模块化可重构无人机机翼结构优化方法研究  

Study on optimization method of the modular reconfigurable UAV's wing structure

作　　者：罗利龙[1] 郭文杰 常亮[1] LUO Lilong;GUO Wenjie;CHANG Liang(National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi’an 710065,China)

机构地区：[1]中国飞机强度研究所强度与结构完整性全国重点实验室,西安710065

出　　处：《航空工程进展》2023年第3期164-170,共7页Advances in Aeronautical Science and Engineering

基　　金：工信部民机专项(MJZ3-2N21)。

摘　　要：模块化可重构无人机设计工况复杂、约束多样,需要根据不同设计思想的特点研究适用的优化方法才能得到最优方案。针对多模型的同步优化方法开展研究,给出不同构型机翼翼根弯矩约束方法,提出多构型机翼结构前后梁弯矩比例约束下的同步优化方法,并以某模块化可重构无人机机翼为对象进行应用验证。结果表明:与文献中模块化机翼优化结果相比,本文多构型机翼结构同步优化方法在解决整机翼更换的模块化可重构机翼结构优化问题时具有较高的适用性和收敛性以及广阔的工程推广价值。The design of the modular reconfigurable unmanned aircraft vehicle(UAV)has complex conditions and multiple constraints,and it is necessary to obtain the optimal scheme by means of the research on suitable optimiza-tion method according to different design thought.The study on multi-model simultaneous optimization method is carried out in this paper.The bending moment constraint method of different configurations of wing is given.The si-multaneous optimization method of multi-configuration wing under the condition of bending moment constraints for front and back beam is proposed,and the wing of a certain modular reconfigurable UAV's wing is taken as the ob-ject for application verification.The results show that,compared with the optimization results of modular wings in references,the proposed simultaneous optimization method of multi-configuration wing structure method has higher applicability and convergence,and wide engineering promotion value to solve the changing modular reconfig-urable wing structure optimization problem of the whole wing.

关 键 词：模块化 可重构 无人机 弯矩约束 优化设计 

分 类 号：V279[航空宇航科学与技术—飞行器设计] V214.19[理学—物理] TB553[理学—声学]