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軌道決定のためのフィルタリング理論-航技研における軌道決定プログラムKOSMOS-
https://jaxa.repo.nii.ac.jp/records/44809
https://jaxa.repo.nii.ac.jp/records/4480989da415e-9a01-4c09-b1ab-7f6e6be31a0f
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
naltr00555.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 | 軌道決定のためのフィルタリング理論-航技研における軌道決定プログラムKOSMOS- | |||||||||
| 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 | Filtering Theory Applied to Near-Earth Satellite Orbit Determination -NAL Satistical Multi-mode Orbit Processing System KOSMOS- | |||||||||
| 著者 |
村田, 正秋
× 村田, 正秋
× MURATA, Masaaki
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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-555 巻 555, p. 43, 発行日 1978-12 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | This report presents both the mathematical specifications of the KOken Statistical Multimode Orbit Processing System(KOSMOS) and its applications to the near-Earth satellite orbit determination problem. The specifications include time, coordinates, satellite dynamics, perturbations with its variational equations, radar tracking equations, as well as problems in statistical orbit determination theory. To evaluate the accuracy of the filtering theory methods applied to orbit determination, extensive simulation studies were conducted using the KOSMOS. From the generated range and range-rate observations at the Katsuura, Masuda, and Okinawa tracking stations, it was found that the accuracy, commensurate with the observation precisions, could be achieved by the extended sequential processor with the State Noise Compensation(SNC) method. Evidence is also presented indicating that, for a sufficiently dense observation data set, the unmodeled acceleration could be recovered by the extended sequential processor through the Dynamic Model Compensation(DMC) method, and that the DMC method can improve the estimation accuracy of the state of the satellite. However the cost of the increased processing time which is about twice more than that of the SNC method, must be paid. Furthermore, the U-D covariance factorization algorithm is discussed and implemented to investigate the effects of the observation type and precision, as well as the effects of mismodeled observation noise level. | |||||||||
| 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: NALTR0555000 | |||||||||
| 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-555 | |||||||||
