Affiliation:
1. Key Laboratory of Dynamics and Control of Flight Vehicle, Ministry of Education, School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, P. R. China
Abstract
A coupled thermal-structural model of a laminated composite plate is proposed by using the absolute nodal coordinate formulation, the transverse shear and normal deformations through element thickness are included. The dynamic equations of structure are established by applying the d'Alembert's principle and then solved numerically to determine dynamic responses and transient heat conduction in the structure due to the nonlinear elastic force and thermal radiation. A cantilevered flexible solar panel subjected suddenly to a solar radiation is examined, it is found that by considering the coupling between the thermal and structural responses, thermal flutter of the composite panel can be well predicted. The coupled behavior of the composite solar panel with a satellite is also analyzed by idealizing it as a rigid-flexible multibody system in the low earth orbit, in which a natural coordinate formulation is established to analyze the attitude of the satellite rigid hub, the thermal snap phenomenon is also well predicted.
Publisher
World Scientific Pub Co Pte Lt
Subject
Mechanical Engineering,Mechanics of Materials,General Materials Science
Cited by
31 articles.
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