查詢結果分析
來源資料
相關文獻
- 直昇機在總和能量控制架構下之狀態回授整合式飛行控制系統設計
- 飛彈縱向動態之狀態回授H垒/極點配置增益排程控制
- 在總合能量控制架構下採用狀態回授方式以H壵最佳化方法設計之整合式飛行/推力控制系統
- Sequential Eigenstructure Assignment with Minimal State-Feedback Gain
- Pole Clustering Inside a Disk for Generalized State-Space Systems-An LMI Approach
- Adaptive Digital Controlled Filter Design Using State-Feedback Approach
- Structurally Constrained H∞ Suboptimal Control Problems: Low-order Controller Design
- Robust Stabilization of Parameter Perturbed Systems with Delayed States and Control Delay
- Mixed H[feaf]/H垒 Cruise Control of High Speed Train via Linear Matrix Inequalities
- Stabilization Controller Design and Stability Criteria of the Perturbed Time-Delay Systems
頁籤選單縮合
題 名 | 直昇機在總和能量控制架構下之狀態回授整合式飛行控制系統設計=The Design of Helicopter State Feedback Integrated Flight Control System under the Total Energy Control Framework |
---|---|
作 者 | 壽鶴年; 鄭耀輝; 陳聖文; 楊憲東; 陳邦家; | 書刊名 | 航空技術學院學報 |
卷 期 | 5:1 民95.08 |
頁 次 | 頁335-344 |
分類號 | 447.738 |
關鍵詞 | 總和能量控制系統; 狀態回授; 線性矩陣不等式; 直昇機飛行控制; Total energy control system; State feedback; Linear matrix inequality; Helicopter flight control; |
語 文 | 中文(Chinese) |
中文摘要 | 本文目的在設計直昇機採用總和能量方式的飛行控制系統。藉由控制總和能量改變率與能量分配變化率,以達到對高度、速度、與飛行路徑角的追蹤。本文首先推導出直昇機在總和能量控制架構下之線性化動態模型。再運用H∞控制理論與線性矩陣不等式的控制器和成方法,以設計狀態回授型式的飛行控制器,最後觀察與討論直昇機受控系統的數值模擬結果。 |
英文摘要 | The purpose of this paper is to design a total energy control system for the helicopter, where energy changing rate and energy distribution rate are manipulated to achieve the tracking of altitude, speed, and flight path angle. First, we derive the linearized dynamic model for the helicopter suitable for design of a total energy control system. Then, by using the H∞ control theory and the method of the linear matrix inequality (LMI) synthesis, we construct the desired state-feedback flight controller. Finally, we observe and give discussion through the numerical simulations for the helicopter controlled system. |
本系統中英文摘要資訊取自各篇刊載內容。