Browse > Article
http://dx.doi.org/10.5139/JKSAS.2002.30.7.029

Aeroelastic Analysis of Deployable Missile Control Fin with Bilinear Nonlinearity  

Bae, Jae-Sung (한국과학기술원 항공우주공학)
Shin, Won-Ho (한국과학기술원 항공우주공학)
Lee, In (한국과학기술원 항공우주공학)
Shin, Young-Sug (국방과학연구소)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.30, no.7, 2002 , pp. 29-35 More about this Journal
Abstract
Aeroelastic characteristics of a deployable missile control fin have been investigated. A deployable missile control fin is modeled by a 2-dimensional typical section. Supersonic Doublet-Point method is used for the computation of supersonic unsteady aerodynamic forces and Karpel's Minimum-State approximation is used for the aerodynamic approximation. Root-locus method and time-integration method are used for the linear and nonlinear flutter analyses. For the nonlinear flutter analysis the deployable hinge is represented by a asymmetric bilinear spring and is linearized by using the describing function method. From the flutter analyses, the effects of nonlinear parameters on the aeroelastic characteristics are investigated.
Keywords
Flutter; Missile Control Fin; Nonlinearity; Root-Locus Method; Mimimum-State Approximation;
Citations & Related Records
연도 인용수 순위
  • Reference
1 Bisplinghoff, R. L., Ashley, H., and Halfman, R. L., Aeroelasticity, Addison-Wesley Publishing Company, Cambridge/ Mass., 1955.
2 Dowell, E. H., Crawley, E. F., Curtiss Jr., H. C, Peters, D. A., Scanlan, R. H., and Sisto, F., A Modern Course in Aeroelasticity, Kluwer Academic Publishers, 1995.
3 Lee, B. H. K. and Tron, A., "Effects of Structural Nonlinearities on Flutter Characteristics of the CF-18 Aircraft," Journal of Aricraft, Vol. 26, No. 8, 1989, pp.781-786.   DOI   ScienceOn
4 Bae, J.S., Yang, S.M. and Lee, I., "Linear and Nonlinear Aeroelastic Analysis of a Fighter-Type Wing with Control Surface," Journal of Aircraft, Vol. 39, 2002, In press.
5 Karpel, M., "Design for Active Flutter Suppression and Gust Alleviation Using State-Space Aeroelastic Modeling," Journal of Aircraft, Vol. 19, No. 3, 1982, pp. 221-227.   DOI   ScienceOn
6 배재성, 김도형, 양승만, 이인, "날개/스토어모델의 플러터 억제," 한국소음진동공학회, 2002, 출판중
7 배재성, 백승길, 이인, "공압식 구동장치가 부착된 미사일 조종날개의 플러터 해석," 한국항공우주학회지, 29권, 7호, 2001, pp. 27-33.
8 배재성, 양승만, 김대관, 김도형, 이인, "미사일 조종날개의 비선형 힌지 강성 측정," 제9회 지상무기체계 발전 세미나, 국방과학연구소, 2001년 10월, pp H63-H73.