Parametric Analysis of a Convergent-Divergent Nozzle for 2N Cold Gas Propulsion of a Nanosatellite

Abstract

In recent times, the concepts of microsatellite development have been a versatile subject ranging from their ability to reduce overall cost of satellites to their improved efficiency and adaptability. This has brought new innovations about creating micro-components for the satellite missions. The study of convergent-divergent (C-D) nozzle is an ever-growing research area due to its wide applications particularly in the aerospace field. Hence, this research study particularly looks into studying the influence of varying divergence angle and divergence length on flow parameters for optimum nozzle design. Propellant selection criteria were drawn up for cold gaseous propellants to test their effectiveness leading to the choice of compressed air and Nitrogen as preferred propellants due to their availability, inertness and non-toxicity. Varying the divergence angle of a C-D nozzle produced a series of nozzle geometries and the analysis of simulation results yielded an optimum angle of 15° with choking effect at the throat located at 0.3m. Other divergence angles considered including 5°, 10°, 20°, 25° and 30o generated multiple shocks across the nozzle throat. A divergence length of 1.35m produced the highest exit pressure of 61.756kPa close to ambient pressure. Divergence length of 1.35m coupled with a divergence angle of 15° appears to be most appropriate for the design of a C-D nozzle suitable for microsatellite propulsion system.