为了准确分析翼面热环境,提出了一种并行迭代耦合方法。气动加热和结构传热分别采用有限体积法(finite volume method,简称FVM)和有限元法(finite element method,简称FEM)求解,且采用基于虚拟空间的插值方法进行数据传递。进行了圆管...为了准确分析翼面热环境,提出了一种并行迭代耦合方法。气动加热和结构传热分别采用有限体积法(finite volume method,简称FVM)和有限元法(finite element method,简称FEM)求解,且采用基于虚拟空间的插值方法进行数据传递。进行了圆管算例分析,2s时刻驻点温度计算值与试验值相对误差为5.16%,验证了并行迭代耦合方法的精度。进行了翼面热环境和热模态的分析,结果表明翼面最高温度与马赫数呈近似线性关系,且非耦合方法获得的翼面最高温度比耦合方法高342.2K,这是由于非耦合方法未考虑气动热与结构传热之间的耦合效应。相比热应力引起的结构附加几何刚度,热环境下材料刚度的降低是翼面刚度和固有频率下降的主要因素,并且随着马赫数的增加,低阶比高阶固有频率下降得更快。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
文摘为了准确分析翼面热环境,提出了一种并行迭代耦合方法。气动加热和结构传热分别采用有限体积法(finite volume method,简称FVM)和有限元法(finite element method,简称FEM)求解,且采用基于虚拟空间的插值方法进行数据传递。进行了圆管算例分析,2s时刻驻点温度计算值与试验值相对误差为5.16%,验证了并行迭代耦合方法的精度。进行了翼面热环境和热模态的分析,结果表明翼面最高温度与马赫数呈近似线性关系,且非耦合方法获得的翼面最高温度比耦合方法高342.2K,这是由于非耦合方法未考虑气动热与结构传热之间的耦合效应。相比热应力引起的结构附加几何刚度,热环境下材料刚度的降低是翼面刚度和固有频率下降的主要因素,并且随着马赫数的增加,低阶比高阶固有频率下降得更快。
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.
