• Aerospace Engineering and Technology
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• v.4 no.1
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• pp.247-259
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• 2005

The interactions of natural atmospheric electricity with aircraft reveals many flight safety problems. It is estimated that on average, each commercial airplane is struck by lightning more than once each year. Thus the lightning strike to aircarft poses an appreciable threat to flight safety. Upset or damage of electrical and electronics equipment by the induced voltages is defined as indirect effect. The protection of aircraft electronics from the indirect effects of lightning can be accomplished first by determining the specific threats to the aircraft and systems contained within, and second, by designing protection methods to the aircraft components.

• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.196-204
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• 2008

Modem rotorcraft is required to have the capability to operate in all-weather conditions. Also icing condition is important issue to aircraft safety and certification. And rotorcraft icing research has come a long way during the past few decades. The aircraft icing is the most difficult to handle. So, icing-related accidents, incidents and operating problems still occur regularly in service, despite improvements in design and test techniques. By reviewing icing certification requirement of FAR(Federal Aviation Regulations) and KAS(Korean Airworthiness Standard), this paper describes methods how to demonstrate safety in the flight and consideration of icing when rotorcraft is required TC(Type Certification).

• 한국항공운항학회:학술대회논문집
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• 2016.05a
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• pp.125-130
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• 2016

최근 국내에서 개발한 KC-100 항공기의 형식증명 및 제작증명이 완료됨에 따라 우리나라도 항공기 제작/설계국 반열에 오르게 되었고, KC-100 개발을 계기로 국내 개발 항공기의 해외 수출을 대비한 제작/설계국으로서의 감항성 유지 체계 및 시스템 구축이 필요로 하게 되었다. 본 연구에서는 ICAO에서 제시하는 국가 유형 별 감항성 유지 업무의 책임 및 해외 항공선진국의 감항성 유지체계와 우리나라의 지속감항업무 수행현황을 비교분석하여 국내 감항성 유지 체계 및 항공기 고장보고 항목에 대한 개선 방안을 제시하였고 항공안전정보 네트워크를 구축하여 지속감항체계에서 획득한 항공 안전기술정보를 안전감독에 활용하기위한 방안을 연구하였다.

• Proceedings of the KAIS Fall Conference
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• 2011.12b
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• pp.635-638
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• 2011

항공기 착륙 시 발생되는 높은 충격하중에서 승무원 및 기체를 보호하기 위해 높은 충격흡수율이 요구된다. 따라서 착륙 시 발생하는 충격을 효과적으로 흡수할 수 있는 착륙장치는 항공기 핵심 구성요소이다. 다양한 종류의 완충장치가 존재하나, 소형항공기 주착륙장치에는 판스프링 방식을 이용하여 충격에너지를 흡수할 수 있다. 착륙장치의 완충 성능은 반드시 낙하시험을 통해 입증하여야 하며, 이는 미 연방 항공 규정에서 요구하고 있는 사항이다. 이 논문에서는 소형항공기 낙하시험을 위한 설비, 시험 절차 및 낙하시험 수행 결과를 제시한다.

• Proceedings of the KIEE Conference
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• 2015.07a
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• pp.886-887
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• 2015

선진 각국에서는 고효율, 친환경 에너지 공급 및 이용 기술, 그리고 효율적인 에너지 절약 기술 개발에 관한 연구 개발이 활발히 진행되고 있다. 이러한 연구 중 항공기 분야에서는 전동기로 프로펠러를 회전시키는 전기추진 항공기에 대한 관심과 수요가 증가하고 있다. 소형 항공기 추진용 전동기는 엔진과 함께 소형 항공기의 주 구동원으로서 중요성이 강조되고 있다. 또한 근래에 전동기의 비중이 커짐에 따라 고출력, 고효율화 되고 있는 추세이다. 본 논문에서는 항공 운항 패턴 중 이륙, 상승, 순항구간에 따라 각각 요구하는 성능을 만족하는 고출력, 고효율 전동기 개발에 대해 다루었다.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.79-86
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• 2019

An anti-collision light of a rotary-wing aircraft is used for the purpose of preventing collision during the operation of an aircraft and is a key component to ensure flight safety. The anti-collision lights of the Korean Utility Helicopter (KUH) consist of upper and lower lights, and the power supply of anti-collision lights mounted on the aircraft. The anti-collision light is designed as a dual structure capable of brightness control and selective lighting. During the operation after delivery of the aircraft, abnormal lighting of anti-collision light occurred. In this paper, a comprehensive review of the aircraft system and component level was conducted to solve these phenomena at first. Then, the causes of anti-collision light anomalies were analyzed and the design changes are presented. The validity of design changes has been verified through the component and aircraft system ground/flight test.

• Journal of Aerospace System Engineering
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• v.13 no.5
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• pp.65-71
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• 2019

In this study, as a part of the aging aircraft performance improvement project for which no design information is provided, a new type of blade antenna is installed on the main part of the aging aircraft, and the method of proving the fatigue life of the main part of the aircraft is reviewed and summarized. There are various methods to prove fatigue life according to the manufacturer and aircraft design conditions. The fatigue life prediction and damage tolerance range of the relevant site were obtained through related regulations and industry examples. From these results, the fatigue life of newly installed antennas around the main parts of the aging aircraft was evaluated and the maintenance period and criteria were set according to the damage tolerance.

• 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 the Korean Society for Aeronautical & Space Sciences
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• v.41 no.5
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• pp.391-403
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• 2013

Propeller aircraft propelled by an electric propulsion system is gaining a renewed interest because of ever-increasing environmental concern on harmful emissions emitted from conventional jet engines and national energy security. Traditional aircraft sizing methods are not readily applicable to electric propulsion aircraft that utilize a variety of alternative energy sources and power generation systems. This study showcases an electric propulsion aircraft sizing exercise based on a generalized, power based sizing method. A general aviation aircraft is propelled by an electric propulsion system that comprises of a propeller, a high temperature super conducting motor, a Proton Exchange Membrance(PEM) fuel cell system fuelled with hydrogen, and power conditioning equipment. In order to assess the impact of technology progression, aircraft sizing was conducted for two different sets of technology assumptions for electric components, and the results were compared with conventional baseline aircraft.

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.7-12
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• 2020

In this paper the new revision of Korean Airworthiness Standards (KAS) - Emissions was proposed for enforced environmental standards. The Aircraft Engine Fuel Venting and Exhaust Emissions Requirements have been only defined for smoke, HC, CO and NOx as management items in previous KAS. However, this standard has not covered the current situation that International Civil Aviation Organization (ICAO) and United States Environmental Protection Agency (EPA) enforced environmental regulations, such as emissions trading system, limitation of CO₂ emissions and restriction of exhaust gas. In order to overcome these outdated situations, we presented the new requirements for aircraft exhaust gas emissions standard of Korea based on the latest standards of United States, Europe and other countries.