Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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Nonlinear Transonic Flutter Analysis of a Composite Fin Considering Delamination Effect

층간분리 효과를 고려한 복합재 핀의 비선형 천음속 플러터 해석

  • Gwang Young Lee (Defence Acquisition Program Administration (DAPA)) ;
  • Ki-Ha Kim (School of Aerospace and Software Engineering, Gyeongsang National University) ;
  • Dong-Hyun Kim (School of Aerospace and Software Engineering, Gyeongsang National University)
  • 이광영 (방위사업청) ;
  • 김기하 (경상국립대학교 항공우주및소프트웨어공학부) ;
  • 김동현 (경상국립대학교 항공우주및소프트웨어공학부)
  • Received : 2023.10.24
  • Accepted : 2023.11.20
  • Published : 2023.12.31
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Abstract

In this paper, nonlinear transonic flutter analyses of a composite missile fin considering the effect of delamination are conducted. An effective modal analysis methodology is adopted and verified with the experimental modal test data for laminated composite plates with delamination. Extended version of the in-house computational aeroelastic analysis program with the transonic small-disturbance (TSD) code is used in order to predict the flutter dynamic pressure of the delaminated composite fin models. In the subsonic, transonic, and supersonic flow regions, nonlinear time-domain flutter analyses are performed for various delamination conditions, and aeroelastic characteristics due to the delamination phenomena are examined in detail.

본 논문에서는 층간분리 현상을 고려한 복합재 미사일 핀의 비선형 천음속 플러터 해석을 수행하였다. 층간분리 효과를 고려한 유한요소 진동해석 기법은 시험 결과와 비교 및 검증하였다. 비선형 천음속 플러터 해석은 자체 개발한 천음속 미소교란 방정식 기반의 시간영역 플러터 해석 프로그램을 개선하여 복합재 날개의 층간분리 효과까지 고려할 수 있도록 확장하여 활용하였다. 복합재 미사일 핀 모델에 대해 층간분리 영역에 따른 아음속, 천음속 및 초음속 플러터 해석을 수행하고 층간분리 영향에 따른 공력탄성학적 특성을 고찰하였다.

Keywords

Acknowledgement

본 논문은 2022년 과학기술정보통신부의 재원으로 한국연구재단 미래우주교육센터(2022M1A3C2074536)의 지원을 받아 수행된 연구이며, 지원에 감사를 표하는 바입니다.

References

  1. Shiau, L.-C., "Flutter of Composite Laminated Beam Plates with Delamination," AIAA Journal, Vol. 30, No. 10, 1992.
  2. Kameyama, M. K., Hanawa, T., Hu, N., and Fukunaga, H., "Supersonic Panel Flutter Analysis of Delaminated Composite Plates," The Journal of the Japan Society of Aeronautical Engineering, Vol. 56, No. 656, September pp. 397-406, 2008. https://doi.org/10.2322/jjsass.56.397
  3. Kuo, S. Y., Shiau, L.-C., and Tsai, Y.-F., "Flutter of Delaminated Composite Plates," Journal of Aeronautics, Astronautics and Aviation, Series A, Vol. 44, No. 3, pp. 149-158, 2012.
  4. Fazilati, J., "Panel flutter of curvilinear composite laminated plates in the presence of delamination," Journal of Composite Materials, Vol. 52, Issue 20, 2018.
  5. Torabi, A. R., Shams, S., Narab, M. F., and Atashgah, M. A., "Delamination effects on the unsteady aero-elastic behavior of composite wing by modal analysis," Journal of Vibration and Control, Vol. 28, Issue 19-20, 2021.
  6. Bharati, R. B., Filippi, M., Mahato, P. K., and Carrera, E. "Flutter analysis of delaminated composite box-beam using higher-order kinematics," Composite Structures Journal, Vol. 301, 116145, 2022.
  7. Kim, D. H. and Lee, I., "Transonic and Low-Supersonic Aerodynamic Analysis of a Wing with Underpylon/Store," Journal of Aircraft, Vol. 37, No. 1, pp. 189-192, January-February 2000. https://doi.org/10.2514/2.2582
  8. Kim, D. H., Kwon, H., and J., Lee, I., "Comparison Study of Flutter Analysis for the Wings with Wind Tunnel Test Data", Journal of Korean Society for Aeronautical and Space Sciences, Vol. 28, No. 3, pp. 53-63, 2000.
  9. Kim, D. H. and Lee, I., "Transonic/Supersonic Flutter Characteristics of a Wing-Box Model with Tip Stores," AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Material Conference, AIAA 16-19, Paper 2001-1464,April 2001.
  10. Kim, D. H. and Lee, I., "CFD-Based Matched-point Linear and Nonlinear Flutter Analysis of Sweptback Wings in Transonic and Supersonic Flows," Computational Fluid Dynamics Journal, Vol. 11, No. 1, pp. 35-49, April 2002.
  11. Kim, D. H., Park, Y. M., Lee I. and Kwon O. J., "Nonlinear Aeroelastic Computation of a Wing/Pylon/Finned-Store Using Parallel Computing," AIAA Journal, Vol. 43, No. 1, pp.53-62, January 2005. https://doi.org/10.2514/1.11011
  12. Kim, D. H. and Lee, I., "Nonlinear Flutter Characteristics of a Composite Missile Wing in Transonic and Low-Supersonic Flows," Journal of Aircraft, Vol. 39, No. 5, September-October 2002.
  13. Kim, D. H. and Lee, I., "Nonlinear Aeroelastic Instability of an Supersonic Missile Wing with Pitch Axis Freeplay," KSAS International Journal, Vol. 4, No. 1, pp. 53-62, May 2003. https://doi.org/10.5139/IJASS.2003.4.1.053
  14. Sandford, M. C., Ruhlin, C. L., and Abel, I., Transonic Flutter Study of a 50.5° cropped-delta wing with two rearward-mounted nacelles, NASA TN D-7544, June 1974.
  15. Callioglu, H., Atlihan, G., and Topcu, M., "Vibration Analysis of Multiple Delaminated Composite Beams," Advanced Composite Materials, Vol. 21, pp. 11-27, 2012. https://doi.org/10.1163/156855111X614538
  16. Shen, M.-H. H. and Grady, J. E. "Free vibrations of delaminated beams," AIAA Journal, Vol. 30, No. 5, pp. 1361-1370, 1992. https://doi.org/10.2514/3.11072
  17. Nu, N., Fukunaga, H., Kameyama, M., Aramaki, Y., and Chang, F. K., International Journal of Mechanical Sciences, Vol. 44, pp. 1479-1503, 2002.