Composites Research

  • 제15권3호
  • /
  • Pages.52-61
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  • 2002
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  • 2288-2103(pISSN)
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  • 2288-2111(eISSN)
한국복합재료학회 (The Korean Society for Composite Materials)
권호 표지

다분야 층별 이론에 기초한 원통형 압전적층 쉘의 공력열탄성학적 해석

Aerothermoelastic Analysis of Cylindrical Piezolaminated Shells Based on Multi-field Layerwise Theory

  • 오일권 (LG전자 DA연구소) ;
  • 신원호 (한국과학기술원 기계공학과 항공우주공학전공) ;
  • 이인 (한국과학기술원 기계공학과 항공우주공학전공)
  • 발행 : 2002.06.01
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⟨ 이전 논문 다음 논문 ⟩

초록

압전재가 부착된 원통형 패널의 공력열탄성학적인 해석을 수행하기 위하여, 다분야 층별 이론에 기초하여 기하학적 비선형 유한 요소를 개발하였다. Han Krumhaar의 초음속 피스톤 이론을 적용하여 압전재가 부착된 원통형 패널에 대하여 열하중과 열변형에 따른 초음속 플러터 해석을 수행하였다. 플러터 임계동압을 증가시키고, 압전재 층의 열탄성학적 변형을 줄이는 가능성에 대하여 압전 작동기를 사용하여 검토하였다. 이 논문의 해석 결과들은 압전 작동기가 플러터 모드의 병합을 늦추고, 열하중을 상쇄하여 임계 동압을 효과적으로 증가시킬 수 있음을 보였다.

For the aerothermoelastic analysis of cylindrical piezolaminated shells, geometrically nonlinear finite elements based on the multi-field layerwise theory hale been developed. Applying a Han Krumhaar's supersonic piston theory, supersonic flutter analyses are performed for the cylindrical piezolaminted shells subject to thermal stresses and deformations. The possibility to increase flutter boundary and reduce thermoelastic deformations of piezolaminated panels is examined using piezoelectric actuations. Results show that active piezoelectric actuations can effectively increase the critical aerodynamic pressure by retarding the coalescence of flutter modes and compensating thermal stresses.

키워드

참고문헌

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