کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1718874 | 1520105 | 2007 | 10 صفحه PDF | دانلود رایگان |
![عکس صفحه اول مقاله: Decoupling the flight control system of a supersonic vehicle Decoupling the flight control system of a supersonic vehicle](/preview/png/1718874.png)
In this paper, a nonlinear decoupling technique is proposed for analyzes and designs of a serious aerodynamic coupled missile flight control system. Decoupling is obtained from multiplications of two measurable accelerations with three controllable output commands of the autopilot. They give exact signs and magnitudes proportional to aerodynamic decoupling. No matrix inversion of the system dynamic for decoupling is needed. From frequency responses of the rolling channel, it will be seen that the decoupling and robustness for copping with aerodynamic couplings can be obtained simultaneously. Furthermore, the decoupling characteristics are kept almost unchanged for large system parameter variations and uncertainties. The 5-DOF simulations give same conclusions.
Journal: Aerospace Science and Technology - Volume 11, Issues 7–8, November–December 2007, Pages 553-562