The exponential growth of small satellite usage for space applications requires self- deployable systems to be highly storable without compromising the mechanical and functional requirements under deployed conditions. The scope of this paper is to highlight the design, development and realization aspect of self-deployable composite boom. Composite boom consists of a thin walled structure with high strain energy storage capability. Boom has a closed cross-section to increase the stiffness by its geometry and at same time to add the flexibility in the structure, a flexure is introduced by providing a mechanical slit at the centre of the boom. Several iterations have been carried out for selection of the material, layup sequence and geometry optimization. To meet the requirement of folding and unfolding behaviour Kevlar Fibre Reinforced Plastic (KFRP) material is used and a slit is optimized for realization of the composite booms. Subtended angle of the slit at the centre of the boom is also optimized. Design iterations are also worked out to optimize the layup sequence of the KFRP laminae w.r.t the axis of the boom. Length of the slit has also played a significant role in folding and unfolding of the boom.