In this paper, the deployment systems of a deployable space telescope for CubeSat are proposed. This telescope can achieve a ground resolution less than 1 meter at an orbital altitude of 400 km. Both the primary and secondary mirrors of it can be stowed in 3U volume 1/4 100mm×100mm×300mm during launching period. The functions of the deployment systems include the locking of the primary and secondary mirrors when stowed, the deployment on-orbit, and the active adjustment of the primary mirror segments after deployment. In this paper, firstly, the optical system of deployable telescope is described, then the deployment systems of the telescope are designed. Finally, the modal analysis is carried out using finite element method. © COPYRIGHT SPIE. Downloading of the abstract is permitted for personal use only.