{"created":"2023-06-20T14:40:36.097408+00:00","id":7514,"links":{},"metadata":{"_buckets":{"deposit":"50ad14e4-1922-4545-a921-b1bff7d03ee0"},"_deposit":{"created_by":1,"id":"7514","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"7514"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00007514","sets":["1543:1544:1557","1887:1891"]},"author_link":["40075","40076"],"item_5_alternative_title_1":{"attribute_name":"その他のタイトル","attribute_value_mlt":[{"subitem_alternative_title":"惑星探査機の軌道推定解析"}]},"item_5_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03","bibliographicIssueDateType":"Issued"},"bibliographicPageEnd":"77","bibliographicPageStart":"72","bibliographic_titles":[{"bibliographic_title":"第16回アストロダイナミクスシンポジウム講演後刷り集　2006"},{"bibliographic_title":"Proceedings of 16th Workshop on JAXA Astrodynamics and Flight Mechanics","bibliographic_titleLang":"en"}]}]},"item_5_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"惑星ミッションの航法として、電波(レンジ・ドップラー)による軌道推定はダイナミクスとして地上局の特性による不確定性と探査機の加速度の不確定性が推定誤差に影響を及ぼす。従来、観測量を十分に取得し不確定なパラメータを推定項目に入れ、バッチによる最小自乗フィルタで推定するのが一般的であるが、この不確定な要素に対しある程度の拘束条件を付加することでフィルタの次元低下が可能となる。本論ではこのフィルタおよび金星ミッションを仮定してX帯の周波数下の観測量に対する評価を行ったので述べる。","subitem_description_type":"Abstract"}]},"item_5_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The error budget analysis is presented which quantifies the effects of different error sources in the Earth-based orbit determination process when the orbit estimation filter is used to reduce radio metric data. The estimator strategy differs from more traditional filtering methods in the nearly all of the principal ground system calibration errors affecting the data are represented as filter parameters. Error budget computations were performed for a Venus mission interplanetary cruise scenario for cases in which only X-band Doppler data were used to determine the spacecraft's orbit, X-band ranging data were used exclusively, and combined set in which the ranging data were used in addition to the Doppler data. Random nongravitational accelerations were found to the largest source of error contributing to the individual error budgets.","subitem_description_type":"Other"}]},"item_5_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063481013","subitem_description_type":"Other"}]},"item_5_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構宇宙科学研究本部"}]},"item_5_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)"}]},"item_5_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構 宇宙科学研究本部"}]},"item_5_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Institute of Space and Astronautical Science"}]},"item_access_right":{"attribute_name":"アクセス権","attribute_value_mlt":[{"subitem_access_right":"metadata only access","subitem_access_right_uri":"http://purl.org/coar/access_right/c_14cb"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"市川, 勉"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Ichikawa, Tsutomu","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"軌道位置推定","subitem_subject_scheme":"Other"},{"subitem_subject":"衛星ドップラ位置決め","subitem_subject_scheme":"Other"},{"subitem_subject":"測距","subitem_subject_scheme":"Other"},{"subitem_subject":"カルマンフィルタ","subitem_subject_scheme":"Other"},{"subitem_subject":"感度解析","subitem_subject_scheme":"Other"},{"subitem_subject":"宇宙探査","subitem_subject_scheme":"Other"},{"subitem_subject":"推定","subitem_subject_scheme":"Other"},{"subitem_subject":"誤差","subitem_subject_scheme":"Other"},{"subitem_subject":"誤差解析","subitem_subject_scheme":"Other"},{"subitem_subject":"ドップラレーダ","subitem_subject_scheme":"Other"},{"subitem_subject":"軌道推定フィルタ","subitem_subject_scheme":"Other"},{"subitem_subject":"最適推定量","subitem_subject_scheme":"Other"},{"subitem_subject":"推定誤差","subitem_subject_scheme":"Other"},{"subitem_subject":"orbital position estimation","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"satellite Doppler positioning","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"rangefinding","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Kalman filter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"sensitivity analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"space exploration","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"estimating","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"error","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"error analysis","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Doppler radar","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"orbit estimation filter","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"optimal estimator","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"estimation error","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"eng"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"conference paper","resourceuri":"http://purl.org/coar/resource_type/c_5794"}]},"item_title":"Orbit estimation analysis for interplanetary mission","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"Orbit estimation analysis for interplanetary mission","subitem_title_language":"en"}]},"item_type_id":"5","owner":"1","path":["1557","1891"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"7514","relation_version_is_last":true,"title":["Orbit estimation analysis for interplanetary mission"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T07:38:20.415615+00:00"}