| 黄朋辉， 刘超峰*， 陈杰， 古学伟， 苏阳.微型折叠翼设计与仿真实验分析[J].轻工机械,2022,40(3):101-104 |
| 微型折叠翼设计与仿真实验分析 |
| esign and Simulation Analysis of Miniature Folding Wing |
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| DOI：10.3969/j.issn.1005 2895.2022.03.017 |
| 中文关键词: 无人机 折叠翼 展开接触力 ADAMS SolidWorks |
| 英文关键词:UAV（Unmanned Aerial Vehicle） folding wing unfolding contact force ADAMS SolidWorks |
| 基金项目: |
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| 摘要点击次数: 186 |
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| 中文摘要: |
| 为了减小微型无人机的横向尺寸并在有效空间内部署更多的无人机，课题组设计了一种可用于微型飞行器的折叠翼机构。以曲柄滑块机构为基础设计了折叠翼机构，采用SolidWorks建立了折叠翼机构的三维模型；采用ADAMS对折叠翼机构进行运动学分析；以拉力弹簧为驱动进行驱动力建模，以展开时间、接触力等为评价指标对折叠翼机构进行运动学分析，得到了在特定拉力弹簧作用下的实验数据。实验结果表明：在拉力弹簧作用下折叠翼可有效展开，展开时间为0.2 s，展开性能稳定。该折叠翼应用于微型飞行器可减小微型飞行器的存储空间，并保护机翼等部件。 |
| 英文摘要: |
| In order to reduce the lateral size of micro UAV and deploy more unmanned aerial vehicles (UAVs) in effective space, a folding wing mechanism for micro UAV was studied. The folding wing mechanism was designed based on crank slider mechanism. The three dimensional model of folding wing mechanism was established by SolidWorks software. The kinematics of folding wing mechanism was analyzed by ADAMS. The driving force was modeled by using the tension spring as the driving force. The kinematic analysis of the folding wing mechanism was carried out by taking unfolding time and unfolding contact force as evaluation indexes. The experimental data under the action of a particular tension spring were analyzed. The experimental results show that the folding wing can be effectively expanded under the action of tension spring, and the expansion time is 0.2 s, and the expansion performance is stable. The folding wing can be used to reduce the storage space of the micro air vehicle and protect the wing and other components. |
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