| タイトル | シングルロータヘリコプタとクワッドロータ機の比較 |
| その他のタイトル | Comparison between a Single Rotor Helicopter and a Quad Rotor UAV |
| 著者（日） | 宮下, 亮; 砂田, 茂; 田辺, 安忠; 青山, 剛史 |
| 著者（英） | Miyashita, Ryo; Sunada, Shigeru; Tanabe, Yasutada; Aoyama, Takashi |
| 著者所属（日） | 大阪府立学; 大阪府立学; 宇宙航空研究開発機構(JAXA); 宇宙航空研究開発機構(JAXA) |
| 著者所属（英） | Osaka Prefecture University; Osaka Prefecture University; Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA) |
| 発行日 | 2014-12-05 |
| 発行機関など | 日本航空宇宙学会
Japan Society for Aeronautical and Space Sciences |
| 刊行物名 | 日本航空宇宙学会論文集
Journal of the Japan Society for Aeronautical and Space Sciences |
| 巻 | 62 |
| 号 | 6 |
| 開始ページ | 193(9) |
| 終了ページ | 197(13) |
| 刊行年月日 | 2014-12-05 |
| 言語 | jpn
eng |
| 抄録 | Flight control of quad rotor UAVs has been studied by a number of research groups. However, a reason for the stable flight of quad rotor UAVs has not been revealed yet. In the present paper, advantages of quad rotor UAVs against a single rotor helicopter are discussed. In the analysis, their weights are assumed to be same. When they encounter a side wind gust, the effect of the gust on the motion of the quad rotor UAVs is smaller than that on the single rotor helicopter. This is a big advantage of the quad rotor UAVs against the single rotor helicopters. |
| 内容記述 | 形態: 図版あり
Physical characteristics: Original contains illustrations |
| キーワード | Yaw Damping; Quad-Rotor; Single Rotor Helicopter; Tail Rotor; UAV |
| 資料種別 | Journal Article |
| NASA分類 | Aircraft Design, Testing and Performance |
| ISSN | 1344-6460 |
| NCID | AA11307372 |
| SHI-NO | AA1540160002 |
| URI | https://repository.exst.jaxa.jp/dspace/handle/a-is/558542 |
