Mission analysis for CubeSat deorbiting using a micro-thrust thin-layer cathode arc thruster

This PhD project aims to carry out the mission analysis for a novel standalone deorbiting propulsion system, known as ALl- printed Propulsion System (ALPS), using printed electronics and thin-layer vacuum arc thruster technology and to innovate a micropropulsion system for nano- / micro-satellites.

Recent advances in CubeSats offer the potential to achieve space activities including high-quality Earth observation at a tenth, if not even cheaper, the cost of a traditional satellite. The increased demands on CubeSats and their abilities have led to the important new need of post-mission disposal mechanism to ensure failsafe and timely deorbit. Despite the proliferation of CubeSats, they have high failure rates due to their low costs and their fast development cycle. The average failure rate of CubeSats is higher than 55%, which is almost twice higher than double the rate of larger satellites, and some of CubeSats are not following the Inter-Agency Space Debris Coordination Committee (IADC) guidelines for post mission disposal, which is recommends a residual orbit lifetime to be no longer than 25 years. A robust and low-cost propulsion system, therefore, is required to provide the ability to conduct post-mission disposal of CubeSats thus enabling new missions and ultimately supporting the development of LEO space commerce.
The project is proposing a new concept of a micropropulsion system, called a ALl-printed Propulsion System (ALPS), to enable failsafe and timely deorbit and to provide a spacecraft-independent, safe, and timely deorbit capability.

The ALPS concept is unexplored and leverages advances in embedded flexible electronics, thin film energy storage, and printing technologies. A flexible thin-film is printed with a complete standalone propulsion system: an array of vacuum arc thrusters using metallic ink propellant are printed directly on the surface of the film. Supporting subsystems are embedded in the film or printed on the surface as required, including high-energy-density micro-lithium ion batteries and communication (antenna/receiver) and control electronics. The resulting independent micropropulsion system produces small amounts of thrust, with potentially limited ability regarding pointing but excellent thrust magnitude control. The challenge is to identify operational modes which allow the satellite to safely deorbit given the restrictions of the system.