Guidance law for a missile after thrust cutoff

  • Baba, Yoriaki (Department of Aerospace Engineering, National Defence Academy) ;
  • Kishitani, Harunobu (Department of Aerospace Engineering, National Defence Academy) ;
  • Takano, Hiroyuki (Department of Aerospace Engineering, National Defence Academy)
  • Published : 1994.10.01

Abstract

In the previous paper, we presented a new guidance law for a missile during boost phase. Thus, this paper deals with the guidance law for a missile after the thrust cutoff against an accelerating and turning target. It is essentially based on the concept of proportional navigation. Some simulation studies were performed using a three dimensional mathematical model of an air-to-air missile and the effectiveness of the guidance law presented was shown.

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