Earticle

초록

영어

This study evaluated the design, fabrication, and performance of CFRP composite propeller blades for naval applications. The blades were designed with a sandwich structure and a dovetail hub connection to achieve both high strength and reduced weight. During fabrication, the outer skin and Melamine Foam core were bonded using adhesive films and integrated through autoclave molding and post-curing. The finished blades were coated with a low-gloss urethane clear finish, and the leading-edge areas received additional coating to ensure surface protection and operational identification. Static bending tests and finite element analysis were conducted to assess failure behavior under maximum load and local stress concentrations, while natural frequency measurements(Hammer test) confirmed agreement between analytical and experimental results, verifying the reliability of dynamic response predictions. The results demonstrate that the composite blades offer superior weight reduction and vibration damping compared to metal counterparts and can serve as a foundational reference for future naval propeller design and optimization of various rotating and winged structures.

목차

Abstract
1. 서론
2. 설계
2.1. 프로펠러 구조 설계
2.2. 블레이드 적층 설계
3. 제작
3.1. 실험 재료
3.2. 실험방법
3.3. 성능 평가
4. 실험 결과 및 고찰
5. 결론 및 토의
References

키워드

저자

• 김선규 [ Sun-Kyu Kim | Member, Professor, Dept. of Aviation MRO, Namincheon Campus of Korea Polytechnic. Ph.D. Program in Mechanical Engineering, Inha University ] Corresponding Author
• 이상의 [ Sang Eui Lee | Member, Professor, Inha University ]

참고문헌

발행기관

간행물

표지보기 관심저널 등록

• 간행물명

  한국기계항공기술학회지(구 한국기계기술학회지) [Journal of the Korean Society of Mechanical and Aviation Technology ]

• 간기

  격월간

• pISSN

  1229-604X

• eISSN

  2508-3805

• 수록기간

  1999~2026

• 등재여부

  KCI 등재

• 십진분류

  KDC 550 DDC 620