This paper presents the multidisciplinary design optimization of monopropellant propulsion system of the nanosatellite for planner maneuver.Mass, configuration Blankets and internal ballistic equations are derived for any part of propulsion system (thruster, tank, pressurized gas,.).
Minimizing total mass of the propulsion system and satisfying all constrains such as Thrust limitation 5 (N) and 10 (N), Minimum specific Pillowcases impulse () and minimum throttle area ().AAO framework is developed and the direct search is selected for optimization method.Finally optimum designs are introduced and compared for 10(N) and 5(N) monopropellant propulsion system.