the main military information in the event of an emergency. However, there are limitations in the existing Zeroize function, and this study was carried out to supplement this. First, we compare and analyze the memory structure of aircraft operating in our military, and examined the currently implemented Zeroize function. Second, we reviewed various methods to overcome the limitation of existing Zeroize function. Third, we implement the existing Zeroize function without additional manipulation. In this paper, we propose that the implementation of this feature will enable us to protect our military data more securely and suggest that we should continue to look for ways to enhance security for our technology in the future.

• Journal of Aerospace System Engineering
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• v.16 no.5
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• pp.78-85
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• 2022

Multicopter-type unmanned aerial vehicles (UAV) are increasingly for cargo transportation to mountainous and island regions, image information acquisition in disaster areas, and emergency rescue transport. In order to successfully perform these tasks, the aircraft structure must be able to safely support the loads induced by flight conditions while ensuring the vibration and aeroelastic stability of the prop-rotor. This study introduced a structural analysis model of a 40kg payload multicopter with an engine-generator hybrid power system. The deformation and stress distribution are investigated depending on the load conditions. In addition, the vibration characteristics and aeroelastic stability of the prop-rotor were also presented to flight speed and aircraft pitch angle. The maximum thrust generated by the prop-rotor and the landing load applied to the multicopter under normal and emergency landing conditions were reviewed., It confirmed that the structure could support without failure. In addition, it confirmed that the damping characteristics of each primary locate in the constant region according to the aircraft's flight speed and the prop-rotors rotating speed.