Captive Flight Testing in a Wind Tunnel for Identification of Dynamic Characteristics of a Small-Sized UAV
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- Fukami Koji
- 九州大学工学府航空宇宙工学専攻
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- Higashino Shin-ichiro
- 九州大学工学府航空宇宙工学専攻
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- Sakurai Akira
- 九州大学工学府航空宇宙工学専攻
Bibliographic Information
- Other Title
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- 小型無人機の動特性同定を目的とした風洞内係留飛行試験法
- 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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Abstract
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.
Journal
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- JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 52 (605), 241-248, 2004
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
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Keywords
Details 詳細情報について
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- CRID
- 1390282679446709376
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- NII Article ID
- 10013078605
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- NII Book ID
- AA11307372
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- ISSN
- 24323691
- 13446460
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- NDL BIB ID
- 6992602
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- Text Lang
- ja
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- Data Source
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- JaLC
- NDL
- Crossref
- CiNii Articles
- KAKEN
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- Abstract License Flag
- Disallowed