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An active damping vibration control system for wind tunnel models
Alternative TitleAn active damping vibration control system for wind tunnel models
Liu Wei1; Zhou Mengde1; Wen Zhengquan1; Yao Zhuang1; Liu Yu2; Wang Shihong2; Cui Xiaochun2; Li Xiao1; Liang Bing1; Jia Zhenyuan1
2019
Source PublicationChinese Journal of Aeronautics
ISSN1000-9361
Volume32Issue:9Pages:2109-2120
AbstractIn wind tunnels, long cantilever sting support systems with low structural damping encounter flow separation and turbulence during wind tunnel tests, which results in destructive low-frequency and big-amplitude resonance, leading to data quality degradation and test envelope limitation. To ensure planed test envelope and obtain high-quality data, an active damping vibration control system independent of balance signal based on stackable piezoelectric actuators and velocity feedback using accelerometer, is proposed to improve the support stability and wind tunnel testing safety in transonic wind tunnel. Meanwhile, a design of powerful sting-root embedded active damping device is given and an active vibration control method is presented based on the mechanism analysis of aircraft model vibration. Furthermore, a self-adaptive fuzzy Proportion Differentiation (PD) control model is proposed to realize control parameters adjustment automatically for various testing conditions. Besides, verification tests are performed in laboratory and a continuous transonic wind tunnel. Experimental results indicate that the aircraft model does not vibrate obviously from ?4° to 11° at Ma?=?0.6, the number of useable angle-of-attack has increased by 7° at Ma?=?0.6 and 5° at Ma?=?0.7 respectively, satisfying the requirements of practical wind tunnel tests. Keywords: Accelerometer, Active damping, Sting vibration, Transonic wind tunnel, Vibration active control
Other AbstractIn wind tunnels, long cantilever sting support systems with low structural damping encounter flow separation and turbulence during wind tunnel tests, which results in destructive low-frequency and big-amplitude resonance, leading to data quality degradation and test envelope limitation. To ensure planed test envelope and obtain high-quality data, an active damping vibration control system independent of balance signal based on stackable piezoelectric actuators and velocity feedback using accelerometer, is proposed to improve the support stability and wind tunnel testing safety in transonic wind tunnel. Meanwhile, a design of powerful sting-root embedded active damping device is given and an active vibration control method is presented based on the mechanism analysis of aircraft model vibration. Furthermore, a self-adaptive fuzzy Proportion Differentiation(PD) control model is proposed to realize control parameters adjustment automatically for various testing conditions. Besides, verification tests are performed in laboratory and a continuous transonic wind tunnel. Experimental results indicate that the aircraft model does not vibrate obviously from -4° to 11° at Ma = 0.6, the number of useable angle-of-attack has increased by 7° at Ma = 0.6 and 5° at Ma = 0.7 respectively, satisfying the requirements of practical wind tunnel tests.
KeywordMotor vehicles. Aeronautics. Astronautics TL1-4050
Indexed ByCSCD
Language英语
Funding Project[National Natural Science Foundation of China] ; [high-level personnel innovation support program of Dalian]
CSCD IDCSCD:6591813
Citation statistics
Document Type期刊论文
Identifierhttp://ir.imr.ac.cn/handle/321006/154615
Collection中国科学院金属研究所
Affiliation1.大连大学
2.中国科学院金属研究所
Recommended Citation
GB/T 7714
Liu Wei,Zhou Mengde,Wen Zhengquan,et al. An active damping vibration control system for wind tunnel models[J]. Chinese Journal of Aeronautics,2019,32(9):2109-2120.
APA Liu Wei.,Zhou Mengde.,Wen Zhengquan.,Yao Zhuang.,Liu Yu.,...&Jia Zhenyuan.(2019).An active damping vibration control system for wind tunnel models.Chinese Journal of Aeronautics,32(9),2109-2120.
MLA Liu Wei,et al."An active damping vibration control system for wind tunnel models".Chinese Journal of Aeronautics 32.9(2019):2109-2120.
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