Design and Configuration of Ground Sample Components of Low Propulsion Monopropellant Thruster Using Some Engineering Software

Davari, Sajjad; Karimaei, Hadiseh; Salimi, Mohammad Reza; Naseh, Hassan

doi:10.30699/jsst.2023.1319

Document Type : Research Paper

Authors

¹ Researcher, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran

² Assistant Professor, Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran, Iran

https://doi.org/10.30699/jsst.2023.1319

Abstract

Monopropellant thruster are used to inject a satellite into orbit or control its position on three axes in space missions. One of them is hydrazine thruster which is widely used. In this research, design of the injector, decomposition chamber and nozzle of a 10N hydrazine monopropellant thruster have been performed. The capillary injector was designed using Fluent software for this thruster which was able to supply the mass flow rate of the thruster (5 gr/sec). The decomposition chamber contains catalyst granules and its dimensions were selected based on the complete decomposition of hydrazine. The nozzle was designed by RPA software. The validation of the design with RPA software was checked by a numeric code. This code was able to calculate the dimensions of the decomposition chamber based on the amount of hydrazine decomposition. Accordingly, the results of both design methods are strongly consistent with each other. At the end of the design, the final thruster design and drawings were prepared.

Keywords

20.1001.1.20084560.1402.16.1.4.5

Main Subjects

System Design, Space Propulsion and Space System Simulation

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Design and Configuration of Ground Sample Components of Low Propulsion Monopropellant Thruster Using Some Engineering Software

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References

Volume 16, Issue 1 - Serial Number 55March 2023Pages 35-46

Volume 16, Issue 1 - Serial Number 55
March 2023
Pages 35-46