某型超低空无人驾驶靶机颤振模型平尾的修改设计

The Dynamic Redesign of the Horizontal Tail of a Flutter Model Unmanned Aircraft

本文针对某型无人机颤振模型平尾作大修改的情况,提出了一种有效的两步设计过程,以解决在满足预定频率和振型及总重量为给定的条件下带约束的动力学再设计问题。在第一步设计过程中,通过将参考振型作为节点质量配置的位置加权函数,有效地将大修改问题转化为小修改问题。进而在第二步设计过程中,对结构进行满足某些性能约束条件及工艺性的小修改再设计工作。通过对实际颤振模型平尾的动力学再设计,证明了此两步设计过程具有高效、快速的特点。

In this paper, an efficient two-step design procedure for solving large dynamic modification redesign problem of complex structures with a given total weight, predetermined frequencies and mode shapes constraints is presented. In the first step, the large modification problem is transferred to a small one by using a mass distribution weighing function, which copes with the inaccurately given mode shapes. In the second step, therefore, the new small modification redesign can be easily and quickly carried out by a common-used optimization procedure. The new redesign procedure presented in this paper is proved to be highly effective and rapid in practically redesigning the horizontal tail of a flutter model unmanned aircraft. The desin results are satisfactory.