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| Active Vibration Control of Full Composite Wing |
| Received:June 25, 2018 Revised:September 25, 2018 |
| View Full Text View/Add Comment Download reader |
| DOI：10.7643/ issn.1672-9242.2018.09.006 |
| KeyWord:full composite wing vibration active control PID control variable parameter analysis ground test |
| Author | Institution |
| LEI Ming |
Aircraft Flight Test Technology Institute, Chinese Flight Test Establishment, Xian , China |
| LI Yang |
Aircraft Flight Test Technology Institute, Chinese Flight Test Establishment, Xian , China |
| KOU Bao-zhi |
Aircraft Flight Test Technology Institute, Chinese Flight Test Establishment, Xian , China |
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| Abstract: |
| Objective To reduce vibration response of composite structure. Methods With the composite wing as the object of study, a structure dynamic simulation model with piezoelectric actuator was established in combination with the finite element model of the wing structure. Active control law was designed with the PID (Proportional, Integral and Differential) control theory. The control law program was developed based on the Simulink simulation software. The design rules of each parameter for PID control were obtained by analysis of variable parameters for control laws. The simulation experiment of vibration active control was conducted based on simulation model. Based on the result of the simulation experiment, ground test of vibration active control was conducted for full composite wing. Results The control laws were demonstrated to be effective in controlling vibration. The vibration response was reduced by 79.74%. The model and control laws were effective. Conclusion With the piezoelectric actuator as the control actuator, the control laws designed based on the PID control theory could effectively control vibration of composite wing and reduce the vibration. |
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