Thermal-Structural Coupling Dynamics of Space Truss-Membrane Structures Based on Isogeometric Analysis

When space truss-membrane structures periodically enter and exit the sunshine area and the shadow area, it may generate thermally induced vibration in the interaction between thermal shock and structural deformations. Isogeometric analysis is applied to the thermal-structural coupling dynamics analysis of space truss-membrane structures. Established models of beam and membrane elements can properly describe the large deformation of the flexible structure under thermal shock. The thermal governing equations of thin-walled beams and membranes are derived, and isogeometric discretization is performed. Equations of motion and thermal governing equations are solved iteratively by the generalized-alpha scheme. The correctness of the model and the solution algorithm is verified by the thermally induced vibrations of a space cantilever thin-walled tube. Finally, a model of the truss-membrane structure is devised, and its dynamic response at different sun incident angles is analyzed. The results show that the maximum quasi-static deformation of a truss-membrane structure occurs when the sun shines vertically. Thermal flutter may occur when the space boom axis points away from the sun and the large deformation of the membrane under thermal shock causes lateral disturbance to the truss. The results indicate that the proposed isogeometric analysis can be used to evaluate the dynamic stability of space truss-membrane structures in orbit. (C) 2022 American Society of Civil Engineers