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題 名 | Variable Structure Controller for a Supersonic Missile Autopilot Design=超音速飛彈之可變結構自動駕駛儀設計 |
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作 者 | 蔡添壽; | 書刊名 | 國立虎尾科技大學學報 |
卷 期 | 25:2 民95.06 |
頁 次 | 頁23-33 |
分類號 | 448.942 |
關鍵詞 | 非線性強健控制; 飛彈飛行控制系統; Nonlinear robust control; Missile flight control system; |
語 文 | 英文(English) |
中文摘要 | 本文提出一個含智慧型非線性的改良型可變結構控制器,它被運用及改善一個受硬體限制及高氣動力藕連的超音速地對空飛彈的滾轉頻道上,此一控制器為數位控制器,簡單容易實現且保持現役飛彈自動駕駛儀的控制系統架構,它大幅擴展傳統設計的穩定裕度邊界。所有 分析與設計結果都經由五自由度及六自由度飛行模擬驗證。穩定裕度的大幅改善,可以提昇飛彈對付更高速運動目標的性能。 |
英文摘要 | A modified digital variable structure controller with intelligent nonlinearity is proposed and used in the rolling channel to improve the robustness of a hardware limited, severe aerodynamic coupled supersonic surface-to-air missile. The analyses and designs of the considered system are simple and found digital controllers are easy to be implemented. They keep the well proven control configurations of the real missile flight control systems and active at the stability boundaries of the conventional design to enlarge the stability boundaries. All analyzed and designed results are verified by 5 and 6 degree of freedom simulations. Robustness of the compensated system is improved significantly for promoting missile performance to engage faster maneuvering targets. |
本系統中英文摘要資訊取自各篇刊載內容。