Session
Technical Session X: Subsystems & Components II
Abstract
Low-cost satellites need low-cost propulsion systems. The research summarised in this paper has focused on investigating low-cost propulsion system options for small satellites with specific application to the upcoming UoSAT-12 mini satellite mission. The research began by looking at available propulsion system technology. Low-cost spacecraft engineering techniques were then explored to identify specific system cost drivers for further investigation. This led to parallel research efforts aimed at (1) basic research & development into hybrid rockets to characterise their applicability to low-cost spacecraft, and (2) applied research into low-cost spacecraft systems engineering - to design and implement a system for UoSAT-12. The experimental results from a 400-Newton thrust hydrogen peroxide and polyethylene hybrid motor are presented. Initial results indicate that >90% combustion efficiency is achievable and an experimental hybrid mission could feasibly be developed over the next few years. Additional research into low-cost propulsion is also discussed including the application of a low thrust (20-Newton) bi-propellant rocket engine - the LEROS-20, developed by British Aerospace, Royal Ordnance Rocket Motors Division. The combination of innovative manufacturing techniques along with low-cost procurement practices makes this engine an attractive, low-cost option. Finally, research into decreasing the cost of support subsystems has lead to a simple, low-cost design which is being implemented on UoSAT-12 at a fraction of the cost of that predicted by industry standard models.
Investigation into Low-Cost Propulsion Systems for Small Satellite Missions
Low-cost satellites need low-cost propulsion systems. The research summarised in this paper has focused on investigating low-cost propulsion system options for small satellites with specific application to the upcoming UoSAT-12 mini satellite mission. The research began by looking at available propulsion system technology. Low-cost spacecraft engineering techniques were then explored to identify specific system cost drivers for further investigation. This led to parallel research efforts aimed at (1) basic research & development into hybrid rockets to characterise their applicability to low-cost spacecraft, and (2) applied research into low-cost spacecraft systems engineering - to design and implement a system for UoSAT-12. The experimental results from a 400-Newton thrust hydrogen peroxide and polyethylene hybrid motor are presented. Initial results indicate that >90% combustion efficiency is achievable and an experimental hybrid mission could feasibly be developed over the next few years. Additional research into low-cost propulsion is also discussed including the application of a low thrust (20-Newton) bi-propellant rocket engine - the LEROS-20, developed by British Aerospace, Royal Ordnance Rocket Motors Division. The combination of innovative manufacturing techniques along with low-cost procurement practices makes this engine an attractive, low-cost option. Finally, research into decreasing the cost of support subsystems has lead to a simple, low-cost design which is being implemented on UoSAT-12 at a fraction of the cost of that predicted by industry standard models.
