Design, Manufacturing and Testing of a Resistojet Suitable for Atmospheric Conditions

Document Type : Original Article

Authors

1 Assistant ProfessorIranian Space Research Center, Tabriz, Iran

2 PhD student, Iran Space Research Institute, Tabriz, Iran

3 Master's degree, Iran Space Research Institute, Tabriz, Iran

Abstract

The purpose of this paper is to design and manufacture a resistojet thruster based on butane propellant with the ability to perform tests in atmospheric conditions. The important sections for designing of this system are heater and nozzle design. The utilized heater is designed for direct heat transfer and the design of the nozzle is based on the thermodynamic relations governing a converging-diverging nozzle which is suitable for the atmospheric outlet pressure. CFD simulation has also been used to investigate the flow of propellant in the nozzle. In the following, the resistojet thruster was built based on the designing and experimental tests were carried out for its validation. By comparing the functional parameters of the thruster, such as thrust force and specific impulse from the experimental results and thermodynamic relationships, the design of the thruster is validated. Considering the heat exchanger power of 30 watts and also the most optimal conditions, the efficiency of the thruster is 21%, the thrust force is 36 millinewtons and the specific impact is computed as 35.9 seconds.

Keywords

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History

  • Receive Date: 24 October 2023
  • Revise Date: 18 January 2024
  • Accept Date: 25 January 2024
  • Publish Date: 19 February 2024

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