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为了研究几何大变形悬臂结构响应问题,首先,本文从理论上提出累积线性法来对这类问题进行结构建模与求解策略的探讨。理论推导与数值计算过程表明:累积线性法既合理又可行,而一次线性法的结果存在不可信等问题;从方法流程上显示,本方法在常规有限元软件平台上十分容易实现,并具有6个明显优点,这便于开展对复杂的柔性结构进行分析,使得运用累积线性法研究柔性机翼的结构响应成为可能。其次,通过比较一次总加载线性模型和不同累积次数的累积线性模型的结果,再次得出一次线性法的误差不可接受,针对此类问题,还提供了累积次数与精度的关系,即累积4次以上,便可达到工程精度要求。由此得出,累积线性法分析柔性机翼结构不仅可行,而且有效。最后,开展了某超轻型无人机全复材结构减重设计,取得了良好的效果。
In order to study the response problem of the large deformation cantilever structure, firstly, this paper presents the theory of cumulative linear method to discuss the structural modeling and solving strategies for such problems. The theoretical derivation and numerical calculation show that the cumulative linear method is reasonable and feasible, while the one-linear method has some problems, such as untrustworthiness. The method shows that this method is very easy to implement in the conventional finite element software platform and has 6 A clear advantage, which facilitates the analysis of complex flexible structures, makes it possible to study the structural response of flexible wings using cumulative linear methods. Second, by comparing the results of a linear model with a total load and a cumulative linear model with different cumulative numbers, the error of a linear method is unacceptable again. For such problems, the relationship between the number of cumulants and the accuracy is also provided, that is, the cumulative number of times Above, can achieve the engineering accuracy requirement. Therefore, it is not only feasible but also valid to analyze the flexible wing structure by the cumulative linear method. Finally, we carried out the weight reduction design of the whole complex structure of an ultralight UAV and achieved good results.