An Adaptive Dynamic Surface Controller for Ultralow Altitude Airdrop Flight Path Angle with Actuator Input Nonlinearity
| Autor: | Maolong Lv, Shu-guang Liu, Xiu-xia Sun, Dong Wang |
|---|---|
| Jazyk: | angličtina |
| Rok vydání: | 2016 |
| Předmět: |
0209 industrial biotechnology
Engineering Article Subject business.industry General Mathematics lcsh:Mathematics General Engineering Control engineering 02 engineering and technology Residual lcsh:QA1-939 Tracking error Nonlinear system 020901 industrial engineering & automation Robustness (computer science) Control theory lcsh:TA1-2040 0202 electrical engineering electronic engineering information engineering Trajectory 020201 artificial intelligence & image processing Actuator business lcsh:Engineering (General). Civil engineering (General) Backlash |
| Zdroj: | Mathematical Problems in Engineering, Vol 2016 (2016) |
| ISSN: | 1024-123X |
| DOI: | 10.1155/2016/4753241 |
| Popis: | In the process of ultralow altitude airdrop, many factors such as actuator input dead-zone, backlash, uncertain external atmospheric disturbance, and model unknown nonlinearity affect the precision of trajectory tracking. In response, a robust adaptive neural network dynamic surface controller is developed. As a result, the aircraft longitudinal dynamics with actuator input nonlinearity is derived; the unknown nonlinear model functions are approximated by means of the RBF neural network. Also, an adaption strategy is used to achieve robustness against model uncertainties. Finally, it has been proved that all the signals in the closed-loop system are bounded and the tracking error converges to a small residual set asymptotically. Simulation results demonstrate the perfect tracking performance and strong robustness of the proposed method, which is not only applicable to the actuator with input dead-zone but also suitable for the backlash nonlinearity. At the same time, it can effectively overcome the effects of dead-zone and the atmospheric disturbance on the system and ensure the fast track of the desired flight path angle instruction, which overthrows the assumption that system functions must be known. |
| Databáze: | OpenAIRE |
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