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Open AccessArticle

Fabrication and Testing of the Cold Gas Propulsion System Flight Unit for the Adelis-SAMSON Nano-Satellites

Rafael—Advanced Defense Systems, Haifa 3102102, Israel
Asher Space Research Institute (ASRI), Technion—Israel Institute of Technology, Haifa 320003, Israel
Author to whom correspondence should be addressed.
Aerospace 2019, 6(8), 91;
Received: 27 June 2019 / Revised: 5 August 2019 / Accepted: 13 August 2019 / Published: 19 August 2019
Adelis-SAMSON is a nano-satellite mission aimed at performing geo-location of target signals on Earth using a tight three-satellite formation in space. To maintain formation, each nano-satellite is equipped with a cold gas propulsion system. The design, qualification, and integration of the Adelis-SAMSON nano-satellite propulsion system is presented in this paper. The cold gas propulsion system mass is approximately 2 kg, takes a volume of 2U, and generates a thrust of 80 mN from four thrusters using krypton as a propellant. We first present the propulsion system requirements and corresponding system configuration conceived to meet the mission requirements. Subsequently, we present the system architecture while listing all the components. We overview the particular role and qualification process of four of the propulsion system’s components: the propellant tank, thruster assembly, pressure regulators, and fill and vent valve. We detail the tests performed on each component, such as proof pressure tests, vibration tests, and external leak tests. Finally, we present the propulsion system level tests before delivery for satellite integration and discuss the propulsion system’s concept of operations. View Full-Text
Keywords: space propulsion; cold gas propulsion; space flight systems space propulsion; cold gas propulsion; space flight systems
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MDPI and ACS Style

Zaberchik, M.; Lev, D.R.; Edlerman, E.; Kaidar, A. Fabrication and Testing of the Cold Gas Propulsion System Flight Unit for the Adelis-SAMSON Nano-Satellites. Aerospace 2019, 6, 91.

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