It is well known that the rolling of the hinge mechanism is the most fragile part on the fully-deployed solar array system when the spacecraft involves a rapid maneuver. In this investigation, a new accurate solar array model is proposed with introducing the hinge rolling in order to capture its inner deformation and stress. The structure of the hinge rolling is explicitly presented. Both the panel and the hinge rolling are modeled by a three-dimensional (3D) fully-parameterized beam using the Absolute Nodal Coordinate Formulation (ANCF). When assembling the panels and its hinge rolling, the concept of body coordinate system is first used to address slope discontinuity problem, and then a set of linear kinematic formulations of the rigid joint is derived that is used for them connection. The resulting equations of motion for the constrained rigid-flexible multibody system is solved by the implicit 4th Adams algorithm. The proposed model is validated using the FE part module of MSC.ADAMS commercial software. Four numerical examples are simulated to study the performance and advantages of the proposed solar array model. Furthermore, this proposed model is also used for the attitude control study of spacecraft main body. It is shown that this accurate model can be a good candidate for the engineering application and subsequent control usage.