Design and Strength Analysis of Light UAV Landing Gear

被引：0

作者：

Wang P. ^{[1
]}

Wu H. ^{[1
]}

Liang Y. ^{[1
]}

Hu X. ^{[1
]}

Ji X. ^{[1
]}

Wang Z. ^{[1
]}

机构：

[1] Liao Shen Industries Group Co., Ltd., Shenyang

来源：

Binggong Xuebao/Acta Armamentarii | 2022年 / 43卷

关键词：

Landing gear; Light unmanned aerial vehicles; Sructural design; Strength analysis;

D O I：

10.12382/bgxb.2022.A023

中图分类号：

学科分类号：

摘要：

A landing gear for a specific light UAV is designed and analyzed to make up for the lack of research on the landing gear or flight-assisting system of light UAVs. According to the actual application requirements, a design scheme of the landing gear structure and electrical system of a light UAV was proposed. Based on the weight of UAV, Ansys simulation software is used to establish a finite element calculation model, and the strength of landing gear structure was analyzed and simulated. The results of structural strength analysis show that the maximum deformation of landing gear is 0.6 mm, which meets the design requirements.The light UAV landing gear designed in this paper has the advantages of simple structure, light weight and high reliability, which provides a solution for related research and engineering applications. © 2022, Editorial Board of Acta Armamentarii. All right reserved.

引用

页码：140 / 145

页数：5

共 15 条

[1]

JIA Y H, GUO K Q., The development of airplane landing gear, Proceedings of the 1st China-Japan International Conference on History of Mechanical Technology, pp. 425-429, (1998)

[2]

CHEN L C., Research on ground modeling of tricyle landing gear UAV, (2016)

[3]

DAI B., Modification design of a UAV landing gear, (2016)

[4]

WU W G, SUN J Q, LENG Y G, Et al., Dynamic modeling of landing gear and its random response analysis, Acta Aeronautica et Astronautica Sinica, 37, 4, pp. 1228-1239, (2016)

[5]

JIA Y H, WANG J J., Active and semi-active control for airplane landing gear, Acta Armamentarii, 27, 3, pp. 528-532, (2006)

[6]

WANG X L, NIE H, XUE C J., A review of fatigue life design for a landing gear, Mechanical Science and Technology for Aerospace Engineering, 28, 7, pp. 921-925, (2009)

[7]

XU H., Static and dynamic mechanical performance analysis and experimental verification of an unmanned aerial vehicle landing gear structure, (2018)

[8]

YAO G S., The key strength of aircraft landing gear components analysis and structural optimization, (2014)

[9]

YAN Z G, ZHAO Y Y., Study and progress of nonlinear dynamics of aircraft landing gear vibrating system, Science Technology and Engineering, 18, 13, pp. 186-190, (2018)

[10]

LEI Y, LIN R Z, WU Z Q., Experimental study on the aerodynamic arrangement of small multi-rotor aircraft with high capacity payload, Acta Armamentarii, 40, 6, pp. 1323-1328, (2019)

← 1 2 →