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第 8 期          岳慧裕,等: 直升机主减速器周期撑杆混合振动控制的机电耦合特性及工作机理研究                                     1731

                   Phase  Ⅱ :  Full  scale  testing:  NASA  Report  172594  [15] ZHANG Y K, LU T F, AL-SARAWI S. Formulation
                  [R]. 1986.                                         of  a  simple  distributed-parameter  model  of  multilayer
             [7] SZEFI  J,  SMITH  E,  LESIEUTRE  G.  Formulation    piezoelectric actuators[J]. Journal of Intelligent Materi‑
                   and  validation  of  a  Ritz-based  analytical  model  for  de‑  al Systems and Structures, 2016, 27(11): 1485-1491.
                   sign  of  periodically-layered  isolators  in  compression  [16] ZHANG Y K, LU T F, PENG Y X. Three-port equiv‑
                  [C]// Proceedings of 19th AIAA Applied Aerodynam‑  alent  circuit  of  multi-layer  piezoelectric  stack[J].  Sen‑
                   ics Conference. Reston, Virginia: AIAA, 2001: 1684.  sors and Actuators A: Physical, 2015, 236: 92-97.
             [8] ASIRI S, BAZ A, PINES D. Periodic struts for gear‑  [17] MENG D, XIA P Q, LANG K, et al. Neural network
                   box  support  system[J].  Journal  of  Vibration  and  Con‑  based hysteresis compensation of piezoelectric stack ac‑
                   trol, 2005, 11(6): 709-721.                       tuator  driven  active  control  of  helicopter  vibration[J].
             [9] BAZ  A.  Active  control  of  periodic  structures[J].  Jour‑  Sensors  and  Actuators  A:  Physical,  2020,  302:
                   nal  of  Vibration  and  Acoustics,  2001,  123(4):   111809.
                   472-479.                                     [18] LANG  K,  XIA  P  Q,  WANG  X.  Active  global  vibra‑
             [10] LU Y, WANG F J, MA X J. Helicopter interior noise   tion  control  of  helicopter  fuselage[J].  AIAA  Journal,
                   reduction using compounded periodic struts[J]. Journal   2023, 61(8): 3692-3706.
                   of Sound and Vibration, 2018, 435: 264-280.  [19] LANG K, XIA P Q. Hybrid active vibration control of
             [11] KIM  B,  WASHINGTON  G  N,  SINGH  R.  Design      helicopter  fuselage  driven  by  piezoelectric  stack  actua‑
                   and analysis of supporting structure with smart struts for   tors[J]. Journal of Aircraft, 2018, 56(2): 719-729.
                   active vibration isolation[C]// Proceeding of Industrial   [20] SONG  L  S,  XIA  P  Q.  Active  control  of  helicopter
                   and Commercial Applications of Smart Structures Tech‑  structural  response  using  piezoelectric  stack  actuators
                   nologies  2010.  San  Diego,  California,  USA:  SPIE,   [J]. Journal of Aircraft, 2013, 50(2): 659-663.
                   2010: 76450R.                                [21] SONG L S, XIA P Q. A harmonic synchronous identifi‑
             [12] MA X J, LU Y, WANG F J. Active structural acoustic   cation-updating  method  for  active  control  of  helicopter
                   control of helicopter interior multifrequency noise using   structural  response  driven  by  piezoelectric  stack  actua‑
                   input-output-based  hybrid  control[J].  Journal  of  Sound   tors[J].  Journal  of  the  American  Helicopter  Society,
                   and Vibration, 2017, 405: 187-207.                2015, 60(3): 1-14.
             [13] 张荣山 . 工程振动与控制[M]. 北京: 中国建筑工业出
                                                                第一作者: 岳慧裕(1995—),男,博士研究生。
                   版社, 2003.
                                                                         E-mail:brendonyueh@163.com
             [14] NAKAMOTO  T,  MORIIZUMI  T.  A  theory  of  a
                                                                通信作者: 陆     洋(1977—),男,博士,教授。
                   quartz crystal microbalance based upon a mason equiva‑
                                                                         E-mail:njluyang@163.com
                   lent  circuit[J].  Japanese  Journal  of  Applied  Physics,
                   1990, 29(5): 963.
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