Development of a Satellite Nozzle-Thruster Design for Geostationary Orbit Deployment: CFD-Based Geometric Optimization for RIDU-Sat

Ahmad Dzakir Nurafif  Mahdin; Sumaryadi; Ansori

doi:10.55927/ijar.v5i5.16479

Authors

Ahmad Dzakir Nurafif Mahdin Motion Power Technology, Faculty of Engineering and Defense Technology, Defense University
Sumaryadi Motion Power Technology, Faculty of Engineering and Defense Technology, Defense University
Ansori Motion Power Technology, Faculty of Engineering and Defense Technology, Defense University

DOI:

https://doi.org/10.55927/ijar.v5i5.16479

Keywords:

Nozzle-Thruster, Nozzle Geometry, CFD Simulation, Throat Diameter, Geostationary Orbit

Abstract

The development of an efficient nozzle-thruster is crucial for the RIDU-Sat nanosatellite to reach and maintain geostationary orbit (GEO) with minimal propellant consumption. This study optimizes the geometry of a convergent-divergent nozzle through Computational Fluid Dynamics (CFD) using ANSYS Fluent with hydrogen peroxide as the monopropellant. Three throat diameter variations (0.5 mm, 1 mm, and 2 mm) were tested with a convergent angle of 45° , and a divergent angle of 30° . The results show that the design with a 0.5 mm throat diameter produces the highest exit velocity (1740 m/s), thrust (609 mN), and specific impulse (177 s). The smaller the throat diameter, the higher these three performance parameters become due to more effective supersonic expansion. These findings provide an optimal nozzle design that can improve propulsion efficiency for the geostationary orbit deployment and maintenance maneuvers of RIDU-Sat.

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