Transactions of the Korean Society for Noise and Vibration Engineering (한국소음진동공학회논문집)

The Korean Society for Noise and Vibration Engineering (한국소음진동공학회)
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Nonlinear Dynamic Characteristics of Deployable Missile Control Fin

접는 미사일 조종날개의 비선형 동특성

  • 김대관 (한국과학기술원 항공우주공학과 대학원) ;
  • 배재성 (한국과학기술원 항공우주공학과 대학원) ;
  • 이인 (한국과학기술원 항공우주공학과) ;
  • 신영석 (국방과학연구소) ;
  • 이열화 (국방과학연구소)
  • Published : 2002.10.01
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Abstract

The nonlinear characteristics for hinge of a deployable missile control fin are investigated experimentally. The nonlinearity is caused by a worn or loose hinge and manufacturing tolerance and cannot be eliminated completely. The structural nonlinearity has an effect on the static and dynamic characteristics of the control fin. Therefore, it is necessary to establish the accurate nonlinear model for the hinge of the control fin. In the present study the existence of nonlinearities in the hinge is confirmed from the frequency response experiments such as tip random excitation and base sine sweep. Using the system identification method. especially, ″Force-state Mapping Technique″, the types of nonlinearities are identified and the nonlinear hinge model of the control fin is established.

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References

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