書誌事項
- タイトル別名
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- Captive Flight Testing in a Wind Tunnel for Identification of Dynamic Characteristics of a Small-Sized UAV
- コガタ ムジンキ ノ ドウトクセイ ドウテイ オ モクテキ ト シタ フウドウ ナイ ケイリュウ ヒコウ シケンホウ
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This paper presents the concept of dynamic wind tunnel testing using captive flight method, in which the airplane is supported by three elastic lines mainly in the vertical direction, and given oscillatory motions by an external actuator. This experimental method is designed for the aerodynamic parameter estimation. Longitudinal and lateral dynamic tests are carried out sweeping driving frequency, and every mode except surging motion, of which damping is weak, was excited. Aerodynamic parameters estimated from flight data showed good accordance with reference data. This experimental method has the advantages of the experimental simplicity, quite small aerodynamic interference, stable flight and the capability of the excitation of motion necessary for the estimation.
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 52 (605), 241-248, 2004
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
- 1390282679446709376
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- NII論文ID
- 10013078605
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- NII書誌ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL書誌ID
- 6992602
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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