Session
Swifty Session 2
Abstract
The use of carbon dioxide as propellant makes small satellite maneuverability safe, affordable and attractive to use for academic space missions. We present a preliminary conceptual design of a propulsion system based on carbon dioxide propellant. The design was tailored for the SAMSON 6U nano-satellite constellation. A careful analysis of the gas properties was made, which provided the essential working points and architecture of the propulsion system. Subsequently, a dedicated conceptual design was performed to comply with the propellant working points and basic satellite requirements. The main components, such as the propellant storage tank and thruster nozzle, were defined and designed. Overall, the system mass is 1,777 gr of which the propellant is 310 gr. The system can generate thrust of 80 mN and ΔV of 20 m/s. Finally, we present an operational analysis of the system, defining the operational constraints and performance. A full mission simulation was run, utilizing the propulsion system characteristics while satisfying mission requirements. The final design fully complies with the mass, volume and performance requirements.
Carbon Dioxide Based Heated Gas Propulsion System for Nano-Satellites
The use of carbon dioxide as propellant makes small satellite maneuverability safe, affordable and attractive to use for academic space missions. We present a preliminary conceptual design of a propulsion system based on carbon dioxide propellant. The design was tailored for the SAMSON 6U nano-satellite constellation. A careful analysis of the gas properties was made, which provided the essential working points and architecture of the propulsion system. Subsequently, a dedicated conceptual design was performed to comply with the propellant working points and basic satellite requirements. The main components, such as the propellant storage tank and thruster nozzle, were defined and designed. Overall, the system mass is 1,777 gr of which the propellant is 310 gr. The system can generate thrust of 80 mN and ΔV of 20 m/s. Finally, we present an operational analysis of the system, defining the operational constraints and performance. A full mission simulation was run, utilizing the propulsion system characteristics while satisfying mission requirements. The final design fully complies with the mass, volume and performance requirements.
