Aerothermoelastic analysis of nonlinear composite laminated panel with aerodynamic heating in hypersonic flow
Aerothermoelastic analysis of nonlinear composite laminated panel with aerodynamic heating in hypersonic flow
复制标题
高超声速流气动加热非线性复合材料层合板气动热弹性分析
DOI：
10.1016/j.compositesb.2013.09.019
复制
发表时间：
2014-01-01
影响因子：
13.1
通讯作者：
Li, Feng-Ming
中科院分区：
文献类型：
--
作者：
Song, Zhi-Guang;Li, Feng-Ming
本文研究了考虑冲击波（SW）和气动加热的高超声速非线性层压板的气动热弹性特性。线性和三阶活塞理论用于评估空气动力压力。采用汉密尔顿原理建立了层压板的气动弹性模型。在气动热模型中，采用参考温度法计算气动加热中的热通量，并应用有限元法（FEM）求解面板中的瞬态传热。分别求解气动弹性模型和气动热模型后，将解相互代入。然后进行迭代过程，实现结构、流体和热力之间的耦合效应。获得层压板的时域响应。还研究了冲击波对面板气动特性的影响。从数值模拟可以看出，随着温度变化的增加，气动弹性稳定性减弱。还需要指出的是，在计算高超声速流气动热弹性分析的气流参数时，应考虑激波的影响。 (C) 2013 Elsevier Ltd. 保留所有权利。
Aero-thermal-elastic characteristics of hypersonic nonlinear laminated panels considering the shock wave (SW) as well as the aerodynamic heating are studied in this paper. The linear and third order piston theories are used to evaluate the aerodynamic pressure. Hamilton's principle is employed to establish the aeroelastic model of the laminated panel. In the aerothermal model, the heat flux in the aerodynamic heating is computed using the reference temperature method, and the finite element method (FEM) is applied to solve the transient heat transfer in the panel. After solving the aeroelastic and aerothermal models separately, the solutions are substituted into each other. Then performing the procedure of iteration, the coupling effects among the structure, fluid and thermal are realized. Time domain responses of the laminated panel are obtained. The influences of the shock wave on the aeroleastic characteristics of the panel are also investigated. From the numerical simulation, it can be observed that the aeroelastic stability is weakened with the increase of the temperature change. It is also noted that in the calculation of the airflow parameters for the aerothermoelastic analysis in the hypersonic flow, the influences of the shock wave should be taken into account. (C) 2013 Elsevier Ltd. All rights reserved.