This paper proposes a solid propellant space launch vehicles (SLV) development program considering the indigenous technology development evolution. The proposed program was elaborated with the main objective to deliver a small payload of 100-200 kg into a low earth orbit of 600-800 km altitude. Several LVs have been proposed with specific characteristics and performances, each LV design model has been optimized using a heuristic optimization method. An integrated multidisciplinary design optimization framework based on multi discipline feasible (MDF) has been implemented along with the aerodynamic, propulsion, mass, and dynamic models. The proposed solid propellant SLV development program serves as the basis of future developments and represents a cost effective initiative strategy for a small country with limited space development budget to master the basic knowledge to rapid access into space.