F. Benzenine - Department of Mechanical Engineering, Energetic and Applied Thermal Laboratory ETAP, University of technology, Chetouane ۱۳۰۰۰, Tlemcen, Algeria
C. Seladji - Department of Mechanical Engineering, Energetic and Applied Thermal Laboratory ETAP, University of technology, Chetouane ۱۳۰۰۰, Tlemcen, Algeria
D. Darfilal - Satellites Development Center, Algerian Space Agency ASAL, IbnRochd USTO ۳۱۱۳۰, Oran, Algeria
O. Bendermel - Department of Mechanical Engineering, Energetic and Applied Thermal Laboratory ETAP, University of technology, Chetouane ۱۳۰۰۰, Tlemcen, Algeria

In this paper, an analytical approach combined with a two-dimensional computational fluid dynamics (CFD) model is pursued to simulate the fluid flow in a monopropellant thruster for satellite propulsion systems. The thruster utilizes hydrogen peroxide (H۲O۲) as a green propellant at a concentration of ۸۷.۵%, with a catalytic bed based on spherical silver particles. Through a parametric analysis of particle diameter, we aim to optimize the design of a monopropellant thruster capable of generating a thrust of ۲۰N. For this purpose, a program in CFD code in the commercially available ANSYS Fluent software is used to solve the energy, momentum, mass transfer, and species transport equations governing the thruster system. The local thermal non-equilibrium (LTNE) approach is used to describe the heat transfer occurring through both the solid and fluid phases within the catalyst bed. The results demonstrate that particle size significantly affects the thermal behaviour, species mass fraction, and exit velocity. An optimum diameter of ۰.۶۵mm exhibits the optimal performance of the monopropellant thruster, ensuring efficient decomposition of H۲O۲ at ۹۶۸K and providing the required level of thrust force with a specific impulse of about ۱۲۰s.

Propulsion, Monopropellant thruster, Hydrogen peroxide, Catalyst packed-bed, Porous medium