A hybrid optimization approach combining a genetic algorithm (GA) with sequential quadratic programming (SQP) has been used for optimization of the trajectory profile of a three stage solid propellant small launch vehicle configured from existing solid rocket motors. The selected launch vehicle (LV) is capable of delivering a small satellite of 80 kg to a low earth orbit (LEO) of 660 km altitude. This hybrid optimization approach combines the advantage of GA as a global optimizer and complemented with SQP to find the local optimum. The vertical flight time, launch maneuver variable, maximum angle of attack, coasting time between the first and second stage and the second coasting time between the second and third stage were optimized. It is shown that the proposed hybrid optimization approach was able to find the convergence of the optimal solution with very acceptable values. © 2013 IEEE.