• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.110-120
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• 2003

As the wooden aircraft in the early times has no way to let lightning flow when lighting flash attaches during flight, the aircraft got damage, or caught fire. Though all metal airplane was developed with an advent of aluminum, a lightning accident still occurred including a fire of a fuel tanks. Eventually, NACA declared problems in 1938, and an artificial lightning test began. III succession, FAA established Airworthiness Requirements for certification. The FAA committed test measures study for the protection of an airplane from lightning to SAE. SAE presented the test current and voltage waveforms that simulating natural lightning, and it is utilized on lightning protection certification of an airplane by public. A lightning effects of an airplane through an analysis of lightning mechanism was made in this technical note. Especially, lightning direct effects on aircraft are analyzed and lightning strike zones are described.

• 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 Industry
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• s.103
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• pp.50-51
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• 2009

장마와 태풍의 계절 여름. 특히 하늘을 짖기라도 하듯 어마어마한 전기를 일으키는 낙뢰를 하늘을 나는 항공기로서는 정말 위협적인 존재가 아닐 수 없다. 하지만 낙뢰를 알고 이에 대한 철저한 보호대책이 따른다면 낙뢰에 의한 항공사고는 충분히 줄일 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.12
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• pp.1071-1086
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• 2016

The safety of aircraft can be threatened by environmental factors, such as icing, turbulence, and lightning strike. Due to its adverse effects on aircraft structure and electronic components of aircraft, lightning strike is one of the biggest hazards on aircraft safety. Lightning strike can inject high voltage electric current to the aircraft, which may generate strong magnetic field and extreme hot spots, leading to severe damage of structure or other equipment in aircraft. In this work, mechanism of lightning strike and associated direct and indirect effects of lightning on aircraft were studied. First, on the basis of aircraft lightning regulations provided by Aerospace Recommended Practice (ARP), we considered different lightning waveform and zones of an aircraft. A coupled thermal-electrical computational model of ABAQUS was then used for simulating flow of heat and electric current caused by a lightning strike. A study on fuel tank, with and without lightning protection system, was also conducted using the computational model. Finally, electric current flow on two full scale airframes was analyzed using the EMA3D code.

• Journal of Advanced Navigation Technology
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• v.19 no.5
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• pp.395-402
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• 2015

This paper introduces the design details and test procedures of the lightning induced transient protection device for protecting the damage caused by indirect lightning strike on the computer mounted on the aircraft. Lightning induced surge voltage is bring a malfunction or damage to the aircraft electrical and electronic equipment, that is referred to indirect effects of lightning. In order to protect the electronic equipment on aircraft from the indirect effects of lightning, that is achieved by analyzing the effect on aircraft from lightning and protect design for each devices. In this paper, we introduce an indirect lightning strike level decisions, the protection circuit design method according to the chosen level through the RTCA DO-160G Section 22 category analysis and selection was performed in order to protect the damage caused by indirect lightning strikes in the protected equipment. In addition, we show the indirect lightning effects verification test performed to validate the designed protection circuits.

• Journal of Advanced Navigation Technology
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• v.21 no.5
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• pp.459-465
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• 2017

In this paper, we introduce the design consideration of the lightning induced transient protection circuit for the indirect lightning strike on the avionics equipment. The lightning induced surge voltage, which is so-called as indirect effects of lightning, may cause a functional failure or physical damage to the electrical and electronic equipment of aircraft. In order to protect the electrical and electronic equipment of aircraft from the indirect effects of lightning, we should analyze the effect of lightning strike on aircraft and consider applying protection design for each avionics device. However, lightning induced transient protection circuits can have unintended consequences because parasitic inductance elements are exist in PCB and TVS diodes. In this paper, we introduce the design method of the protection circuit considering the parasitic inductance of the protection circuit. In addition, we show the result of verification test performed to validate the protection circuits for indirect effects of lightning.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.9
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• pp.801-811
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• 2021

