摘要
针对复合材料场景下机翼结构设计理论的缺失,文中通过引入有限元模型进行机翼的仿真与分析,提出了一套全流程的综合设计方法。该方法基于材料强度、刚度与机翼稳定性的要求,通过传力分析、静强度优化、稳定性优化3个流程得到机翼的打样结构。使用有限元方法对打样结构进行计算机数学建模,结合材料的结构效率指标要求进行迭代优化,从而得到机翼结构的最终方案。文中使用某型号无人机机翼的相关参数进行了方法验证,获得结构效率为92.9%的设计方案,在尽量满足机翼强度与刚度的情况下,减小了材料的浪费。方案中的临界失稳应变接近实际环境,证明了机翼结构布局合理,且有较强的承载能力。
In view of the lack of wing structure design theory in the composite scene,the finite element model to simulate and analyze the wing is introduced,and a comprehensive design method of the whole process is put.Based on the requirements of material strength,stiffness and wing stability,the method obtains the sample structure of wing through three processes of force transfer analysis,static strength optimization and stability optimization.The finite element method to model the proofing structure by computer is used,and combine with the structural efficiency index requirements of materials to carry out iterative optimization to get the final scheme of the wing structure.The relevant parameters of a certain type of UAV wing are used to verify the method,and obtains the design scheme with the structural efficiency of 92.9%,which reduces the waste of materials under the condition of satisfying the strength and rigidity of the wing as much as possible.In addition,the critical instability strain in the scheme is close to the actual environment,which proves that the wing structure layout is reasonable and has strong bearing capacity.
作者
王飞
孙培杰
WANG Fei;SUN Peijie(Xi’an Aeronautical University,Xi’an 710077,China)
出处
《电子设计工程》
2021年第9期41-45,共5页
Electronic Design Engineering
基金
西安航空学院校级科研基金(2019KY1228)。
关键词
复合材料
机翼结构设计
有限元
数学建模
composite material
wing structure design
finite element
mathematical modeling
