航天器
复合数
太阳帆
材料科学
运动方程
结构工程
航空航天工程
工程类
复合材料
物理
经典力学
作者
Zhang Wei,Weiping Zhu,Shijie Zhang
出处
期刊:Journal of Aerospace Engineering
[American Society of Civil Engineers]
日期:2020-11-01
卷期号:33 (6)
被引量:10
标识
DOI:10.1061/(asce)as.1943-5525.0001186
摘要
Modern spacecraft often deploy large-scale and lightweight solar arrays consisting of composite-laminated plates because of their high reliability, superior mechanical properties, and low manufacturing cost. This paper presents the deployment dynamics of a flexible solar array composed of composite-laminated plates undergoing large rotation and large deformation motions. The subject is a constrained rigid–flexible coupling spacecraft consisting of a rigid main body and a flexible solar array composed of composite-laminated plates. The rigid main body and the flexible solar array are described by the natural coordinate formulation and the absolute nodal coordinate formulation, respectively. A constitutive model of a laminated shell formed of fiber-reinforced composite material is established, and the corresponding generalized elastic force is derived. Thus, the spacecraft’s equations of motion are derived as a set of differential algebraic equations and a computational scheme based on the Hilber-Hughes-Taylor (HHT)-I3 method is illustrated. A series of numerical calculations and simulations are conducted to investigate the solar array deployment dynamics. The results show that the solar panel flexibility and fiber orientation of fiber-reinforced composite materials have obvious effects on spacecraft dynamic responses during solar array deployment.
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