The development of small satellite payloads in current times requires efficient use of limited space, while achieving high performance. For high-performance missions, reflector antennas with a certain size or larger may be necessary, but spatial constraints can pose a challenge. To overcome these limitations, researchers are designing these structures in deployable configurations.In this research, we propose the origami-based deployable structure, which can be easily and efficiently packed. The structure is able to deploy itself by applying a compliant flexure hinge. In order to evaluate the performance of the proposed deployable reflector structure, the packaging efficiency, surface error, and focus error are analyzed in relation to changing the design parameter. A deployable prototype is constructed using a torsion-based compliant hinge. Finally, the position change of specific points is experimentally measured to analyze a deployment repeatability.