RESISTOJET propulsion system for small satellite

Darfilal Djamal, Khatir Mohamed, Alim Rustem Aslan

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

5 Citations (Scopus)

Abstract

Due to the launch safety constraints placed on Space companies built microsatellites, designing a simple and reliable propulsion system with performance and characteristics in line with the typical requirements of microsatellites presents a significant challenge to aspiring engineers. This paper presents the design process of a low-cost, propulsion system with a two-phase high density propellant. The aim of this study is the preliminary design of a 50mN RESISTOJET system operating at low pressure. The preliminary design and the optimization of the thruster dimensions are presented.

Original languageEnglish
Title of host publicationProceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019
EditorsS. Menekay, O. Cetin, O. Alparslan
PublisherInstitute of Electrical and Electronics Engineers Inc.
Pages159-166
Number of pages8
ISBN (Electronic)9781538694480
DOIs
Publication statusPublished - Jun 2019
Event9th International Conference on Recent Advances in Space Technologies, RAST 2019 - Istanbul, Turkey
Duration: 11 Jun 201914 Jun 2019

Publication series

NameProceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019

Conference

Conference9th International Conference on Recent Advances in Space Technologies, RAST 2019
Country/TerritoryTurkey
CityIstanbul
Period11/06/1914/06/19

Bibliographical note

Publisher Copyright:
© 2019 IEEE.

Keywords

  • Cold gas
  • heater
  • RESISTOJET
  • small satellites

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