High Propellant Throughput Microthrusters for Next-Generation Nanosatellites

XCOR proposes to develop a family of small propulsion systems based on small thrusters (1 to 250 N). We will address the issues such as good thrust/weight ratio at small size, low toxicity propellants, and will demonstrate an increase in performance and maneuverability for microthruster technology compared to cold gas or monopropellants. The proposed propulsion system uses self-pressurizing nitrous oxide and ethane with specific impulse approximately 265 seconds for the smaller sizes and 280 seconds for the larger sizes where the injector geometry is more favorable for good mixing. XCOR has developed a 10 N thruster that will be modified with a high expansion vacuum nozzle and partial radiative cooling for this application. The technical objectives of the Phase I program will be to show a complete propulsion system design that masses 5 kg and has a useful propellant mass fraction. A further objective is to look at the trade between thruster types for a larger, more capable, higher thrust system in the 10 kg class and do a preliminary design on the larger system by the end of Phase I.