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dc.contributor.author毛修羽en_US
dc.contributor.authorMao, Xiu-Yuen_US
dc.contributor.author高一智en_US
dc.contributor.authorGao, Yi-Zhien_US
dc.date.accessioned2014-12-12T02:02:35Z-
dc.date.available2014-12-12T02:02:35Z-
dc.date.issued1982en_US
dc.identifier.urihttp://140.113.39.130/cdrfb3/record/nctu/#NT714146010en_US
dc.identifier.urihttp://hdl.handle.net/11536/51685-
dc.description.abstract當一高性能飛彈運作於其任務中時,由於飛行高度和速度的隨時不同,飛彈氣動力轉 換函數將發生快速而巨大的改變本文將探討如何設計一自適性自動駛儀,俾能克服上 述狀況的影響,而能有近似的響應。 文中就兩類設計方式,分基於明顯式的和隱含式的參數判別方法,提出三計。此三種 設計均以數位系模擬研究其結果,並比較和評估此三者之適用性。zh_TW
dc.language.isozh_TWen_US
dc.subject自適性zh_TW
dc.subject自動駕駛儀zh_TW
dc.subject氣動力轉換函數zh_TW
dc.subject明顯式參數判別法zh_TW
dc.subject隱含式參數判別法zh_TW
dc.subject數位系統zh_TW
dc.subject自動控制zh_TW
dc.subject控制工程zh_TW
dc.subject電腦zh_TW
dc.subjectAUTOMATIC-CONTROL-ENGINEERINGen_US
dc.subjectCONTROL-ENGINEERINGen_US
dc.subjectCOMPUTERen_US
dc.title自適性自動駕駛儀設計zh_TW
dc.typeThesisen_US
dc.contributor.department電控工程研究所zh_TW
Appears in Collections:Thesis