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 language | English |
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Title of host publication | Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019 |
Editors | S. Menekay, O. Cetin, O. Alparslan |
Publisher | Institute of Electrical and Electronics Engineers Inc. |
Pages | 159-166 |
Number of pages | 8 |
ISBN (Electronic) | 9781538694480 |
DOIs | |
Publication status | Published - Jun 2019 |
Event | 9th International Conference on Recent Advances in Space Technologies, RAST 2019 - Istanbul, Turkey Duration: 11 Jun 2019 → 14 Jun 2019 |
Publication series
Name | Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019 |
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Conference
Conference | 9th International Conference on Recent Advances in Space Technologies, RAST 2019 |
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Country/Territory | Turkey |
City | Istanbul |
Period | 11/06/19 → 14/06/19 |
Bibliographical note
Publisher Copyright:© 2019 IEEE.
Keywords
- Cold gas
- heater
- RESISTOJET
- small satellites