| Item type |
紀要論文 / Departmental Bulletin Paper(1) |
| 公開日 |
2015-03-26 |
| タイトル |
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タイトル |
KalmanフィルタによるL-4SC-3号機の推力飛しょう中のパラメータ推定について |
| 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_6501 |
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資源タイプ |
departmental bulletin paper |
| その他のタイトル（英） |
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その他のタイトル |
Application of Kalman Filtering Algorithm to Evaluate the Attitude Reference System of the L-4SC-3 Rocket. |
| 著者 |
石谷, 久
馬場, 康子
飯田, 幸栄
ISHITANI, Hisashi
BABA, Yasuko
IIDA, Sachie
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| 著者所属 |
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東京大学宇宙航空研究所 |
| 著者所属 |
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東京大学宇宙航空研究所 |
| 著者所属 |
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東京大学宇宙航空研究所 |
| 出版者 |
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出版者 |
東京大学宇宙航空研究所 |
| 書誌情報 |
東京大学宇宙航空研究所報告
巻 11,
号 4_A,
p. 825-837,
発行日 1975-11
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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 |
It is well known that the Kalman-Bucy filtering algorithm is most appropriate for estimating the latest state of the system by real time data processing with a digital computor. It becomes the optimum estimation in the sense that it gives the minimum variance and most likelihood estimator on the following conditions: The system and observation mechanism is represented by linear equations. The corresponding noise follows the normal distribution whose parameters are known beforehand, and used properly in the estimation. As a matter of course, this can be applied to trajectory estimation of the space vehicle with slight modification, and validity of the method for such purposes has been widely assured. Therefore, in order to estimate the most probable powered flight trajectories of sounding rockets launched at KSC from all the available imformation about the system state, Kalman filters are applied and formulated with necessary approximations and modifications. The system is linearized by applying the purturbation around the nominal trajectory and nine state variables are selected taking the properties of the system and quality of the available data into considerations. This filter was used to evaluate the newly adopted attitude reference system of L-4SC-3 rocket launched in September, 1974. The results are shown in this paper and they correspond well with that of telemetry data or a priori information about the system. If these telemetry data about the attitude or accerelation of the vehicle are provided instantaneously at the launching site in addition to the tracking radar data, the same filter can be applied to the real time trajectory estimation. As this filter also can be effectively utilized for off-1ine parameter estimation with iterative computation, we are now extending it to the optimum smoother. |
| 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 |
0563-8100 |
| 書誌レコードID |
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収録物識別子タイプ |
NCID |
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収録物識別子 |
AN00161914 |
| 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: SA0124534000 |
SA0124534.pdf (583.9 kB)
