{"created":"2023-06-20T14:35:54.678230+00:00","id":2201,"links":{},"metadata":{"_buckets":{"deposit":"356efa1f-532c-45ce-8234-d76eb52358b8"},"_deposit":{"created_by":1,"id":"2201","owners":[1],"pid":{"revision_id":0,"type":"depid","value":"2201"},"status":"published"},"_oai":{"id":"oai:jaxa.repo.nii.ac.jp:00002201","sets":["1887:1893","9:10:200:222"]},"author_link":["4256","4259","4255","4254","4258","4257"],"item_3_alternative_title_2":{"attribute_name":"その他のタイトル（英）","attribute_value_mlt":[{"subitem_alternative_title":"Study on the residual strength and the test method for envelope materials after low altitude stationary flight test"}]},"item_3_biblio_info_10":{"attribute_name":"書誌情報","attribute_value_mlt":[{"bibliographicIssueDates":{"bibliographicIssueDate":"2007-03-31","bibliographicIssueDateType":"Issued"},"bibliographicVolumeNumber":"JAXA-RR-06-030","bibliographic_titles":[{"bibliographic_title":"宇宙航空研究開発機構研究開発報告"},{"bibliographic_title":"JAXA Research and Development Report","bibliographic_titleLang":"en"}]}]},"item_3_description_16":{"attribute_name":"抄録","attribute_value_mlt":[{"subitem_description":"成層圏プラットフォーム開発の一環として、2004年に北海道大樹町において定点滞空飛行試験が実施された。ベクトランおよびザイロンを基布とする高強度軽量膜材が本試験機に適用され、飛行試験においてその性能が十分であることを証明した。しかしながらこれらの膜材は運用によって劣化することが知られており、太陽光や紫外線に対する劣化対策が長期運用上の課題である。勿論、開発試験において環境劣化特性データを取得し、問題ないことを確認した上で実機に適用しているが、実際の運用環境下での劣化特性は、今後の開発に非常に貴重なデータとなる。そのため飛行試験終了後、実機から膜材を切り出し、保存しておいた補用品膜材および実機上に配置していた劣化モニタ膜材と共に各種試験を実施した。試験項目は、設計上重要と考えられる常温および高温での引張強度、常温での引裂き強度、高温クリープ強度を選定した。試験を実施するに当たって試験法の調査を行い、JIS(Japanese Industrial Standards)規格やFED-STD(Federal Standard)に則った膜材特有の試験法を採用した。その結果、補用品のデータが開発試験結果と比べて20％程度高い値を示し、適切な試験法によって材料本来の特性が取得できたと考えられる。換言すれば定点滞空試験機は安全側の設計値を使用していたことになる。ベクトラン膜材は飛行試験によって10％程度の引張強度低下が観測された。一方、ザイロン膜材は、本来成層圏プラットフォーム用に開発されたものと層構成が異なり、飛行試験によってかなりの強度低下が見られた。成層圏プラットフォーム用に開発されたものは劣化がほとんどなく、保護膜の選定が不適切な場合には劣化することが判明した。接合部のクリープ強度については、飛行試験後の膜材の寿命が開発試験に比べて長くなった。接合部の供試体の作成方法に問題があったと推定される。特に開発試験では短時間で破断していたザイロン膜材は、1,000時間でも全く破断せず、非常に良好なクリープ特性を有することが判明した。今後の開発に有用な飛行試験後の膜材データが取得できた。また高強度膜材に対する試験法の重要性が認識された。","subitem_description_type":"Abstract"}]},"item_3_description_17":{"attribute_name":"抄録（英）","attribute_value_mlt":[{"subitem_description":"The Low Altitude Stationary Flight Test was conducted at Taiki-cho, Hokkaido in 2004 as a part of the Stratospheric Platform development. High strength and lightweight envelope materials such as Vectran and Zylon were applied to the test vehicle and they have proven to have sufficient performances in the flight test. However, these materials are known to deteriorate during operation and measures to prevent deterioration caused by exposure to sunlight and ultraviolet rays are issues for their long life operation. Accordingly, data on their deterioration characteristics were obtained and the materials were applied to the Low Altitude Stationary Flight Test Vehicle after confirming durability. Nevertheless, the deterioration characteristics under actual operation are still very important data for the coming development. After the flight test, the envelope materials were cut off from the test vehicle and tested with spare materials and monitor materials placed on the top of the hull during the flight test. Test parameters were tensile strength at room and high temperatures, tear strength at room temperature, and creep strength at high temperature, all of which are important in the design. Before starting the test, test methods were investigated and the rigorous methods specified by JIS (Japanese Industrial Standards) and FED-STD (Federal Standard) were adopted. The tensile strengths of the spare materials were found to be about 20 percent higher than the development test results. It was possible to obtain their intrinsic material properties by selection of the proper test method. In other words conservative data were used in the design of the test vehicle. The Vectran envelope material showed a 10 percent reduction in tensile strength after the flight test. The Zylon envelope material, whose layer composition differs from that being developed for a stratospheric platform, showed a large reduction. The Zylon envelope material, which was developed for a stratospheric platform, showed almost no deterioration. This result made it clear that improper selection of the protective layer induces deterioration. Regarding the creep strength of the joint specimen, the test results after the flight test showed longer life than those of the development test. The specimen production method in the development test seems inappropriate. The Zylon envelope material which showed very short creep life in the development test did not rupture after 1,000 hours. Thus Zylon has demonstrated excellent creep strength. Valuable data on envelope materials after the flight test were obtained. It became clear that proper test method