Experimental Study on the Application of Flat Spin to Vertical Landing of a Fixed-Wing Small UAV
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- HIGASHINO Shin-Ichiro
- Department of Aeronautics and Astronautics, Kyushu University
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- NAKAMA Kota
- Department of Aeronautics and Astronautics, Kyushu University Currently, Kawasaki Heavy Industries
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- SUMITOMO Yuki
- Department of Aeronautics and Astronautics, Kyushu University Currently, Kawasaki Heavy Industries
説明
<p>The flat spin of a fixed-wing airplane is usually considered to be dangerous, and should be avoided by all means. However, an airplane in a flat spin descends almost vertically and relatively slowly. It can be used as a means of vertical landing, especially for a small fixed-wing unmanned aerial vehicle. Controlling the impact speed to the ground and touchdown position is necessary to realize the application of flat-spin landing. A large pitch-up moment generated by the combination of an all-flying tail and the gyro precession due to the yawing motion generated by the so-called P-factor of the propeller rotation was found to be effective not only for the rapid entry into flat spin, but also to control the pitch attitude and rate of descent during a flat spin. In this paper, the results regarding the relationships among the deflection angle of the all-flying tail, the rotational speed of the propeller, the spin rate, and the rate of descent obtained by flight tests using a small unmanned aerial vehicle are presented as fundamental knowledge towards the realization of practical flat-spin landing.</p>
収録刊行物
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- TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN
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TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 20 (0), 1-9, 2022
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
- 1390290617367706752
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- NII論文ID
- 130008139196
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- ISSN
- 18840485
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- HANDLE
- 2324/4774242
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- 本文言語コード
- en
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- データソース種別
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- JaLC
- IRDB
- Crossref
- CiNii Articles
- KAKEN
- OpenAIRE
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- 抄録ライセンスフラグ
- 使用不可
