This paper presents a sounding rocket (SR) development program considering the indigenous technology development evolution. This program was elaborated with the main objective of delivering a small scientific payload of 5-80 kg to suborbital flight of 80-200 km maximum altitude. Several SRs has been proposed with specific characteristics and performances, each SR design model has been optimized using a heuristic optimization method. An integrated multidisciplinary design optimization framework based on a multi discipline feasible (MDF) has been implemented along with the aerodynamic, propulsion, mass, and dynamic models. The proposed solid propellant SR development program serves as base of future developments and represents a cost effective initiative for a small country with limited space development budget to master the basic knowledge to rapid access into space.