Development and verification of shape memory alloy self-resetting vibration damping device

被引：0
|
作者：
Ma Y. [1 ,2 ,3 ]
Li D. [1 ,2 ]
Nie X. [3 ]
Zhang W. [1 ,3 ]
Gao X. [3 ]
Chen W. [3 ]
Chen Z. [3 ]
机构：
[1] College of Aerospace Science and Engineering, National University Defense Technology, Changsha
[2] Hunan Key Laboratory of Intelligent Planning and Simulation for Aerospace Missions, Changsha
[3] Facility Design and Instrumentation Institute, China Aerodynamics Research and Development Center, Mianyang
来源：
Guofang Keji Daxue Xuebao/Journal of National University of Defense Technology | 2024年 / 46卷 / 03期
关键词：
central flap mechanism; numerical analysis; self-resetting vibration damping device; shape memory alloy; vibration reduction test; wind tunnel;
D O I：
10.11887/j.cn.202403011
中图分类号：
学科分类号：
摘要：
In order to improve the flow induced vibration of the adjustable central flap mechanism deployed in the second throat in the working state, a SMA (shape memory alloy) self-resetting vibration damping device which could meet the limited installation space of the central flap mechanism was designed and manufactured according to the biasing two-way driving principle of SMA. The SMA constitutive relation subroutine compiled by UMAT interface was used to realize the numerical analysis of the maximum pressing force of the damping device, and the error between the numerical analysis and the static test results is about 2.58%. A ground vibration reduction test platform was built to test the vibration reduction effect of SMA self-resetting vibration damping device in the separated and closed states. The vibration reduction test results show that the vibration response of the central flap mechanism is significantly reduced with SMA self-resetting damping device activated. An obvious damping effect appear in the frequency band of 0 ~ 100 Hz, especially, the damping rate in the range of low frequency to 55 Hz is greater than 50%. © 2024 National University of Defense Technology. All rights reserved.
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页码：105 / 115
页数：10
相关论文
共 35 条
  • [1] LU B, LYU B B, LUO J G, Et al., Wind tunnel technique for transonic full-model flutter test, Acta Aeronautica et Astronautica Sinica, 36, 4, pp. 1086-1092, (2015)
  • [2] HE L, QIAN W Q, YI X, Et al., Graphical prediction method of airfoil ice shape based on transposed convolution neural networks, Journal of National University of Defense Technology, 43, 3, pp. 98-106, (2021)
  • [3] WANG N T, XU X B, MA X Y, Et al., Degradation and failure detection technology on strain balance measuring circuit, Journal of National University of Defense Technology, 42, 1, pp. 150-155, (2020)
  • [4] CHEN J M, WU S H, LIAO D X, Et al., Experimental study for improving flow-field quality for 0.6 m continuous transonic wind tunnel, Journal of Nanjing University of Aeronautics & Astronautics, 53, 2, pp. 236-242, (2021)
  • [5] CHEN J B, GAO X Y, CAI Q Q., Analysis and design of adjustable flaps mechanism of second throat in wind tunnel, Mechanical Engineering & Automation, 5, pp. 87-89, (2012)
  • [6] LAYUKALLO T, NAKAMURA Y., Flow stabilization in a transonic wind tunnel with a second throat, Journal of Aircraft, 37, 6, pp. 1033-1037, (2000)
  • [7] CHEN D, ZHANG Y S, LI G, Et al., Mach number control strategy for continuous wind tunnel with second throat, Journal of Aerospace Power, 34, 10, pp. 2167-2176, (2019)
  • [8] CUI X C, MENG F M, LI Q L, Et al., Preliminary research on center body of adjusting plate second throat in transonic wind tunnel, Acta Aeronautica et Astronautica Sinica, 38, 11, (2017)
  • [9] MENG F M, ZHANG R, LI Q L, Et al., Research on asymmetric field flow in the subsonic second throat, Journal of Experiments in Fluid Mechanics, 29, 2, pp. 43-47, (2015)
  • [10] BARTLEY-CHO J D, WANG D P, MARTIN C A, Et al., Development of high-rate, adaptive trailing edge control surface for the smart wing phase 2 wind tunnel model, Journal of Intelligent Material Systems and Structures, 15, 4, pp. 279-291, (2004)
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