Large telescopes which can collect more light and longer focal length for larger views are necessary to study the fine detailing of the Universe. Due to the limitations in the envelope, larger telescopes cannot be accommodated in any of the existing launch vehicles. Deployable space structures have gained popularity due to these requirements of large-scale space structures and envelope limitation of a rocket launch. They provide the advantage of folding to a tightly packed configuration and deploying to a much larger configuration in space and can take any form including cylinder and tripod. In the present study, a deployable truss structure was chosen and designed to accommodate the mirrors. The designed structure was then analysed for strength and stiffness requirements in both stowed and deployed configurations. Normal mode analysis is conducted to obtain the fundamental frequencies and mode shapes. Linear static analysis is performed to compute the stresses and reaction forces in the CFRP elements and metallic fittings. For the stability requirements, thermal distortion analysis is also performed numerically.