selection is very important for such high strength materials.","subitem_description_type":"Other"}]},"item_3_description_32":{"attribute_name":"資料番号","attribute_value_mlt":[{"subitem_description":"資料番号: AA0063462000","subitem_description_type":"Other"}]},"item_3_description_33":{"attribute_name":"レポート番号","attribute_value_mlt":[{"subitem_description":"レポート番号: JAXA-RR-06-030","subitem_description_type":"Other"}]},"item_3_publisher_8":{"attribute_name":"出版者","attribute_value_mlt":[{"subitem_publisher":"宇宙航空研究開発機構"}]},"item_3_publisher_9":{"attribute_name":"出版者（英）","attribute_value_mlt":[{"subitem_publisher":"Japan Aerospace Exploration Agency (JAXA)"}]},"item_3_source_id_21":{"attribute_name":"ISSN","attribute_value_mlt":[{"subitem_source_identifier":"1349-1113","subitem_source_identifier_type":"ISSN"}]},"item_3_source_id_24":{"attribute_name":"書誌レコードID","attribute_value_mlt":[{"subitem_source_identifier":"AA1192675X","subitem_source_identifier_type":"NCID"}]},"item_3_text_6":{"attribute_name":"著者所属","attribute_value_mlt":[{"subitem_text_value":"宇宙航空研究開発機構 航空プログラムグループ"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　安全・品質保証室"},{"subitem_text_value":"宇宙航空研究開発機構 総合技術研究本部　複合材技術開発センター"}]},"item_3_text_7":{"attribute_name":"著者所属（英）","attribute_value_mlt":[{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Aviation Program Group"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Safety and Quality Assurance Office, Institute of Aerospace Technology"},{"subitem_text_language":"en","subitem_text_value":"Japan Aerospace Exploration Agency Advanced Composite Technology Center, Institute of Aerospace Technology"}]},"item_creator":{"attribute_name":"著者","attribute_type":"creator","attribute_value_mlt":[{"creatorNames":[{"creatorName":"前川, 昭二"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"田中, 公人"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"濱口, 泰正"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Maekawa, Shoji","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Tanaka, Kimito","creatorNameLang":"en"}],"nameIdentifiers":[{}]},{"creatorNames":[{"creatorName":"Hamaguchi, Yasumasa","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":"2020-01-15"}],"displaytype":"detail","filename":"63462000.pdf","filesize":[{"value":"11.8 MB"}],"format":"application/pdf","licensetype":"license_note","mimetype":"application/pdf","url":{"label":"63462000.pdf","url":"https://jaxa.repo.nii.ac.jp/record/2201/files/63462000.pdf"},"version_id":"88de9a98-d46b-45e0-9739-f6711a2177db"}]},"item_keyword":{"attribute_name":"キーワード","attribute_value_mlt":[{"subitem_subject":"気球飛翔","subitem_subject_scheme":"Other"},{"subitem_subject":"薄膜","subitem_subject_scheme":"Other"},{"subitem_subject":"膜構造物","subitem_subject_scheme":"Other"},{"subitem_subject":"成層圏プラットフォーム飛行船","subitem_subject_scheme":"Other"},{"subitem_subject":"飛行試験","subitem_subject_scheme":"Other"},{"subitem_subject":"ベクトラン","subitem_subject_scheme":"Other"},{"subitem_subject":"ザイロン","subitem_subject_scheme":"Other"},{"subitem_subject":"引張強度","subitem_subject_scheme":"Other"},{"subitem_subject":"引張試験","subitem_subject_scheme":"Other"},{"subitem_subject":"疲労試験","subitem_subject_scheme":"Other"},{"subitem_subject":"残留強度","subitem_subject_scheme":"Other"},{"subitem_subject":"クリープ強度","subitem_subject_scheme":"Other"},{"subitem_subject":"balloon flight","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"thin film","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"membrane structure","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"stratospheric platform airship","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"flight test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Vectran","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"Zylon","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"tensile strength","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"tensile test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"fatigue test","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"residual strength","subitem_subject_language":"en","subitem_subject_scheme":"Other"},{"subitem_subject":"creep strength","subitem_subject_language":"en","subitem_subject_scheme":"Other"}]},"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":"technical report","resourceuri":"http://purl.org/coar/resource_type/c_18gh"}]},"item_title":"定点滞空飛行試験後の膜材残留強度及び試験法評価","item_titles":{"attribute_name":"タイトル","attribute_value_mlt":[{"subitem_title":"定点滞空飛行試験後の膜材残留強度及び試験法評価"}]},"item_type_id":"3","owner":"1","path":["222","1893"],"pubdate":{"attribute_name":"公開日","attribute_value":"2015-03-26"},"publish_date":"2015-03-26","publish_status":"0","recid":"2201","relation_version_is_last":true,"title":["定点滞空飛行試験後の膜材残留強度及び試験法評価"],"weko_creator_id":"1","weko_shared_id":-1},"updated":"2023-06-21T09:26:44.804798+00:00"}