Optimization of Micro-Thruster Cold Gas Propulsion System Design for Space Applications | Journal of

Cold gas micro thrusters are much simpler than other propulsion thrusters in terms of hardware and control system complexity. For mass requirement, mass flow rate, valves, and feed system design, numerical calculations were used, and computational fluid dynamics with finite element analysis was used for tank, pipe, and nozzle design. For tank design, four different materials were considered: structural steel, stainless steel, aluminium, and titanium. For four different tank geometries, they were subjected to the same conditions. The propulsion system was intended to produce between 1 and 2 minutes of continuous thrust and between 0.8 and 1 second of gas expulsion in sudden impulses, with a desired thrust time of over 20 impulses. The mass and volume required for a variety of tank geometries, ideas, and materials have been calculated. Pressure Distribution, Velocity Profile, Temperature Distribution, Nozzle Efficiency, and the corresponding Mach Number Distribution were the primary performance characteristics of the micro thrusters that were assessed. The aim of this project is to create a stable and controllable platform for testing equipment that will be used in space applications.

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