제어로봇시스템학회:학술대회논문집
- 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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- Pages.647-652
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- 1994
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)
- 발행 : 1994.10.01
초록
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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