Lightning can deliver large amounts of energy to the aircraft in a short period of time, resulting in catastrophic consequence. In particular, lightning strikes accompanied by high temperature heat and current can damage aircraft surface and internal electronic equipment, seriously affecting flight safety. Lightning experiments to analyze this effect use a Component A waveform with a maximum current of 200 kA as specified in SAE ARP 5412B. However, the actual lightning occurs mostly below 35kA and lightning indirect tests are conducted by reducing waveforms to prevent damage to internal electronic equipment. In this study, we examine previous methods to plot the Component A reduced waveform and identify their limitations. We then propose a new method to plot the reduced waveform based on adjusting the correction factor of the aircraft lightning Component A waveform. Finally, the electromagnetic analysis software EMA3D was used to compare the internal induced current size reduction ratio of the internal cable harness of the EC-155B helicopter.

• Current Industrial and Technological Trends in Aerospace
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• v.5 no.2
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• pp.87-97
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• 2007

오늘날 항공기 설계와 제작은 다국적인 산업의 형태로 이루어지고 있다. 즉 항공기 서브시스템은 세계 각국에서 독립적으로 설계, 제작 및 시험한 후 한 곳으로 납품되어 조립 제작되는 데 이 때 중요한 것이 표준화이다. 항공전자장비의 낙뢰 간접영향에 대한 인증의 경우 RTCA DO-160E, Section 22 Lightning Induced Transient Susceptibility(낙뢰 유도 과도현상 적응성)로 표준화 되어 있다. 이 Section 22는 낙뢰 간접영향에 대한 항공전자장비 단위 즉, LRU (Line Replaceable Units)와 같은 부품단위의 시험 요건을 규정하고 있으며 이 규격은 현재 전 세계적으로 통용이 되고 있다. 1980년대 초 상용 수송기에 디지털 "Fly by Wire" 비행 시스템과 엔진제어시스템(EEC, Electronic Engine Control)의 도입 이후, 항공기 시스템이 낙뢰 환경에서 운용시 신뢰성을 보증할 필요성이 대두되었다. 데이터 처리를 통하여 제어되는 각종 항공전자장비에는 다중타격(MS)과 다중파열(MB) 기법에 의한 시험 사항이 최근 추가 되었다. 실제 낙뢰 환경과 유사한 시험실 모사를 위해 계속적인 연구가 진행 중이며 신규 시험 규격서가 새로이 출간되고 있다.

• Journal of Advanced Navigation Technology
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• v.18 no.5
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• pp.445-454
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• 2014

In this paper, we introduce measures designed content for RTCA DO-160 F, Section 22 tests performed to verify the effects of indirect lightning and testing process of the test was carried out in the multi-purpose display certification process. This is referred to as indirect effects of lightning capability of an aircraft having electrical electronic equipment failure or damage to bring lightning induced voltages. In order to protect the avionics from lightning indirect effects of these aircraft are analyzing the effects of lightning strikes on aircraft and aircraft systems and interior design needs protection against the threat on their part. In this paper, we introduce RTCA DO-160 F, component selection process according to Section 22 category selection method and the selected level for determining the level of such measures for protection against lightning of multipurpose display for this aircraft. It also introduces the actual test process to confirm that the designed effectiveness of the selected part. We expect a good example of the lightning planned for future development of measures designed avionics through each step of the process introduced this.

• Journal of Aerospace System Engineering
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• v.13 no.6
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• pp.60-69
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• 2019

Companies around the world are actively developing Personal Air Vehicle (PAV) to solve the serious social problem of traffic jams. Airworthiness certification for PAV is required, since it is a manned vehicle. As with aircraft, the critical threat to the safe operation of PAV is lightning strike with strong thermal load and magnetic fields. Lightning certification issue also remains important for PAV, since there are still insufficient development of PAV-related lightning certification technologies, guidelines, and requirements. In this study, the SAE Aerospace Recommended Practice (ARP), an international standard certification guideline recognized by the Federal Aviation Administration (FAA), was analyzed. In addition, the guideline of lightning certification was applied to a PAV. The impact of lightning on PAV was also analyzed through computational software. Finally, the basis for the establishment of the PAV lightning certification guidance was presented.