Flow control with pitching motion of UAV using MEMS flow sensors
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A new pitch controller for our developed small airplane was designed, and its ability was confirmed by simulation. In the pitch controller, outputs from the MEMS (Micro Electro Mechanical System) flow sensor and the transfer function determined by the results of the wind tunnel tests are used. MEMS technology is a key technology of this pitch controller.
資料番号: AA0063908010
レポート番号: JAXA-SP-07-026E
収録刊行物
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- 宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集 第40回 = JAXA Special Publication: Proceedings of the 40th JAXA Workshop on Investigation and Control of Boundary-Layer Transition
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宇宙航空研究開発機構特別資料: 境界層遷移の解明と制御研究会講演論文集 第40回 = JAXA Special Publication: Proceedings of the 40th JAXA Workshop on Investigation and Control of Boundary-Layer Transition JAXA-SP-07-026E 31-34, 2008-02-29
宇宙航空研究開発機構
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詳細情報 詳細情報について
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- CRID
- 1050574036210396160
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- NII論文ID
- 120006828995
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- NII書誌ID
- AA11984031
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- ISSN
- 1349113X
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- Web Site
- http://id.nii.ac.jp/1696/00005525/
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- 本文言語コード
- en
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- 資料種別
- conference paper
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- データソース種別
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- IRDB
- CiNii Articles