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Abstract: The deployable boom plays an important role in the realisation of various spacecraft missions. In this paper, we will propose a deployable boom that is composed of a lenticular boom with a storage reel, a retractable/deployable mechanism and other auxiliary devices for use in a small spacecraft. To satisfy the requirements of specific specifications, such as having a small stowed volume, being light weight, having a large magnification ratio and an unrumpled retraction/deployment, an optimal design of the deployable boom is developed based on a review of its mechanical analysis. Therefore, the parameters of the boom's cross-section and the diameter of the storage reel are optimised using definite geometrical and physical constrains. Furthermore, by considering the geometrical dimensions and the energy equilibrium relationship constrains, key parameters of the retractable/deployable mechanism are deduced. Additionally, it is valuable to mention that the sequential quadratic programming method is adopted to reduce the computational complexity. Finally, the results of a finite element method are in good agreement with the aforementioned theoretical prediction, which validates the efficiency of the optimal design for the deployable boom. [Copyright &y& Elsevier]