著者

土肥 直人 馬場 順昭 高野 博行

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.52, no.605, pp.280-288, 2004 (Released:2004-06-30)

参考文献数

8

被引用文献数

1 1

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This paper presents a new guidance law for a missile with varying velocity against a maneuvering target with a constant acceleration. Since an approximate missile velocity change during boost phase or after thrust cutoff can be calculated, the intercept point can be estimated if the target acceleration is measured. The guidance law presented guides the missile to the point directly. The guidance law is constructed by combining augmented proportional navigation and pure pursuit navigation with some mixture ratio. From some simulations, it is found that the guidance law presented is more effective and has the higher off-boresight ability and the smaller lateral divert requirements than conventional augmented proportional navigation or proportional navigation even if there exist the LOS angle noises.

著者

土肥 直人 馬場 順昭 高野 博行

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.51, no.594, pp.380-387, 2003 (Released:2003-09-26)

参考文献数

10

被引用文献数

1 1

---

This paper deals with a guidance law for a flight vehicle with varying velocity after thrust cutoff. This guidance law is mechanized by combining the proportional navigation and the pure pursuit navigation with the mixture ratio. Since the performance of the guidance law depends on the ratio, the discussion is focused on the determination of the ratio. Finally, the simulation results show that if the LOS angle noises are small, the proposed guidance law is effective even if the missile velocity decreases and has higher off-boresight ability than the proportional navigation.

著者

高野 博行 馬場 順昭

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.47, no.547, pp.117-121, 1999-08-05 (Released:2019-04-09)

参考文献数

6