Earticle

초록

영어

There are various restrictions in the requirements of aircraft and instrument depending on their operational circumstances. Especially, strict vibration requirements are applied to aircrafts with high level of maneuvering. In this paper, new attachment was installed in the cockpit of a propeller aircraft which served a high level of maneuvering, and vibration influence caused by the new equipment was presented. Futhermore, the validity for design of the new equipment's supporting structures was verified by examining the vibration influence and by meeting the requirements. The finite element analysis is an important tool in evaluating the dynamic characteristics of aircraft before and after its modification. The dynamic characteristics analysis was performed in two stages. In the first stage, mode analysis was performed to identify the natural frequency of the supporting structure and to derive the dynamic change of the instrument panel by installing the supporting structure and new equipment. And in the second stage, random vibrations which spectrum specified in MIL-STD-810G was applied to the FE model of before and after modification is carried out.

목차

Abstract
 1. 서론
 2. 설계조건
  2.1 요구조건
  2.2 해석조건
 3. 모드해석
 4. 랜덤해석
 5. 결론
 참고문헌

키워드

저자

• 이숙 [ Lee, Sook | 대한항공 기술연구원 대리 ] 저자
• 김경남 [ Kim, Kyoung Nam | 대한항공 기술연구원 차장 ]
• 김승일 [ Kim, Seung li ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  한국방위산업학회지 [Journal of the Korean Association of Defense Industry Studies]

• 간기

  연3회

• pISSN

  1738-6144

• 수록기간

  2000~2025

• 등재여부

  KCI 등재

• 십진분류

  KDC 390 DDC 355