Analysis of control characteristics for high speed rolling guided missile with one axis steering fin

1축 날개 조종형 고속회전 유도탄의 조정 특성 해석

  • Chin, Jong-Sok (Agency for Defense Development) ;
  • Lee, Jae-Hyuk (Agency for Defense Development, Dept.of Electric Engineering, Yonsei University)
  • 진정석 (국방과학연구소 대공유도무기사업단) ;
  • 이재혁 (국방과학연구소 대공유도무기사업단 및 연세대학교 전기공학과)
  • Published : 1996.06.01

Abstract

It is difficult to analyze the high speed rolling missile with the generally used missile body fixed coordinates. In this study, we formulate the dynamic equations of the high speed rolling missile with the principal axis of inertia, and make the analytical model of one axis steering missile using pitch/yaw symmetry and complex summation method. With this model we analyze the control characteristics and propose the design considerations of high speed rolling missile with one axis control fin using PNG law in conjuntion with a seeker signal.

References

  1. Inertial Navigation Systems Analysis, Measurement System Laboratory Kenneth,R.Britting
  2. J. Guidance and Control v.2 no.1 Instability of spinning projectiles during terminal guidance K.H.Lloyd;D.P.Brown
  3. J. Guidance and Control v.2 no.6 Angular motion of spinning almost-symmetric missile Charls,H.Murphy
  4. J. Guidance and Control v.12 no.6 Control decoupling analysis for gyroscopic effects in rolling missiles Peter,W.Fortescue;Eduardo,M.Belo
  5. Missile Configuration Design S.S.Chin