The Design and Analysis for Autopilot Control and Stability mentation of UAV
碩士 === 中華技術學院 === 飛機系統工程研究所 === 97 === Flight control systems are required for aircrafts which are unstable and unable to meet aviation quality specification. The flight control system for a general aircraft consists of three control loops: pitch, roll, and yaw. The output for the transfer function...
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| Format: | Others |
| Language: | zh-TW |
| Published: |
2009
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| Online Access: | http://ndltd.ncl.edu.tw/handle/07840379476607438541 |
| Summary: | 碩士 === 中華技術學院 === 飛機系統工程研究所 === 97 === Flight control systems are required for aircrafts which are unstable and unable to meet aviation quality specification. The flight control system for a general aircraft consists of three control loops: pitch, roll, and yaw. The output for the transfer function of each loop is close to a first order or second order dynamic response. After the elevator is deflected for a certain angle (input), the angle of attack will not reach the corresponding degree (output) immediately; rather, it will take some amount of oscillations to converge. The Automatic Stability Augmentation System can help aircraft reach the profile or path specified by the pilot rapidly and smoothly. The purpose of this study is to apply the classic and modern control theories which are taught in the textbooks to the design of autopilot and Stability Augmentation System of an unmanned aircraft: speed feedback is used in the internal loop to increase the system damping during the design process for longitudinal movement and washout filter technology is added during the design process of the lateral movement so that the order issued by the pilot will be reflected truthfully by the control system; and Matlab/Simulink software package is used as a tool for simulation and verification analysis.
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