Journal of the Korean Society for Aeronautical & Space Sciences (한국항공우주학회지)

The Korean Society for Aeronautical and Space Sciences (한국항공우주학회)
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A Study of Certification of Lightning Indirect Effects on Cable Harness in Personal Air Vehicles

PAV 케이블 하네스에 대한 낙뢰 간접 영향성 인증 기법에 관한 연구

  • Jo, Jae-Hyeon (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Kim, Yun-Gon (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Park, Se-Woong (School of Mechanical and Aerospace Engineering, Gyeongsang National University) ;
  • Myong, Rho-Shin (School of Mechanical and Aerospace Engineering, Gyeongsang National University)
  • Received : 2020.11.22
  • Accepted : 2021.02.23
  • Published : 2021.03.01
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Abstract

The airworthiness certification of lightning indirect effects becomes an important issue in personal air vehicles (PAVs), which are being actively developed around the world. PAVs are very vulnerable to lightning strikes, because of miniaturization, use of the electric engines, composite materials, and application of unmanned navigation systems. In this study, we first examined various steps of certifications for lightning indirect effects shown in AC 20 136B issued by the Federal Aviation Administration (FAA). We then applied certification guidelines for equipment transient design level listed in RTCA DO 160G Section 22 to PAVs and investigated lightning transient environments inside the PAVs. We also analyzed the aircraft level tests specified in SAE ARP 5416A by using electromagnetic computational analysis software EMA3D. Finally, we analyzed the actual transient level for PAVs and derived the data necessary for conformity certification.

최근 세계적으로 연구개발이 활발히 진행되고 있는 PAV(Personal Air Vehicle)에 대한 낙뢰 간접 영향성 인증 지침의 중요성이 부각되고 있다. 미래 교통수단으로서 소형화, 전기 엔진 사용, 복합재 사용 증가, 무인 항법 시스템 적용하는 추세인 PAV는 낙뢰에 취약할 수밖에 없다. 본 연구에서는 미연방항공청(FAA)에서 발행한 AC 20 136B에 나타난 낙뢰 간접 영향에 대한 적합성 인증절차를 확인하였다. 이와 함께 RTCA DO 160G Sec. 22에 수록된 장비 과도 설계 수준에 대한 인증 지침을 PAV에 적용하였다. 이어서 SAE ARP 5416A에 수록된 항공기 수준 시험을 전자기 해석 소프트웨어 EMA3D을 통해 수행하였다. 이를 통해 PAV에 대한 실제 과도 수준을 분석하였으며 이를 통해 적합성 인증에 필요한 자료를 도출하였다.

Keywords

Acknowledgement

이 논문은 국토교통부와 국토교통과학기술진흥원 및 항공안전기술원의 민수헬기인증개발사업의 지원을 받아 수행되었습니다(20CHTR-C139569-04).

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