Abstract: To meet the urgent demand for large-scale and high-packing-ratio space support mechanisms in spacecraft, a modular multi-fold rib deployable support mechanism with topological array characteristics was proposed. Firstly, the overall scheme design of the deployable support mechanism was carried out, and the structure composition and deployment principle of the rib unit were described. Secondly, a parametric model of the rib unit was established based on the closed-loop vector method. By solving the kinematic constraint equations, the parametric calculation of the linkage dimensions was achieved, and kinematic simulation was conducted using the numerical simulation software MATLAB to verify the correctness of the model. Subsequently, detailed structure design of the key components of the mechanism was conducted, and a three-dimensional model of the deployable support mechanism was established. The deployment process of the modular unit was simulated and verified using the virtual prototyping software ADAMS. Finally, to validate the engineering feasibility of the design, a principle prototype was developed based on 3D printing technology, and ground deployment experiments were carried out to further verify the feasibility of the proposed scheme. The research results indicate that the principle prototype has a measured mass of 0.901 kg and a comprehensive-packing-ratio of 15.7 : 1, demonstrating good extensibility and providing a new design approach and engineering reference for future large-scale space deployable support mechanisms.