| 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 |
クインエア機の縦の安定操縦微係数の推定 |
| 言語 |
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言語 |
jpn |
| 資源タイプ |
|
|
資源タイプ識別子 |
http://purl.org/coar/resource_type/c_18gh |
|
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 |
Determination of Longitudinal Stability and Control Derivatives of the Queen Air |
| 著者 |
森, 幹彦
真柳, 光美
名越, 孝行
後藤, 芳夫
照井, 祐之
MORI, Mikihiko
MAYANAGI, Mitsuyoshi
NAGOSHI, Takayuki
GOTO, Yoshio
TERUI, Yushi
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| 著者所属 |
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航空宇宙技術研究所計測部 |
| 著者所属 |
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航空宇宙技術研究所計測部 |
| 著者所属 |
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航空宇宙技術研究所計測部 |
| 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 |
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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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Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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|
en |
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Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Instrumentation and Control Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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en |
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Flight Research Division, National Aerospace Laboratory(NAL) |
| 著者所属（英） |
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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-406
巻 406,
p. 30,
発行日 1975-02
|
| 抄録（英） |
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内容記述タイプ |
Other |
|
内容記述 |
The longitudinal stability and control derivatives of the Beechcraft Queen Air-Model 65-were determined from the flight data for landing and cruising flight configurations. The result will be used for designing an automatic landing system for the airplane. To analyze the flight data, the least square method of conventional derivative type was adopted, which brought the raw estimate of derivatives with considerable variations depending upon the sampling intervals. The final value of each derivatives was determined by a simulated computation and was compared with the wind tunnel test data. The accuracy of the derivatives is estimated to be of about 50 percent error for stability derivatives and less than 30 percent for control derivatives. Of noticed is a large discrepancy which exists in the two values of Mα derived from the flight test and the wind tunnel test. Since Mα is one of the most important derivatives, a detailed simulation was made to confirm the appropriateness of the flight test result, and it was concluded that the discrepancy is apparent because the reference points of the pitching moment were different for the flight test and the wind tunnel test. Also regarding the role of Mα in the motion of an airplane, the generally used two degree of freedom approximation to a long period motion was examined, and another expressions for ωnph and ζph were obtained. These expressions are suitably applicable to approximate the long period dynamics of an airplane with small |Mα|. |
| ISSN |
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収録物識別子タイプ |
ISSN |
|
収録物識別子 |
0389-4010 |
| 資料番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
資料番号: NALTR0406000 |
| レポート番号 |
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|
内容記述タイプ |
Other |
|
内容記述 |
レポート番号: NAL TR-406 |
naltr00406.pdf (2.6 MB)
