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无人机折叠翼分步展开机构设计及动力学分析

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小型巡飞无人机折叠翼的展开方案对于无人机飞行模式切换具有重要影响.针对无人机折叠翼折叠特点与展开需求,提出同步展开和分步展开2种方案.采用拉格朗日法建立折叠翼展开动力学模型,应用气动力仿真软件计算折叠翼在展开过程中所受空气阻力,得出折叠翼采用不同展开方案时所需驱动力矩,以驱动力矩作为评判标准,选取折叠翼最优展开方案.仿真计算结果表明,折叠翼分步展开方案可在保证展开到位的情况下,以小力矩在短时间内完成展开运动.针对折叠翼分步展开方案设计折叠翼分步展开机构,并进行结构静强度分析,验证结构方案的可行性.
Stepwise Deployable Mechanism Design and Dynamics Analysis of UAV Folding Wing
Folding wing deployment scheme of small patrol UAV has an important influence on UAV flight mode switching.According to folding characteristics and deployment requirements of UAV folding wing,two deployment schemes synchronous deployment and stepwise deployment are proposed.With deployment dynamics model of a folding wing being established based on Lagrangian method,and folding wing drag force during deployment being calculated with aerodynamic simulation tool,driving torques needed for different deployment schemes are obtained.Driving torque is used as the evaluation criterion to optimise deployment scheme of the folding wing.Simulation results show that the stepwise deployment scheme has a short deployment time and a small deployment torque to reach the required deployment position.Finally,a deployment mechanism is designed for the stepwise deployment scheme,and static strength analysis of the structure is provided to verify the feasibility of the structure.

folding wingdeployment schemesLagrangiandynamical modelaerodynamic simulationstep deployment mechanism

许冶、许国胜、王钰坤、王刚、刘景旺、范伯钧、吴淼

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武汉天拓宇航智能装备有限公司,湖北武汉 430207

北华航天工业学院河北省跨气水介质飞行器重点实验室,河北廊坊 065099

北华航天工业学院河北省微小型航天器技术国防重点学科实验室,河北廊坊 065099

北京电子工程总体研究所,北京 100854

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折叠翼 展开方案 拉格朗日法 动力学模型 气动力仿真 分步展开机构

国家自然科学基金青年项目河北省青年自然科学基金河北省高等学校科学研究项目河北省省级科技计划河北省研究生创新资助

52305002E2021409025QN2022123213754140CXZSS2023164

2024

10.3969/j.issn.1009-086x.2024.01.004

现代防御技术
北京电子工程总体研究所

现代防御技术

CSTPCD北大核心
影响因子：0.357
ISSN：1009-086X
年,卷(期)：2024.52(1)
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