抄録
With over 272 attempted launches since 2000, CubeSat technology has exponentially increased as industries and universities have realized their potential. While this growth looks promising for space research possibilities, there are still a number of issues, with the largest being CubeSat maneuverability. The majority of CubeSats cannot orient or propel themselves, meaning mission functionality is limited and collision probability will increase as time goes on. CubeSat technology has been improving, and the mission of this technology has become increasingly more important in the development and advancement of new technologies. The Micro-propulsion and Nanotechnology Laboratory at The George Washington University has constructed a four-channel Micro-Cathode Arc Thruster (μCAT) micro-propulsion subsystem that allows these satellites to perform missions without reliance on their launch vehicles. The propulsion system has a volume of approximately 541 cm3 that can produce specific impulse values up to 3000 s. Each μCAT onboard is used for the CubeSat's attitude control, orbit change, de-orbiting, and movement. The μCAT system was integrated into the USNA's 1.5U CubeSat (BRICSat-P) to be used to perform three maneuvers while at an orbit of 500 km: de-tumbling, spin, and a deltaV that will attempt to change the orbit of the CubeSat relative to the orientation of Earth's magnetic field. The objective of this paper is to provide an overview of the thruster subsystem’s development and application for the BRICSat-P mission parameters. In addition, the μCAT subsystem’s circuitry, thruster head design, and development will be reviewed to provide the information used to reach CubeSat flight standards.
