基于累积线性法的柔性大展弦比机翼结构分析方法

Flexible and High-Aspect-Ratio Wing Structure Analysis Based on Accumulated Linearity

大展弦比柔性机翼的结构响应是典型的几何非线性问题,为研究翼尖位移为半翼展长的10%以内,本文开展了累积线性法与一次线性法的对比计算工作。理论推导结果表明,累积线性法在常规线性有限元软件平台上易于实现。数值计算表明,两种方法的结果误差在2%左右,从而得出仍然可以用一次线性法来解决机翼"10%位移"问题。而超出此范围的,应进一步开展相关工作,以判断一次线性法是否可以继续使用。

The structural response of flexible and high-aspect-ratio wing is a typical geometry nonlinearity problem. In order to study the wing tip displacement less than 10% length of the wing half span, the compared calculation between the ＇accumulated lineafity＇ （AL） and ＇one-time linearity＇ （OTL） is finished. Theoretical deduction expresses that AL is easy to program in usual FEM software. Numerical calculation shows that the error between the two methods is about 2% and it means that OTL can be applied to solve the problem of wing ＇10% displacement＇. Beyond that scope, more work should be done to judge the OTL is suitable or not.