Session
Technical Session V: Propulsion
Abstract
CubeSat technology and mission envelope has been steadily increasing in the recent years as the CubeSat platform became increasingly popular throughout space community. One of the key technologies that will advance the satellite capability to a higher level is propulsion. Commercially available propulsion system for CubeSats, including electric propulsion units, currently exist. However, the size and power consumption of the current electric propulsion units make them difficult to be integrated to smaller form factor CubeSats with lower power and volume availability. The Micro-Cathode Arc Thruster, a micro-propulsion system developed by The George Washington University, seeks to provide a solution for the power and volume limitations of smaller CubeSats. Four Micro-Cathode thrusters have been successfully integrated and tested in space onboard the U.S. Naval Academy (USNA)’s 1.5 U CubeSat, BRICSat-P. This system will enable satellite developers to plan and build more ambitious and complex CubeSat missions. The thruster gives CubeSats (and other small satellites) the ability to perform orbital maneuvers, orbital corrections, and active attitude control capabilities. The thruster utilizes a metallic propellant (e.g. nickel) to produce thrust. The propellant is ionized to a high degree (usually above 99 %) during the discharge, producing ions with velocities in the magnitude of 104 m/s. The AMODS mission by USNA will take advantage of these thrusters in order to perform rendezvous and docking maneuvers between two different 3 U CubeSats, RSat, and BRICSat. This paper will describe the Micro-Cathode Arc Thruster system, as well as the past, current, and future implementation of the system on USNA’s CubeSat missions.
μCAT Micro-Propulsion Solution for Autonomous Mobile On-Orbit Diagnostic System
CubeSat technology and mission envelope has been steadily increasing in the recent years as the CubeSat platform became increasingly popular throughout space community. One of the key technologies that will advance the satellite capability to a higher level is propulsion. Commercially available propulsion system for CubeSats, including electric propulsion units, currently exist. However, the size and power consumption of the current electric propulsion units make them difficult to be integrated to smaller form factor CubeSats with lower power and volume availability. The Micro-Cathode Arc Thruster, a micro-propulsion system developed by The George Washington University, seeks to provide a solution for the power and volume limitations of smaller CubeSats. Four Micro-Cathode thrusters have been successfully integrated and tested in space onboard the U.S. Naval Academy (USNA)’s 1.5 U CubeSat, BRICSat-P. This system will enable satellite developers to plan and build more ambitious and complex CubeSat missions. The thruster gives CubeSats (and other small satellites) the ability to perform orbital maneuvers, orbital corrections, and active attitude control capabilities. The thruster utilizes a metallic propellant (e.g. nickel) to produce thrust. The propellant is ionized to a high degree (usually above 99 %) during the discharge, producing ions with velocities in the magnitude of 104 m/s. The AMODS mission by USNA will take advantage of these thrusters in order to perform rendezvous and docking maneuvers between two different 3 U CubeSats, RSat, and BRICSat. This paper will describe the Micro-Cathode Arc Thruster system, as well as the past, current, and future implementation of the system on USNA’s CubeSat missions.
