Dynamics modeling of flexible multibody structure for a spacecraft mechanism with nonlinear factors

This chapter establishes a methodology for modeling a spacecraft deployment and locking mechanism comprising laminated composite appendages with a large rotational motion; the nonlinear model takes into account the coupling relationship between a large rotational motion and geometric nonlinear characteristics of laminated material. The deformation description of laminated material is established with the consideration of laying angles and layers, and the displacement-strain relationship is acquired based on the third-order shear deformation theory. Furthermore, the effect of contact and impact located at a spring hinge is investigated, which can achieve the actuating and locking functions. The generalized contact-impact forces between the pin and locking groove are considered in the model. Then, the corresponding efficient formulations for evaluating both nonlinear stiffness terms and elastic force are derived explicitly using the third-order laminated plate theory and Hamilton’s principle. The dynamics behavior of the spacecraft system is analyzed by comparison of orthogonal-symmetric, singular and unidirectional laminated materials. The results show that the laminated composite structures have significant influences on dynamics characteristics of the spacecraft. Hence, the nonlinear model is well suitable for approaching the problem of coupling relationship between the geometric nonlinearity and large rotation motions.