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題名 | 飛行追蹤控制系統之非極小相分析 |
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作者 | 張松國; | 書刊名 | 華岡工程學報 |
卷期 | 9 1995.07[民84.07] |
頁次 | 頁277-292 |
分類號 | 447.85 |
關鍵詞 | 飛行追蹤控制系統; |
語文 | 中文(Chinese) |
中文摘要 | 飛行追蹤控制系統的任務在精確地追蹤導航命令,使追蹤誤差降至最小。但是飛行控制系統如果有非極小相存在,常造成控制的難題,結果使追蹤控制系統誤差增加,無法作完美的追蹤。非線性系統在作輸出輸入線性化處理時,系統若含有非極小相的特性,會使線性化的系統產生不穩定的現像。在本文中分別由線性及非線性理論導出飛行系統判斷非線性極小相存在的特性方程式,可作為飛行追蹤控制設計改進的依據。 |
英文摘要 | It is well known that bank to turn steering is more attractive in terms of missile performance over skid to turn steering Author (Chang1990) delived a nonlinear misslile dynamic model of six of degree freedom and proposed an optimal nonlinear tracking control method to solve this problem. But the nonlinear nonminimun phase problem still existed in missile system is needed to be solved. It is known that the mission of missile tracking control system is to follow the guidance command perfectly and the tracking error must be reduced to be minimum. If a nonminimun guidance command exactly and the tracking error is increased. A nonlinear system is linearized by output input linearization, the linearized system will have a unstable phenomenon if the system have a nominimun phase. This paper will delived some characteristic equations and rules to judge the nonminimun phase problem by using linear and nonlinear theory. In design step of missile control system, the equations we delived can be used to solve the nonlinear nonminimum phase problem, therefore the missile performance can be improved. |
本系統之摘要資訊系依該期刊論文摘要之資訊為主。