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二自由度回転駆動振動検出型ジャイロの研究
https://jaxa.repo.nii.ac.jp/records/44533
https://jaxa.repo.nii.ac.jp/records/445337a20fc6a-1fef-40ec-8787-87130d932f5c
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00290.pdf (2.9 MB)
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| Item type | テクニカルレポート / Technical Report(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 二自由度回転駆動振動検出型ジャイロの研究 | |||||||||
| 言語 | ||||||||||
| 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） | ||||||||||
| その他のタイトル | Study of a Rotary-drive Vibratory-output Two-degree-of-freedom Gyro | |||||||||
| 著者 |
山田, 博
× 山田, 博
× YAMADA, Hiroshi
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| 著者所属 | ||||||||||
| 航空宇宙技術研究所計測部 | ||||||||||
| 著者所属（英） | ||||||||||
| en | ||||||||||
| Instrumentation and Control Division, National Aerospace Laboratory(NAL) | ||||||||||
| 出版者 | ||||||||||
| 出版者 | 航空宇宙技術研究所 | |||||||||
| 出版者（英） | ||||||||||
| 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-290 巻 290, p. 16, 発行日 1972-07 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | This paper reports a study of a rotary-drive vibratory-output two-degree-of-freedom gyro in order to give inertial refference as an attitude control component of a rocket and other such applications. The gyro has the advantage of eliminating error based on acceleration of rocket etc. The unconventional gyro can be constructed by mounting an asymmetrical rotor in two gimbals orthogonal each other. The moments of inertia of the rotor about its three principal axes are unequal. If the rotor is spun, at a constant angular rate, about one of its principal axes and an angular rate is applied to the gyro with a component in the plane of rotor rotation, some vibratory moment at twice the spin frequency of the rotor is separately developed about two gimbal axes normal to the rotor spin axis. These moments is respectively proportional to the sensed angular rate in magnitude, and has a phase that is related to the direction of the sensed angular rate in the rate-sensitive plane. A unique, trial production, gyro using an asymmetrical rotor has been produced and tested. This gyro uses elastic suspensions for the gimbals. A dynamic gas bearing that utilizes as the spin bearing is also used to suspend the asymmetrical rotor. The author has explained the function and the theory of operation of the gyro. Experimental results are presented for the trial production gyro. The experimental results agreed well with the theoretical description. These results show the rate resolution to be of the order 1×10(exp -3) deg/s based on a unity signal-to-noise ratio, and the author has confirmed the practicability of the gyro. | |||||||||
| ISSN | ||||||||||
| 収録物識別子タイプ | ISSN | |||||||||
| 収録物識別子 | 0389-4010 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: NALTR0290000 | |||||||||
| レポート番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | レポート番号: NAL TR-290 | |||||||||
