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。
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 configura- tion. 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 calcu- lated. Based on the minimum weight requirement, the carbon fiber laminates optimization design of the initial struc- ture 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.
出处
《玻璃钢／复合材料》
CSCD
北大核心
2017年第4期17-23,共7页
Fiber Reinforced Plastics/Composites
基金
中国民用航空飞行学院成果转化与创新基金项目(CJ2013-02)
中国民用航空飞行学院研究生创新项目(X2016-34)
国家级大学生创新创业训练项目(201510624033)
关键词
四旋翼
无人机
有限元
碳纤维
结构优化
four rotor
UAV
finite element
carbon fiber
structure optimization
vibration
