为了研究新型电磁惯性质量阻尼器(Electromagnetic Inertial Mass Damper,EIMD)应用于偏心高层结构振动控制工程的可行性,鉴于半主动控制技术的优点,基于LQR主动控制算法,提出一种可行的EIMD-偏心高层结构半主动控制策略,同时研究EIMD...为了研究新型电磁惯性质量阻尼器(Electromagnetic Inertial Mass Damper,EIMD)应用于偏心高层结构振动控制工程的可行性,鉴于半主动控制技术的优点,基于LQR主动控制算法,提出一种可行的EIMD-偏心高层结构半主动控制策略,同时研究EIMD在结构每层中安装位置不同对于控制偏心高层结构扭转反应的影响。以一个实体24层偏心高层结构作为研究对象验证地震作用下所提控制策略的有效性,仿真结果表明:(1)所提半主动控制策略基本能够达到主动控制对于结构振动反应分量的控制效果;(2)当采用半主动控制策略时,调整EIMD的安装位置对于偏心高层结构转角和转角加速度反应有着较好的控制效果。展开更多
Variable stiffness composite laminates(VSCLs)are promising in aerospace engineering due to their designable material properties through changing fiber angles and stacking sequences.Aiming to control the thermal postbu...Variable stiffness composite laminates(VSCLs)are promising in aerospace engineering due to their designable material properties through changing fiber angles and stacking sequences.Aiming to control the thermal postbuckling and nonlinear panel flutter motions of VSCLs,a full-order numerical model is developed based on the linear quadratic regulator(LQR)algorithm in control theory,the classical laminate plate theory(CLPT)considering von Kármán geometrical nonlinearity,and the first-order Piston theory.The critical buckling temperature and the critical aerodynamic pressure of VSCLs are parametrically investigated.The location and shape of piezoelectric actuators for optimal control of the dynamic responses of VSCLs are determined through comparing the norms of feedback control gain(NFCG).Numerical simulations show that the temperature field has a great effect on aeroelastic tailoring of VSCLs;the curvilinear fiber path of VSCLs can significantly affect the optimal location and shape of piezoelectric actuator for flutter suppression;the unstable panel flutter and the thermal postbuckling deflection can be suppressed effectively through optimal design of piezoelectric patches.展开更多
文摘为了研究新型电磁惯性质量阻尼器(Electromagnetic Inertial Mass Damper,EIMD)应用于偏心高层结构振动控制工程的可行性,鉴于半主动控制技术的优点,基于LQR主动控制算法,提出一种可行的EIMD-偏心高层结构半主动控制策略,同时研究EIMD在结构每层中安装位置不同对于控制偏心高层结构扭转反应的影响。以一个实体24层偏心高层结构作为研究对象验证地震作用下所提控制策略的有效性,仿真结果表明:(1)所提半主动控制策略基本能够达到主动控制对于结构振动反应分量的控制效果;(2)当采用半主动控制策略时,调整EIMD的安装位置对于偏心高层结构转角和转角加速度反应有着较好的控制效果。
基金Project(JCYJ20190808175801656)supported by the Science and Technology Innovation Commission of Shenzhen,ChinaProject(2021M691427)supported by Postdoctoral Science Foundation of ChinaProject(9680086)supported by the City University of Hong Kong,China。
文摘Variable stiffness composite laminates(VSCLs)are promising in aerospace engineering due to their designable material properties through changing fiber angles and stacking sequences.Aiming to control the thermal postbuckling and nonlinear panel flutter motions of VSCLs,a full-order numerical model is developed based on the linear quadratic regulator(LQR)algorithm in control theory,the classical laminate plate theory(CLPT)considering von Kármán geometrical nonlinearity,and the first-order Piston theory.The critical buckling temperature and the critical aerodynamic pressure of VSCLs are parametrically investigated.The location and shape of piezoelectric actuators for optimal control of the dynamic responses of VSCLs are determined through comparing the norms of feedback control gain(NFCG).Numerical simulations show that the temperature field has a great effect on aeroelastic tailoring of VSCLs;the curvilinear fiber path of VSCLs can significantly affect the optimal location and shape of piezoelectric actuator for flutter suppression;the unstable panel flutter and the thermal postbuckling deflection can be suppressed effectively through optimal design of piezoelectric patches.
