基于有限元的四旋翼无人机碳纤维结构优化设计与固有模态分析

玻璃钢/复合材料 ›› 2017, Vol. 0 ›› Issue (4): 17-23.

基于有限元的四旋翼无人机碳纤维结构优化设计与固有模态分析

刘峰, 高鸿渐^*, 喻辉, 代海亮

中国民用航空飞行学院航空工程学院,广汉618307

收稿日期:2016-11-30 出版日期:2017-04-28 发布日期:2017-04-28
通讯作者: 高鸿渐(1991-),男,硕士研究生,主要研究方向为复合材料结构设计与分析。
作者简介:刘峰(1977-),男,博士,教授,主要研究方向为飞机结构与强度,复合材料结构设计与分析,数值计算与计算机仿真,飞机结构维修。
基金资助:
中国民用航空飞行学院成果转化与创新基金项目(CJ2013-02);国家级大学生创新创业训练项目(201510624033);中国民用航空飞行学院研究生创新项目(X2016-34)

THE OPTIMIZATION DESIGN OF QUADROTOR UAV CARBON FIBER STRUCTURE AND NATURAL VIBRATION ANALYSIS BASED ON FINITE ELEMENT METHOD

LIU feng, GAO Hong-jian^*, YU Hui, DAI Hai-liang

Aviation Engineering Institute, Civil Aviation Flight University of China, Guanghan 618307, China

Received:2016-11-30 Online:2017-04-28 Published:2017-04-28

摘要/Abstract

摘要： 根据消费级四旋翼无人机性能要求,设计了一款质量轻、强度高、航时长、构型简洁的全碳纤维结构消费级四旋翼无人机。建立了四旋翼无人机结构有限元模型,对额定载荷下无人机的结构应力进行了分析。基于最大应力强度准则,对无人机结构强度进行了校核。分析了结构的稳定性,计算了初始结构失稳临界载荷和失稳模态。基于最小重量要求对无人机初始结构的碳纤维铺层进行了优化设计。对优化后的结构进行了固有振动分析,给出了结构的前四阶固有频率和振动模态。优化后的结构在2 g过载下,极限载荷是最大使用载荷的2.57倍,失稳临界载荷是最大载荷的2.09倍,满足设计目标和要求。优化后的结构重量减少了21%,降低为108.6 g,有效载荷约为机体结构重量的3倍。

关键词: 四旋翼, 无人机, 有限元, 碳纤维, 结构优化

Abstract: According to the performance requirements, a full carbon fiber structural consumer-grade quadrotor UAV is designed,which has the features of light weight, high strength, long navigation time and simple configuration. The finite element model of quadrotor UAV structure is established, and the structure stress state of the UAV under the rated load is analyzed. The structure strength is checked based on the maximum stress strength criterion. The stability of the initial UAV structure is analyzed, and the critical buckling load and buckling modes are calculated. Based on the minimum weight requirement, the carbon fiber laminates optimization design of the initial structure is carried out. The natural vibration analysis of the optimized structure is conducted, and the first four natural frequencies and vibration modes are given. Under condition of 2 g load factor, the structure ultimate load is 2.57 times of the maximum service load, and the buckling critical load is 2.09 times of the maximum service load. The design goals and requirements are met. The weight of optimized structure is decreased by 21%, and reduced to 108.6 g. Payload is about three times of the structure weight.

Key words: four rotor, UAV, finite element, carbon fiber, structure optimization, vibration

中图分类号:

TB332

刘峰, 高鸿渐, 喻辉, 代海亮. 基于有限元的四旋翼无人机碳纤维结构优化设计与固有模态分析[J]. 玻璃钢/复合材料, 2017, 0(4): 17-23.

LIU feng, GAO Hong-jian, YU Hui, DAI Hai-liang. THE OPTIMIZATION DESIGN OF QUADROTOR UAV CARBON FIBER STRUCTURE AND NATURAL VIBRATION ANALYSIS BASED ON FINITE ELEMENT METHOD[J]. Fiber Reinforced Plastics/Composites, 2017, 0(4): 17-23.

参考文献

[1] 王伟, 马浩, 徐金琦. 多旋翼无人机标准化机体设计方法研究[J]. 机械设计与制造, 2014(5): 147-150.
[2] 何宇, 刘海军, 刘博. 微小型旋翼无人机总体设计与实现[J]. 战速导弹技术, 2012(4): 09-15.
[3] Ashfaq Ahmad Mian,Wang Daobo. Modeling and Backstepping-based Nonlinear Control Strategy for a 6 DOF Quadrotor Helicopter[J]. Chinese Journal of Aeronautics, 2008, 21: 261-268.
[4] 吴文志, 吴斌, 周星. 某四旋翼无人飞行器的力学仿真分析[J]. 电子机械工程, 2016, 32(1): 52-54.
[5] 刘峰, 张成雷, 马佳. 复合材料工字梁铺层结构设计及强度研究[J]. 机械科学与技术, 2016, 35(4): 1-5.
[6] 刘峰, 马佳, 张春, 等. 某无人机复合材料主翼盒准等强度设计与有限元分析[J]. 玻璃钢/复合材料, 2015(4): 16-21.
[7] 刘峰, 马佳, 张春, 等. 某型无人机复合材料机翼大梁准等强度设计与有限元分析[J]. 机械设计与制造, 2015(6): 59-62.
[8] Chen W F, Liu E M. Structural stability-theory and implementation[M]. New York: Elsevier,1987.
[9] Omprakash Seresta, ZaferGürdal, David B. Adams. Optimal design of composite wing structures with blended laminates[J].Composites PartB, 2006, 38(4): 469-480.
[10] 台元月, 邱启艳, 陈静, 等. 提高胶粘剂质量一致性检验准确率的相关研究[J]. 航空制造技术, 2014(15): 98-100.
[11] Jeon S M, Cho M H, Lee I. Static and dynamic analysis of composite box beams using large deflection theory[J]. Computers & s-tructures, 1995, 57(4): 635-642.
[12] Stemple A D, Lee S W. A finite element model for Composite beams undergoing large deflection with arbitrary cross-sectional warping[J]. International Journal for Numerical Methods in Engineering, 1989, 28(9): 2143-2160.
[13] Chang N, Yang W, Wang J, et al. Design optimization of composite wing box for flutter and stiffness[C]. 48th AIAA Aerospace Sc-iences Meeting Including the New Horizons Forum and Aerospace Exposition, 2010.
[14] JIN J, WU X. Analysis of the finite element mesh problem[J]. Computer Aided Engineering, 2005, 14(2): 75-78.
[15] Wind J W, Perdahcoɡlu D A, De Boer A. Distributed multilevel optimization for comp-lex structures[J]. Structural and Multidisc-riplinary Optimization, 2008, 36(1): 71-81.
[16] 田卫军, 李郁, 何扣芳. 四旋翼飞行器结构设计和模态分析[J]. 制造业自动化, 2014, 36(2): 37-39.