{"created":"2023-06-20T15:03:02.374542+00:00","id":32137,"links":{},"metadata":{"_buckets":{"deposit":"36dcbd4e-0c42-4cda-aeda-1bce1eb774e2"},"_deposit":{"created_by":1,"id":"32137","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"32137"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00032137","sets":["1887:1890","1896:1898:1899:1910"]},"author_link":["407449","407451","407448","407450","407453","407452"],"item_9_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Radio Guidance Concept. Part II."}]},"item_9_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"1973-10","bibliographicIssueDateType":"Issued"},"bibliographicIssueNumber":"4","bibliographicPageEnd":"853","bibliographicPageStart":"832","bibliographicVolumeNumber":"9","bibliographic_titles":[{"bibliographic_title":"東京大学宇宙航空研究所報告"}]}]},"item_9_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"人工衛星の打上げにおいて,その達成軌道精度を向上させるためには,それ迄に受けた外乱を検出しつつ,その後の制御を最適化するフィードバック最適化手法の適用が有効であることは,明らかである.本文においては,2段目モータに推力軸制御装置を備え,最終段モータの打出し方向が制御可能な3段式ロケットの電波誘導方式を,実時間のフィードバック最適化の例として検討している.最終段モータに関する誘導法については,文献[1]に示されており,誘導プログラムは,L4SC-2号機打上げ実験において適用されているので,本文では,制御不可能な1段目モータの外乱を補正するための,2段目モータの誘導法を中心として,これを,その後につづく最終段モータの修正とあわせて,全体として最適化する手法について論じられている.これは,単に,2段階の動的最適問題の例に過ぎないが,1段階の正確な最適化計算(2段目モータに対するもの)は,その時点で同時に考慮すべきその後の段階の最適化のために,非常に複雑となる.この場合,ロケットエネルギーの有効利用の要求から,第1段燃焼終了後,筆2段モータ点火までの時間は十分とれず,最終段モータの最適化の場合の様に,最適化計算のために十分な計算時間は許されない.ただし,上と同じ理由により,第1段モータで受けた外乱は拡大していないので,標準軌道からの線形摂動の利用が可能であり,誘導の評価関数も,その後の最適化によって得られるその時間の最適評価を反映する様な,2段目軌道に関する二次形式で近似される.これらの近似により,計算は非常に簡単化され,2段目モータに対する最適解は直ちに求められる.更に,文献[1]に示されるすべての電波誘導読破は,この場合も利用可能である.この様な手法による,実際の誘導に対する適用可能性及び仮定の妥当性は,代表的な飛しょうデータにより,数値的に確認されている.また,この誘導において,最も重要な第1段モータ軌道の推定精度については,最近の実績結果より,10秒程度の推定で,十分な精度が得られることが示される.","subitem_description_type":"Abstract"}]},"item_9_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"It is well known that application of feedback optimization technique, a technique for detecting disturbances suffered so far and then optimizing the subsequent control strategy, is most effective to improve the accuracy of the orbit in launching a satellite. In this paper, a radio guidance concept for 3 stage launching rocket with a thrust vector controlled second stage motor and an injection controlled final motor is discussed as an example of real time feedback optimization. As to a guidance method concerning the final motor, its concept and algorithm have been already shown in ref. 1, and the radio guidance program was applied to L4SC-2 launching experiment. Therefore, the discussion is mainly focused on the guidance scheme for controlling the second stage motor to compensate disturbances caused by the uncontrolled first stage motor in an optimum way considering the succeeding correction for the final motor. Though this is a simple example of two step dynamic optimization problem, the precise calculation for the first step of optimization (guidance to the second stage motor) becomes very complex because of the following step of optimization, results of which are necessary to optimize the first step. In this case, a time interval for computation is not long enough to obtain the completely optimum guidance law, for the long time interval between burn out of the first motor and ignition of the second motor cannot be allowed because of the demand for effective use of rocket energy. However, as the disturbance suffered in the first stage flight is not enlarged for the same reason, a linear perturbation method developed at the nominal trajectory is applicable and the criterion function of this step is approximated by a quadratic function in terms of attainable trajectory parameters of the second stage flight. This function approximately represents the performance index for the first step optimization on the condition that the next step optimization is executed. With these approximations, the computation becomes very simple and a nearly optimum solution for this step can be obtained immediately. In addition, all hard-wares or radio guidance systems shown in ref. 1, are also available for this case. The adaptability of the method for practical experiments and the validity of assumptions are assured by the numerical examples applied to some typical flight data. The accuracy of trajectory estimation of the first stage flight that is most significant for the method is investigated, and the results of last few experiments show that the estimation from ten seconds data will give enough accuracy for this object.","subitem_description_type":"Other"}]},"item_9_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: SA0125264000","subitem_description_type":"Other"}]},"item_9_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"東京大学宇宙航空研究所"}]},"item_9_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"0563-8100","subitem_source_identifier_type":"ISSN"}]},"item_9_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AN00161914","subitem_source_identifier_type":"NCID"}]},"item_9_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"東京大学宇宙航空研究所"},{"subitem_text_value":"東京大学宇宙航空研究所"},{"subitem_text_value":"東京大学宇宙航空研究所"}]},"item_9_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeronautical Science"},{"subitem_text_language":"en","subitem_text_value":"Institute of Space and Aeronautical Science"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"石谷, 久"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"馬場, 康子"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"前田, 行雄"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"ISHITANI, Hisashi","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"BABA, Yasuko","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"MAEDA, Yukio","creatorNameLang":"en"}],"nameIdentifiers":[{}]}]},"item_files":{"attribute_name":"ファイル情報","attribute_type":"file","attribute_value_mlt":[{"accessrole":"open_date","date":[{"dateType":"Available","dateValue":"2020-01-24"}],"displaytype":"detail","filename":"SA0125264.pdf","filesize":[{"value":"1.6 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"SA0125264.pdf","url":"https://jaxa.repo.nii.ac.jp/record/32137/files/SA0125264.pdf"},"version_id":"7bbe0d24-a775-4b60-9c5f-77517a291030"}]},"item_language":{"attribute_name":"言語","attribute_value_mlt":[{"subitem_language":"jpn"}]},"item_resource_type":{"attribute_name":"資源タイプ","attribute_value_mlt":[{"resourcetype":"departmental bulletin paper","resourceuri":"http://purl.org/coar/resource_type/c_6501"}]},"item_title":"電波誘導方式(II)","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"電波誘導方式(II)"}]},"item_type_id":"9","owner":"1","path":["1890","1910"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"32137","relation_version_is_last":true,"title":["電波誘導方式(II)"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T00:40:03.350079+00:00"}