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Graphical abstract Abstract In this paper, a dynamic model equation of the RazakSAT ® class satellite three flexible solar panels for three-dimensional dynamic studies is developed based on the coupling deformation field. In the model, each solar panel is flexible and attached to the satellite body via a fixed joint where the assumption of Euler-Bernoulli beam is applied for the solar panels. Lagrange and assumed mode method are used to develop the dynamic model of the RazakSAT ® multi-bodydoi:10.11113/jt.v76.5857 fatcat:f6uhtevv3bcrzd63xatfqzz6ka