大展弦比双尾撑布局飞行器的静气动弹性分析

Research on the Effects of Static Aeroelasticity on High-Aspect-Ratio-Wing & Twin-Tail Configuration Aircraft

摘要:

大展弦比双尾撑布局飞行器通过提升低速气动效率显著改善了飞行性能，但其柔性结构在气动载荷作用下的变形对气动特性和操稳特性产生了不可忽略的影响。为提高设计可靠性，本研究针对静气动弹性对气动力特性的影响展开分析，采用三维气动网格与结构动力学模型，结合有限元仿真和网格变形技术，实现了流固耦合的静气弹仿真。研究结果表明，静气弹变形显著改变了纵横向气动力特性及各操纵面舵效，其中升力线斜率增大10%～20%，焦点位置向前移动1%～8%平均气动弦长，侧向力系数斜率减小5%～10%，偏航力矩系数斜率减小10%～23%，滚转力矩系数斜率增加10%～34%，舵面效率变化范围为10%～40%。研究为该布局的气动弹性修正与优化设计提供了理论依据。

Abstract:

The high-aspect-ratio-wing & twin-tail configuration aircraft significantly improves flight performance by enhancing low-speed aerodynamic efficiency. However, the deformation of its flexible structure under aerodynamic loads has a non-negligible impact on aerodynamic characteristics and stability/control characteristics. To enhance design reliability, this study investigates the effects of static aeroelasticity on aerodynamic characteristics. A three-dimensional aerodynamic grid and a structural dynamics model were established, and fluid-structure coupling static aeroelastic simulations were conducted using finite element simulation and mesh deformation techniques. The results indicate that static aeroelastic deformation significantly alters the longitudinal and lateral aerodynamic characteristics as well as the control surface efficiency. Specifically, the lift slope increases by 10%–20%, the aerodynamic center shifts forward by 1%–8% of the mean aerodynamic chord, the side force coefficient slope decreases by 5%–10%, the yaw moment coefficient slope decreases by 10%–23%, the roll moment coefficient slope increases by 10%–34%, and the control surface efficiency varies by 10%–40%. This study provides a theoretical basis for the aeroelastic correction and optimization design of this configuration.