Deployment Dynamics for a Flexible Solar Array Composed of Composite-Laminated Plates
Publication: Journal of Aerospace Engineering
Volume 33, Issue 6
Abstract
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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Data Availability Statement
All data and models generated or used during the study appear in this article.
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Journal of Aerospace Engineering
Volume 33 • Issue 6 • November 2020
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© 2020 American Society of Civil Engineers.
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Received: Dec 9, 2019
Accepted: May 29, 2020
Published online: Jul 25, 2020
Published in print: Nov 1, 2020
Discussion open until: Dec 25, 2020
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