摘要
综合考虑复合材料机翼的材料耦合和几何耦合的特点,利用Hamilton原理建立了非定常气动力作用下复合材料机翼/外挂系统的气动弹性运动方程。采用微分求积法进行离散,运用MATLAB语言编程对系统响应进行数值仿真。计算结果表明:用微分求积法计算复合材料机翼的颤振特性是可行的;随材料耦合刚度的增加,机翼的颤振临界速度出现了双峰值;而对于复合材料机翼/外挂系统,颤振临界速度随材料耦合刚度的变化规律较为复杂,与外挂参数的设置相关。
The aeroelastic equations of composite wing with store system under unsteady aerodynamic forces are established by applying the Hamilton’s principle.The material coupling and geometrical coupling are considered.The system dynamics is numerically simulated by use of differential quadrature method(DQM).Results show that it is feasible to use DQM for solving the flutter characteristics of composite wing.On the other hand,it is shown that the critical flutter speed presents two peak values with the increase of material coupling rigidity.However,for the composite wing with store system,the critical flutter speed presents complex variation which relates to the setting of store parameters.
出处
《应用力学学报》
CSCD
北大核心
2017年第3期502-506,共5页
Chinese Journal of Applied Mechanics
基金
中国民航飞行学院面上项目(J2013-03)
