Hybrid Hot and Cold Gas Micro Thruster for Rocket

This study presents the design, numerical analysis, and performance evaluation of a titanium-based Hot Gas Thruster (HGT) system for small satellite propulsion. Operating with ethanol at 3,000,000 Pa inlet pressure, the thruster offers a non-combustive, low-risk alternative to traditional systems. Using CFD simulations, the internal flow dynamics, turbulence, and nozzle interactions are analyzed to assess efficiency and optimize performance. Results highlight the system's potential for precise, cost-effective, and safe maneuvering in small satellite applications.