基于显式动力学的软式飞艇流固耦合计算框架  

Fluid-Structure Interaction Calculation Framework for Non-Rigid Airship Based on Explicit Dynamics

作　　者：张宇 王晓亮[1] ZHANG Yu;WANG Xiaoliang(School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China)

机构地区：[1]上海交通大学航空航天学院,上海200240

出　　处：《上海交通大学学报》2021年第3期311-319,共9页Journal of Shanghai Jiaotong University

基　　金：国家自然科学基金(61733017),上海市自然科学基金(18ZR1419000)资助项目。

摘　　要：软式飞艇作为一种低刚度、具有充气结构的飞行器,其流固耦合特性明显.结合参数化截面(PARSEC)方法、径向基函数(RBF)和Delaunay映射方法,构建对软式飞艇的非定常显式动力学流固耦合分析框架.借助平板冲击和NACA0014机翼气动弹性案例验证该数值方法的可靠性和精度.该计算框架也同样适用于高空气球等薄膜类浮空器的非定常双向流固耦合分析.最后,应用上述框架对某软式飞艇在不同压差下的结构响应进行分析.研究结果表明,飞艇振动主频与飞艇的内外压差之间呈现近似线性关系.The non-rigid airship is a low-rigidity and inflatable aircraft which has obvious fluid-structure interaction characteristics.In this paper,the unsteady explicit dynamic fluid-structure interaction analysis framework of non-rigid airship is constructed based on the parametric section(PARSEC)method,the radial basis function(RBF),and the Delaunay mapping method.The reliability and accuracy of the numerical method are verified by the cases of plate impact and the aeroelasticity of NACA0014 wing.The calculation framework is also suitable for unsteady bidirectional fluid-structure interaction analysis of thin-envelope aerostats such as high-altitude balloon.Finally,the time domain and frequency domain responses of one non-rigid airship are simulated by the above framework.The research results show that there is an approximately linear relationship between the dominant frequency of vibration and the pressure difference of the airship.

关 键 词：软式飞艇 流固耦合 径向基函数 Delaunay映射 参数化截面 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]