{"_buckets": {"deposit": "cc7258d4-46c6-4bed-ac75-f63a9b146a62"}, "_deposit": {"id": "30072", "owners": [], "pid": {"revision_id": 0, "type": "depid", "value": "30072"}, "status": "published"}, "_oai": {"id": "oai:nagoya.repo.nii.ac.jp:00030072"}, "item_10_biblio_info_6": {"attribute_name": "\u66f8\u8a8c\u60c5\u5831", "attribute_value_mlt": [{"bibliographicIssueDates": {"bibliographicIssueDate": "2020-03", "bibliographicIssueDateType": "Issued"}, "bibliographicIssueNumber": "2", "bibliographicPageEnd": "263", "bibliographicPageStart": "256", "bibliographicVolumeNumber": "36", "bibliographic_titles": [{"bibliographic_title": "Journal of Propulsion and Power"}]}]}, "item_10_description_4": {"attribute_name": "\u6284\u9332", "attribute_value_mlt": [{"subitem_description": "In this study, an electrostatic thruster was newly developed, in which a diverging magnetic field with a cusp around a cathode was applied by using two solenoid coils. The effects of the magnetic field strength on thrust performance under a similar applied-magnetic-field configuration were investigated. Because of its light weight and lower price, argon was used as a propellant. By increasing the magnetic field strength, the thrust efficiency was improved owing to the suppression of the discharge current while an almost constant thrust was maintained. A specific impulse of 3800 s with thrust efficiency greater than 30% was obtained; the corresponding mass-averaged exhaust velocity exceeded the value by full-potential electrostatic acceleration of singly charged ions. From the thrust performance, ion beam current, and ion energy distribution function that were experimentally measured under the representative operation condition, 32% of the ion beam current and 43% of the total thrust were evaluated as the contribution of doubly charged ions.", "subitem_description_type": "Abstract"}]}, "item_10_publisher_32": {"attribute_name": "\u51fa\u7248\u8005", "attribute_value_mlt": [{"subitem_publisher": "American Institute of Aeronautics and Astronautics"}]}, "item_10_relation_11": {"attribute_name": "DOI", "attribute_value_mlt": [{"subitem_relation_type_id": {"subitem_relation_type_id_text": "https://doi.org/10.2514/1.B37675", "subitem_relation_type_select": "DOI"}}]}, "item_10_rights_12": {"attribute_name": "\u6a29\u5229", "attribute_value_mlt": [{"subitem_rights": "Copyright \u00a9 2020 by Daisuke Ichihara, Toshihiro Matsuba, Akira Iwakawa, and Akihiro Sasoh. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-3876 to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp."}]}, "item_10_select_15": {"attribute_name": "\u8457\u8005\u7248\u30d5\u30e9\u30b0", "attribute_value_mlt": [{"subitem_select_item": "author"}]}, "item_10_source_id_61": {"attribute_name": "ISSN\uff08print\uff09", "attribute_value_mlt": [{"subitem_source_identifier": "1533-3876", "subitem_source_identifier_type": "ISSN"}]}, "item_creator": {"attribute_name": "\u8457\u8005", "attribute_type": "creator", "attribute_value_mlt": [{"creatorNames": [{"creatorName": "Ichihara, Daisuke"}], "nameIdentifiers": [{"nameIdentifier": "99189", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Matsuba, Toshihiro"}], "nameIdentifiers": [{"nameIdentifier": "99190", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Iwakawa, Akira"}], "nameIdentifiers": [{"nameIdentifier": "99191", "nameIdentifierScheme": "WEKO"}]}, {"creatorNames": [{"creatorName": "Sasoh, Akihiro"}], "nameIdentifiers": [{"nameIdentifier": "99192", "nameIdentifierScheme": "WEKO"}]}]}, "item_files": {"attribute_name": "\u30d5\u30a1\u30a4\u30eb\u60c5\u5831", "attribute_type": "file", "attribute_value_mlt": [{"accessrole": "open_date", "date": [{"dateType": "Available", "dateValue": "2020-05-26"}], "displaytype": "detail", "download_preview_message": "", "file_order": 0, "filename": "JPP-B37675_AUTHOR_submitted.pdf", "filesize": [{"value": "990.2 kB"}], "format": "application/pdf", "future_date_message": "", "is_thumbnail": false, "licensetype": "license_free", "mimetype": "application/pdf", "size": 990200.0, "url": {"label": "JPP-B37675_AUTHOR_submitted", "url": "https://nagoya.repo.nii.ac.jp/record/30072/files/JPP-B37675_AUTHOR_submitted.pdf"}, "version_id": "5a34157b-9297-489a-bbac-67b11b32645f"}]}, "item_language": {"attribute_name": "\u8a00\u8a9e", "attribute_value_mlt": [{"subitem_language": "eng"}]}, "item_resource_type": {"attribute_name": "\u8cc7\u6e90\u30bf\u30a4\u30d7", "attribute_value_mlt": [{"resourcetype": "journal article", "resourceuri": "http://purl.org/coar/resource_type/c_6501"}]}, "item_title": "High-Specific-Impulse Electrostatic Thruster with Argon Propellant", "item_titles": {"attribute_name": "\u30bf\u30a4\u30c8\u30eb", "attribute_value_mlt": [{"subitem_title": "High-Specific-Impulse Electrostatic Thruster with Argon Propellant"}]}, "item_type_id": "10", "owner": "1", "path": ["320/321/322"], "permalink_uri": "http://hdl.handle.net/2237/00032258", "pubdate": {"attribute_name": "\u516c\u958b\u65e5", "attribute_value": "2020-05-26"}, "publish_date": "2020-05-26", "publish_status": "0", "recid": "30072", "relation": {}, "relation_version_is_last": true, "title": ["High-Specific-Impulse Electrostatic Thruster with Argon Propellant"], "weko_shared_id": null}