書誌事項
- タイトル別名
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- Online Guidance Law of Missile Using Multiple Design Point Method
- フクスウ セッケイテンホウ オ リヨウ シタ ヒショウタイ ノ オンライン ユウドウソク
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This paper deals with design procedure of online guidance law for future missiles that are required to have agile maneuverability. For the purpose, the authors propose to mount high power side-thrusters on a missile. The guidance law for such missiles is discussed from a point of view of optimal control theory in this paper. Minimum time problem is solved for the approximated system. It is derived that bang-bang control is optimal input from the necessary conditions of optimal solution. Feedback guidance without iterative calculation is useful for actual systems. Multiple design point method is applied to design feedback gains and feedforward inputs of the guidance law. The numerical results show the good performance of the proposed guidance law.
収録刊行物
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- 日本航空宇宙学会論文集
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日本航空宇宙学会論文集 58 (674), 61-67, 2010
一般社団法人 日本航空宇宙学会
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詳細情報 詳細情報について
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- CRID
- 1390282679445764096
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- NII論文ID
- 10026520628
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- NII書誌ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL書誌ID
- 10619384
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- 本文言語コード
- ja
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- データソース種別
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- JaLC
- NDL
- Crossref
- CiNii Articles
- KAKEN
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- 抄録ライセンスフラグ
- 使用不可