• Journal of Aerospace System Engineering
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• v.15 no.5
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• pp.106-112
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• 2021

In this study, we performed a design and structural analysis of a blade-shaped antenna installation on the rear fuselage of a rotary wing aircraft operated by the military. When the structure is damaged while the aircraft is in operation, it is separated from the aircraft main structure and may collide with the rotor or blades to cause the aircraft to crash. Therefore, structural safety for the modified structure must be secured. The design requirement for the newly installed modified part were established, and the load condition was constructed by applying the load that may occur in the aircraft after the modification. Structure safety for the modified structure was secured by performing structure analysis. To analysis stress and deformation of aircraft structure, we developed finite element model and verified it by using hand calculation method. We confirmed the safety of the modified structure through the final structural integrity analysis.

• Journal of Advanced Navigation Technology
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• v.28 no.1
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• pp.37-43
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• 2024

National aircraft are subject to exceptions under the International Civil Aviation Convention. Each country must ensure the safety of civil aircraft through reasonable consideration (due regard). Accordingly, the Aviation Safety Act of Korea also includes an exception for national aircraft. However, Korea Coast Guard aircraft are legislated to be subject to the law on five provisions. As Korea Coast Guard aircraft operate under the application of these provisions of international and domestic laws, they will be required to control flight procedures from China's civil air traffic control when flying over provisional action zone, which is international waters in the West Sea. China's demand is a major limiting factor in protecting the safety of the people of Korea, which is the original mission of Korea Coast Guard aircraft, and through this study, countermeasures to solving these problems at the national level were suggested.

• Journal of Aerospace System Engineering
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• v.1 no.3
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• pp.13-20
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• 2007

The objective of this study is to investigate endurance test of localization part for T-50 aircraft engine. Major localization parts of the engine (F404-STW-102) was performed using Accelerated Simulated Mission Engine Test. The purpose of this test is to evaluate of quality demonstration capability, to verify design of engine localization parts, and to improvement safety and operation rate of T-50 advanced trainer by finding out operational problems in production phase and fixing it.

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.95-98
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• 2016

It is true that Aircraft accident investigation organization of Republic of Korea does not have independent role structurally and administratively. Also, in the event of an aviation accident it does not take the appropriate response and post-institutional measures for victims and their families support. With aware of this fact and to improvement this research paper present approach direction and suggestion of issues and implications for those by researching the operational practices of the United State's Victim Family support.

• Information and Communications Magazine
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• v.7 no.3
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• pp.27-34
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• 1990

The $(L,\psi)$ feature description on the binary boundary air craft image is introduced of classifying 3-D object (aircraft) identification. Three types for associative matrix memories are employed and tested for their classification performance. The fast association involved in these memories can be implemented using a parallel optical matrix-vector operation. Two associative memories are based on pseudoinverse solutions and the third one is interoduced as a paralell version of a nearest-neighbor classifier. Detailed simulation results for each associative processor are provided.

• Journal of Aerospace System Engineering
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• v.4 no.2
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• pp.16-20
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• 2010

In General, the hydraulic system of T-50 Advanced Trainer is applied to flight control system, wheel & Brake system and fuel system for aircraft operation. The hydraulic system is operation with pressure of 3000psi. and many mechanical parts which is operated by hydraulic system has been stressed in incomplete environment same as heat and friction. for example, Oil leakage had occurred in the shutoff valve of FFP used in a certain period of time. After study, The crack progressed by fatigue due to the irregular hydraulic pressure and vibration has been identified as the reason of oil leakage. This paper presents life cycle extension plans of FFP shutoff valve by configuration improvements of shutoff valve and FFP hydraulic motor.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.3 no.1
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• pp.21-35
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• 1995

Nowadays aviation noise significantly affects a number of people over the world. This paper is mainly focused on the effect of temporary and permanent hearing loss of cockpit crew, flight attendants, passengers, persons in communities exposed to aircraft overflight. Also this paper describes the human hearing mechanism and the processes of temporary and permanent hearing loss. The results of research are presented and the potential for hearing loss in aviation noise environments evaluated. The Occupational Safety and Health Administration (OSHA) hearing protection criteria are also addressed.

• Journal of Aerospace System Engineering
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• v.15 no.6
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• pp.50-58
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• 2021

Byteflight is developed based on RS-485 communication (an international standard), and it can be used as a data bus during the operation of an integrated avionics system in the latest aircraft. Therefore, the integrated avionics system can perform an effective and safe flight mission only when the accurate and seamless display of flight information, communication, and accurate functions of navigation are implemented. In this study, cause analysis and failure investigation were performed on screen abnormalities and communication interruptions due to signal interference in the Byteflight data bus of the integrated avionics system during aircraft operation. To improve signal interference between avionics units, the branch point and wiring path of the Byteflight data bus were changed, and the verification result of the improved method was also described.

• Journal of Aerospace System Engineering
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• v.14 no.6
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• pp.10-17
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• 2020

The Korean medical evacuation helicopter was developed based on the Korean Utility Helicopter (hereafter referred to as 'Surion'). It uses an auxiliary power unit and engine for heating during winter operation. The helicopter maintains the internal temperature of the aircraft using its bleed air to satisfy its operational capability. However, due to the air inflow through the gap between the aircraft skin and door, additional heating for operating the portable medical equipment and preventing hypothermia in evacuated patients is required. Accordingly, an electric auxiliary heater was developed for additional heating during winter operation, and environmental, durability, and performance tests were conducted per MIL-STD-810G and MIL-STD-461F. The auxiliary heater was verified per the tailored airworthiness certification criteria.

• 한국항공운항학회:학술대회논문집
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• 2005.05a
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• pp.6-10
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• 2005