Abstract
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.
Highlights
In recent years, nano-satellite missions consisting of spacecraft with a launch mass of less than 50 kg have seen a rapid growth from less than 20 nano-satellites launched in 2010 to over 200 launched in 2018 [1]
We present a brief overview of the propulsion system concept of operations for the successful execution of the Adelis-SAMSON mission
We overviewed the particular role and qualification processes of four of the propulsion system’s components, all of which were produced at Rafael
Summary
Nano-satellite missions consisting of spacecraft with a launch mass of less than 50 kg have seen a rapid growth from less than 20 nano-satellites launched in 2010 to over 200 launched in 2018 [1]. Cubesats are nano-satellites constructed of basic 10 × 10 × 10 cm units, denoted “U” Due to their small size and modular structure, cubesats are cost-effective and integrated compared to conventional satellites weighing hundreds or several thousands of kilograms. For this reason, numerous universities and academic institutes have executed cubesat missions where the cubesat was manufactured and integrated in-house by the academic institutes. This poses technological challenges to the academic institutes and industries that in many cases have to develop their own subsystems tailored for cubesats
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