Multidisciplinary Conceptual Design Optimization of Monopropellant Propulsion System of Nanosatellite

Multidisciplinary Conceptual Design Optimization of Monopropellant Propulsion System of Nanosatellite

Blog Article

This paper presents the multidisciplinary design optimization of monopropellant propulsion system of the nanosatellite for planner maneuver.Mass, configuration and internal ballistic equations are derived for any part of propulsion system (thruster, tank, pressurized gas,.).Minimizing total Automotive Kits mass of the propulsion system and satisfying all constrains such as Thrust limitation 5 (N) and 10 (N), Minimum specific 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) Shacket and 5(N) monopropellant propulsion system.