无人直升机轻质机身结构方案设计研究

发布时间：2018-01-20 16:06

本文关键词： 有限元机身结构复合材料传力路径拓扑优化响应面法　出处：《南京航空航天大学》2015年硕士论文　论文类型：学位论文

【摘要】：现代无人直升机作战效能的发挥,很大程度上依赖于其平台性能,而持续的战场感知能力对机身携带的燃油量和机体重量提出了更高的要求。结构重量通常在整机重量中占比很大,可达到整机空重的三分之一,其中机身结构是降低整机空重的重要设计对象。传统直升机机身结构由于材料和设计方法上的限制,通常重量偏大,结构冗余过多,重量效率不高,无法携带更多燃油。随着复合材料工业的迅猛发展,以及相关工程应用经验的逐渐积累,随着尺寸优化、形状优化、拓扑优化等一系列优化设计方法的出现,高重量效率的轻质机身结构方案在设计过程中逐渐得以实现。本文在参考多种无人直升机机体结构设计方案的基础上,首先根据无人直升机总体布置设计要求,结合拓扑优化设计,得出主体结构最优传力路径,形成初始的机身结构方案。然后通过ANSYS软件对上述结构进行有限元建模分析,校核其强度和刚度,进行初始机身结构方案的设计完善,得到满足强度刚度要求的机身结构可行方案。最后采用基于响应面的优化方法对复合材料方案进行了参数优化设计分析,形成了完整的拓扑建模-结构分析-参数优化设计流程。通过这一系列建模分析优化,最终得出了满足重量效率指标的轻质机身结构优化设计方案。本文结合机身结构方案设计研究,详细讨论了两类优化设计方法,具体包括三个方面:(1)通过拓扑优化给出中机身核心承力设计域的最优结构形式;(2)根据Puck失效准则给出复合材料铺层中相邻层夹角过大可能导致的失效形式;(3)基于响应面优化(RSM)结果,得到机身分段结构的承力特征,并给出相应的复合材料铺层方案设计原则。本文完整的建模分析优化思路对轻质机身结构设计具有重要参考价值。
[Abstract]:The combat effectiveness of modern unmanned helicopter depends on its platform performance to a great extent. However, sustained battlefield perception requires higher fuel capacity and body weight. The structural weight usually accounts for a large proportion of the whole machine weight, which can reach 1/3 of the empty weight of the whole machine. The fuselage structure is an important design object to reduce the empty weight of the whole machine. Because of the limitation of material and design method, the traditional helicopter fuselage structure is usually too heavy, redundant and inefficient. With the rapid development of composite material industry and the gradual accumulation of engineering application experience, with the size optimization, shape optimization, topology optimization and so on, a series of optimization design methods appear. The lightweight fuselage structure scheme with high weight efficiency is gradually realized in the design process. Based on the reference of a variety of unmanned helicopter airframe structure design scheme, first of all according to the overall layout of unmanned helicopter design requirements. Combined with the topology optimization design, the optimal force transfer path of the main body structure is obtained, and the initial fuselage structure scheme is formed. Then the finite element modeling analysis of the above structure is carried out by ANSYS software, and the strength and stiffness of the structure are checked. The design of the initial fuselage structure is improved and the feasible scheme of the fuselage structure is obtained. Finally, the optimization method based on the response surface is used to optimize the design of the composite material. A complete process of topology modeling, structure analysis and parameter optimization design is formed. Finally, the optimal design scheme of lightweight fuselage structure is obtained, which meets the weight efficiency index. In this paper, two kinds of optimization design methods are discussed in detail combined with the research of fuselage structure scheme design. It includes three aspects: (1) the optimal structure form of the center fuselage core bearing design domain is given by topology optimization. (2) according to the Puck failure criterion, the failure forms which may be caused by the excessive angle of adjacent layers in composite laminates are given. 3) based on the response surface optimization (RSM) results, the bearing characteristics of the fuselage segmented structure are obtained. The corresponding design principle of composite lamination scheme is given. The whole modeling and optimization method has important reference value for the design of light fuselage structure.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V275.1

【相似文献】