日本航空宇宙学会論文集
Online ISSN : 2432-3691
Print ISSN : 1344-6460
ISSN-L : 1344-6460
Articles
μ 設計を用いた比例航法のための補償器の設計
熊谷 賢治越智 徳昌
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2005 年 53 巻 614 号 p. 116-122

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This paper proposes a design method of a missile guidance system with robust control. The design method provides a compensator for the proportional navigation guidance law, explicitly considering the uncertainties by employing the μ-synthesis, a design method of robust control systems. The proposed method has two features: One is that the plant is modeled so that the feedback signal becomes the same as that of the proportional navigation, i.e., the relative velocity multiplied by the line-of-sight angular rate. The other is that the controlled output is chosen to be the component of the relative velocity perpendicular to the line of sight, instead of the line-of-sight angular rate, which is usually chosen in guidance law design based on modern control. Computer simulation is performed using a two-dimensional engagement model to show the effectiveness of the guidance law.

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© 2005 The Japan Society for Aeronautical and Space Sciences
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