Dynamic Modeling and Synchronous Deployment Analysis of Bidirectional Solar Array with Clearances

The synchronization of deployable components is crucial for the successful deployment of solar array systems. This study employs close cable loop (CCL) mechanisms to facilitate synchronous deployment of a large solar array system. A multibody dynamics model based on the natural coordinate formulation is developed for a two-step deployable bidirectional solar array with multiple clearance joints. This model is used to investigate the influences of CCL mechanisms on the dynamic behaviors, collision characteristics, and spacecraft main-body attitude performances of the bidirectional solar array during two deployment phases. A multistage solving strategy is proposed to efficiently handle the complex topological transformations involved. The findings demonstrate that a larger CCL equivalent stiffness coefficient enhances the synchrony of the main solar panels during the first deployment phase. However, during the second deployment phase, it worsens the synchrony of the side panels as the stronger excitation forces are generated by locked main panels. Additionally, an increased CCL equivalent stiffness coefficient accelerates the vibration attenuation and enhances nonlinearity of the system. Meanwhile, it also worsens the spacecraft’s attitude and intensifies the collision between the journal and bearing.