模块化可重构无人机机翼结构优化方法研究

Study on the optimization of the modular reconfigurable UAV"s wing structure

摘要:

针对模块化可重构无人机设计工况复杂、约束多样、周期冗长的问题,以采用整机翼更换方式的模块化可重构无人机为对象,考虑不同构型机翼共用一套机身的特点,研究了不同构型机翼翼根弯矩约束的施加方法,提出了可考虑前后梁弯矩比例约束的多构型同步优化技术,并采用该技术完成了某模块化可重构无人机机翼结构的优化设计。通过与传统单方案等两种优化方法进行对比,验证了本文可考虑前后梁弯矩比例约束的多构型同步优化技术的正确性和收敛性,以及良好的工程推广价值。

Abstract:

To deal with the complex load conditions, diverse constraints and time-consuming problems faced during the design of the modular reconfigurable unmanned aircraft vehicle (UAV), taking the modular reconfigurable UAV in which different wings can be changed by using a common fuselage to meet different flying missions as the research object, different wings’ bending moment constraints application methods are studied in depth. A simultaneous multi-configuration optimization technique considering the wing’s front and back bars’ bending moment constraints is proposed. A typical modular reconfigurable UAV’s wing structure is designed and optimized by using the proposed method. Compared with the design results obtained by using the typical two traditional optimization formulations, the proposed technique is proven validate and convergent. And this method has some value in the practical engineering fields.