飞翼布局舵面连接的气动弹性建模与计算

Aeroelastic Modeling and Calculation of Flying Wing Control Surface Linkage

以一种高机动飞翼布局为背景,建立全机的三维有限元模型,模拟飞机的真实结构,并与空气动力模型耦合插值,进行气动弹性的仿真分析。针对此翼面上有升降舵的多舵面布局,建立了俯仰运动下不同于翼面上只有副翼的动力学模型。主要研究了在舵面连接的局部建模中,因连接方式不同导致舵面支撑刚度和操纵刚度的不一致而对舵面操纵效率造成的影响。根据舵面悬挂点与摇臂操纵形式的不同,提出了四种连接方式的局部模型。通过相应的四个模型在同一飞行状态下的仿真计算与结果分析,总结出了舵面连接方式建模的变化规律,得出的结论为类似飞机的舵面连接及结构设计提供了参考。

A three- dimensional finite element model for a high- maneuverability flying wing aircraft was developed, which simulated its realistic structure closely. After connecting with the aerodynamic model, static aeroelastic analysis was processed. About multi- control surface configuration with elevators, its dynamic model was established under pitch movement, differing from wing with ailerons alone. Different linkage forms would cause the variety of control surface linkage stiffness;therefore, the main focus was to investigate the effects on control surface effectiveness among different linkage forms in finite element modeling. Based on different forms of hinge points and rocker- arms, four local models of control surface linkage forms were proposed. Through the simulative calculation and results analysis of these four models at the same flight condition, corresponding rules of control surface linkage forms modeling were summarized. The conclusions are valuable for control surface linkage and structure design on similar aircrafts.