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A robust, versatile, and cost-effective propulsion system to provide wide mobility to small satellite platforms and nanosatellite deployers. A Plug&Play propulsion system designed to be easily integrated into different satellite platforms and to match customer's requirements, with minimal customization efforts and costs.

New Space technology for Small Satellites has greatly advanced in the past five years. These progresses shall match with a swift integration and testing phase, to be readily marketable, therefore IOD missions are essential to expedite project outcomes. GAUSS has started working on Small Satellites since 1990s, with its first satellite, UNISAT, launched in 2000. In 2013, UNISAT-5 was the first platform to accomplish in-orbit-release of third-party satellites, with UNISAT-6 following in less than one year. UNISAT-7 is the latest addition to the UNISAT series: a 32kg microsatellite designed and manufactured by GAUSS Srl (a spin-off company of Scuola di Ingegneria Aerospaziale, Sapienza University of Roma), built from scratch thanks to the extensive experience gained with past missions. Launch is scheduled in in Q1 2021. It is the most complex mission ever flown by GAUSS, and it includes several original GAUSS subsystems developed for Earth Observation, sat-to-ground optical links, navigation, power, RF, and Smallsat in-orbit-deployments. All these subsystems are tested in orbit in specific IOD missions. Moreover, UNISAT-7 integrates a precise ADCS solution and a newly developed low-thrust, electric propulsion system named REGULUS, from Italian Company Technology for Propulsion and Innovation (T4i), which will allow the satellite to modify its final orbit, as well as to execute housekeeping maneuvers for drag compensation. REGULUS is a propulsive unit based on MEPT (Magnetically Enhanced Plasma Thruster) technology developed inside the propulsion laboratory of the University of Padua. T4i, born as a Spin-off of the University of Padua, industrialized this technology in order to make it fly. REGULUS is T4i very first product that has ever flown into space. Its envelope is 1.5 U of volume, it is equipped with solid iodine propellant and its main features are a thrust level of 0.55 mN and Isp of 550 s at 50 W of input power, and wet mass of 2.5 kg at 3000 Ns of Itot. REGULUS is designed to serve nanosatellite platforms from 6U to 24U and CubeSat carriers. The integration took place in GAUSS white chamber in Rome in late 2020 and the launch is scheduled in March 2021 from Baikonur as a secondary payload of Soyuz-2-1a/Fregat. Performances of REGULUS propulsion system are evaluated after the initial commissioning of UNISAT-7. This key IOD mission paves the way to next UNISAT programs, where GAUSS microsatellites will be able to execute orbital maneuvers before any single CubeSat deployment, in order to efficiently shape customized constellations by using UNISATs as autonomous vehicles for in-orbit-deployment. Provide an informative abstract of no more than 500 words. The abstract should stand alone as a summary of the paper, not as an introduction (i.e., no numerical references). Type the abstract across both columns and fully justified.

REGULUS is an electric propulsion (EP) system for CubeSats at TRL8 and now waiting for the IoD flight in late 2020. REGULUS system is provided for integration with all electronics, fluidic line, iodine tank and structures for total mass below 3 kg. Thanks in particular to the Magnetically Enhanced RF Plasma Thruster (MEPT) technology and the use of iodine propellant, the system can provide 3000Ns of total impulse in a 93.8 x 95.0 x 150.0 mm volume performance, fitting in a 1.5U Cubesat. REGULUS includes the whole propulsion package for integration in CubeSats and MicroSats as well as small CubeSat carriers. The system is composed by the thruster, the electronics (PPUs and PCU) the fluidic line and the tank. The main features of REGULUS are the presence of a simple architecture, a thruster with no neutralizer and grids, no high DC-voltage PPU and the use of solid iodine as propellant, that can be substituted with Xenon fluidic line and tank when required. Its first mission will be onboard of Unisat-7 by GAUSS. The flight will take place in late 2020 in a Soyuz flight. During the mission, REGULUS will allow Unisat-7 to perform an orbit descending maneuver, drag compensation in VLEO and decommissioning.

We have developed a numerical tool devoted to the design and the optimization of an Helicon plasma source employed in an Helicon Plasma Thruster. Our tool is specifically conceived to model high density (higher than 1^018 m^ 3 ) Helicon plasma sources. The tool is realized coupling ADAMANT, an Electro Magnetic solver which solves for the wave propagation and in turn the power deposition, and OpenFOAM, an open-source C++ library in which we have implemented the fluid transport model. We have developed three versions of the tool, namely 1D-axial, 1D-radial, and 2D-radial-axial. First we have benchmarked our tool against a well-established solver; than we have compared the results given by the three versions of the tool among each other and against a 0D global model for a fixed source configuration. The three models grasp the main features of the Helicon sources and show a better agreement among themselves and with the 0D model in absence of magnetic field.