论文首先对无人机的发展历史及其的现状进行了综合描述，然后再对一些主要的

The thesis first comprehensively describes the development history and current status of drones, and then analyzes and studies some of the main structural optimization design methods. On this basis, the software is selected for multi-objective optimization design analysis of the UAV wing structure. During the optimization design, it is necessary to determine that it meets the requirements of strength and stiffness. Then through a detailed analysis of the structure of this type of UAV, a finite element model of the wing structure is established, and then the node load acting on the wing model of the UAV is calculated through the corresponding manual and specifications of the aircraft design And determine the most severe load case for subsequent structural analysis and optimization design work: the paper further selected the tension line and the cross-sectional area of ​​the front and rear beam flanges as the design variables under the most severe load case selected. The aircraft was multi-objective optimized design of the wing structure, and the most satisfactory design scheme and its structural size were obtained: Finally, the paper did not calculate the final optimization scheme and the original optimization scheme under some typical load conditions in the UAV flight envelope Some design schemes were compared and discussed by imitation analysis.

论文首先对无人机的发展历史及其的现状进行了综合描述，然后再对一些主要的结构优化设计方法进行分析、研究。在此基础上，选择软件进行无人机机翼结构的多目标优化设计分析，优化设计的过程中，要确定其满足强度和刚度的要求。再通过对该型无人机机属结构进行详细分析，建立了机翼结构的有限元模型，然后通过飞机设计的相应手册及规范计算了作用在该无人机机翼模型上的结点载荷，并确定了最严重载荷工况用于进行后续的结构分析与优化设计工作：论文进一步在选定的最严重载荷工况下以张线和前后梁缘条横截面积为设计变量对无人机进行了机翼结构多目标优化设计，得出了最满意设计方案及其结构尺寸：最后，论文在无人机飞行包线内的一些典型载荷工况下对最终的优化没计方案和原有设计方案进行了仿分析比较与讨论。

Firstly, the paper describes the development history and current situation of UAV, and then analyzes and studies some main structural optimization design methods. On this basis, software is selected to carry out multi-objective optimization design analysis of UAV wing structure. In the process of optimization design, it is necessary to ensure that it meets the requirements of strength and stiffness. Through the detailed analysis of the structure of the UAV, the finite element model of the wing structure is established, and then the node load acting on the UAV wing model is calculated through the corresponding manual and specification of the aircraft design, and the most severe load condition is determined for the subsequent structural analysis and optimization design work: the paper further studies the most severe load condition selected In this case, the multi-objective optimization design of the UAV wing structure is carried out by taking the cross-sectional area of the tension line and the front and rear beam edge as the design variables, and the most satisfactory design scheme and its structure size are obtained. Finally, the final optimization scheme and the original design scheme are compared and discussed under some typical load conditions in the UAV flight envelope.