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

Abstract

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

CLC Number:

TB332

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.

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