| Item type |
テクニカルレポート / Technical Report(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
フライングテストベッド・ホバー実験-第5次実験- |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
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資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
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資源タイプ |
technical report |
| その他のタイトル（英） |
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その他のタイトル |
Hover Control Tests on Flying Test Bed for VTOL Aircraft |
| 著者 |
滝澤, 直人
藤枝, 郭俊
小野, 幸一
田辺, 義一
渋谷, 昭義
小川, 敏雄
甲斐, 忠夫
宮本, 義人
鳥崎, 忠雄
後藤, 芳夫
TAKIZAWA, NAOTO
FUJIEDA, Hirotoshi
ONO, Koichi
TANABE, Yoshikazu
SHIBUYA, Akiyoshi
OGAWA, Toshio
KAI, Tadao
MIYAMOTO, Yoshito
TORISAKI, Tadao
GOTO, Yoshio
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| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所機体第一部 |
| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所新型航空機研究グループ |
| 著者所属 |
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航空宇宙技術研究所原動機部 |
| 著者所属 |
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航空宇宙技術研究所飛行実験部 |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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V/STOL Aircraft Research Group, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Aeroengine Division, National Aerospace Laboratory(NAL) |
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en |
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Flight Research Division, National Aerospace Laboratory(NAL) |
| 出版者 |
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出版者 |
航空宇宙技術研究所 |
| 出版者（英） |
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出版者 |
National Aerospace Laboratory(NAL) |
| 書誌情報 |
航空宇宙技術研究所報告
en : Technical Report of National Aerospace Laboratory TR-425
巻 425,
p. 54,
発行日 1975-09
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| 抄録（英） |
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内容記述タイプ |
Other |
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内容記述 |
This paper describes hover control tests on the Flying Test Bed(FTB) which has been developed by the National Aerospace Laboratory to study problems associated with hovering and vertical takeoff and landing operations of VTOL aircraft. The tests were carried out in four steps. The first step was composed of three preliminary tests and five semi-constrained attitude control tests(roll and pitch) by remote controlled step-input. The second step was composed of twelve semi-constrained attitude control tests by two pilots(in two-and three-degree-of-freedom). The third step was composed of four tie-down tests with the crew. The last step was composed of two ground operation tests and five free flight tests by two pilots. The Semi-constrained attitude control tests showed good characteristics of the attitude control system including the automatic stabilization equipment of the FTB. Control stick travel was within 15％ of the half stroke respectively to maintain the neutral attitude. The tie-down tests showed that adverse effects of exhaust gas were not found in undercarriage temperature, surface winds, ground erosion and noxious fumes. Various maximum values in the free flight tests were as follows: height; 2.5m clear, vertical acceleration; 0.02g at climb, -0.03g at descent, 0.185g at touch down, attitude angle; 2.5deg in roll and pitch, yawing velocity; 1.75deg/s, flight time; 3 min 55s(total 12min 40s). The free flight hover control tests showed good control characteristics for force gradients, sensitivities, power, rate damping levels and overall effects on pilot feeling. The FTB remained within a height of ±0.3m and a level of ±0.5m in the 4～8m/s windy condition. It was conjectured that the FTB remained within a sphere of 0.1m in radius under windless condition. The ground effects were negligible for 0.5m height hover, takeoff and landing. The pilots evaluated roll and pitch control characteristics as excellent and the yaw and height control characteristics were comparable to current helicopters. FTB vibration on the ground was most noticeable an engine speed of 11,500 rpm, but it disappeared above this speed. During hover, rolling, pitching and vertical vibrations were noted, and their frequencies were 1.4, 0.8 and 0.2～0.3Hz respectively. The first two were regarded as induced vibration through the pilot as a mechanical element, and the last was regarded as vibration due to pilot control, but the pilot did not feel these vibrations. |
| ISSN |
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収録物識別子タイプ |
ISSN |
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収録物識別子 |
0389-4010 |
| 資料番号 |
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内容記述タイプ |
Other |
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内容記述 |
資料番号: NALTR0425000 |
| レポート番号 |
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内容記述タイプ |
Other |
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内容記述 |
レポート番号: NAL TR-425 |
naltr00425.pdf (5.6 MB)
