An Iterative Determination Method of an Axial Deployment Force of a Lanyard-Deployed Coilable Mast in Local Coil Mode

IF 1.1 4区工程技术 Q3 ENGINEERING, AEROSPACE

International Journal of Aerospace Engineering Pub Date : 2024-03-26 DOI:10.1155/2024/3503468

Yu Liu, Liang Sun, Hai Huang, Xurui Zhao, Jiahao Liu, Yishi Qiao

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引用次数: 0

Abstract

The axial deployment force is an indispensable parameter of a lanyard-deployed coilable mast, which reflects its load capacity in practical applications. However, research on the axial deployment force in the literature is very limited, and there are no mature numerical methods to determine this parameter in the design stage of coilable masts. In this paper, a numerical method for determining the axial deployment force of a lanyard-deployed coilable mast in the local coil mode is presented. Through this method, the designer can quickly obtain the estimated value of the axial deployment force in the design stage, which is convenient for the quantitative design of parameters. To verify the correctness of the proposed method, a dynamic simulation of the coilable mast is carried out, and a microgravity test is performed. The comparison results show that the error between the numerical method and the simulation and experimental results is less than 5%, which proves the correctness of the proposed method. In addition, the coilable mast studied in this paper has been verified by an actual microsatellite deployment in orbit.

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局部卷绕模式下系索式可卷绕桅杆轴向展开力的迭代确定方法

轴向展开力是系索式可卷绕桅杆不可或缺的参数，它反映了桅杆在实际应用中的承载能力。然而，文献中关于轴向展开力的研究非常有限，在可卷绕桅杆的设计阶段也没有成熟的数值方法来确定该参数。本文提出了一种数值方法，用于确定局部线圈模式下系索式可卷绕桅杆的轴向展开力。通过该方法，设计人员可以在设计阶段快速获得轴向展开力的估算值，方便参数的定量设计。为了验证所提方法的正确性，对可卷绕桅杆进行了动态模拟，并进行了微重力试验。对比结果表明，数值方法与仿真和实验结果之间的误差小于 5%，证明了所提方法的正确性。此外，本文所研究的可卷曲桅杆还通过在轨道上实际部署微型卫星得到了验证。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Aerospace Engineering ENGINEERING, AEROSPACE-

CiteScore

2.70

自引率

7.10%

发文量

195

审稿时长

22 weeks

期刊介绍： International Journal of Aerospace Engineering aims to serve the international aerospace engineering community through dissemination of scientific knowledge on practical engineering and design methodologies pertaining to aircraft and space vehicles. Original unpublished manuscripts are solicited on all areas of aerospace engineering including but not limited to: -Mechanics of materials and structures- Aerodynamics and fluid mechanics- Dynamics and control- Aeroacoustics- Aeroelasticity- Propulsion and combustion- Avionics and systems- Flight simulation and mechanics- Unmanned air vehicles (UAVs). Review articles on any of the above topics are also welcome.