HEMPT-NG addresses the topic COMPET-3-2016-a on Incremental Technologies part of the SRC electrical propulsion in line with the EPIC roadmap “to increase the competitiveness of EP systems developed in Europe” by developing an integrated solution based on HEMPT (Highly Efficient Multistage Plasma Thruster) , the fluidic management system, and the power processing unit. The proposed development will raise the performance of all components beyond current state-of-the-art. The results will offer an ideal EPS system for LEO application up to 700 W and for Telecom/Navigation application up 5 kW. The HEMPT technology offers unique innovative features compared to other EP technologies and makes HEMP a key candidate to overcome all the currently identified deficiencies: 1. No discharge channel erosion leading to higher lifetimes of the thruster, 2. Acceleration voltages enabling a high specific Impulse (ISP) leading to a drastic reduction of propellant consumption, 3. Unique large range of thrust offer enormous flexibility, 4. Minimal complexity of concept providing an excellent basis for economic competitiveness. The HEMPT-NG consortium is led by TES (Thales Electronic System GmbH), subsidiary of the Thales Group, worldwide leader in the development and production of space products, responsible for thruster equipment and integrated EPS. European industrial partners are: Thales, OHB, Airbus and Aerospazio, who bring their expertise in spacecraft mission studies, equipment development and testing capacities. The University of Greifswald will provide plasma simulation to support the thrusters developed. These eight partners in five European member-states (Germany, France, UK, Belgium, Italy) will develop an economical and well-performing HEMPT LEO and GEO EPS to guarantee European leadership and competitiveness, as well as the non-dependence of European capabilities in electric propulsion. This proposal falls under the CONFIDENTIALITY rules described in Section 5.

SALTO will perform, for the first time in Europe, fly / recover / refly cycles of a reusable rocket first stage demonstrator. Operating a large-scale vehicle at low altitude, consistent with future European strategic needs, and embedding a set of critical technologies, the project will significantly boost the strategic launchers roadmap, enabling the vision of a future launch fleet improving by 50% space access costs and reducing environmental impacts. SALTO will hence act as a “stepping stone” towards reusability of strategic launchers in Europe which is one of the key leverages to reach such vision. Fully aligned with previous ESA-funded activities (e.g. Themis initial phase Program), SALTO focuses on - Technologies and building blocks maturation up to TRL5/6 for the first stage of a strategic launcher; - Subsystem/system tests with two low altitude system tests (“hop test”) campaigns. SALTO's methodology will combine robust system engineering with technology maturation activities and a stepped demonstration strategy to accelerate experimental learning through the implementation of the Agile methodology. The SALTO project will culminate in flight test campaigns to demonstrate and validate the technologies necessary for a reusable launch vehicle. SALTO will contribute to the cost reduction target for strategic launcher in Europe by addressing ~3/4 (in cost) of all technologies / operations involved in a future European reusable rocket stage. While Europe is currently lagging behind other global players when it comes to reusable launchers, SALTO will reinforce EU’s independent capacity to access space, secure autonomy of supply for critical technologies and equipment, and foster EU's space sector competitiveness. At the end of the project, lessons will be drawn regarding the maturity of the different technological bricks, TRL and readiness for flight tests. A roadmap to increase their maturity will be prepared in view of suborbital tests by 2025.

MINOTOR’s strategic objective is to demonstrate the feasibility of the ECRA technology as a disruptive game-changer in electric propulsion, and to prepare roadmaps paving the way for the 2nd EPIC call, in close alignment with the overall SRC-EPIC strategy. Based on electron cyclotron resonance (ECR) as the sole ionization and acceleration process, ECRA is a cathodeless thruster with magnetic nozzle, allowing thrust vectoring. It has a considerable advantage in terms of global system cost, where a reduction of at least a factor of 2 is expected, and reliability compared to mature technologies. It is also scalable and can potentially be considered for all electric propulsion applications, from microsatellites to space tugs. Although the first results obtained with ECRA have been encouraging, the complexity of the physics at play has been an obstacle for the understanding and development of the technology. Thus an in-depth numerical and experimental investigation plan has been devised for the project, in order to bring the technology from TRL3 to TRL5. The strong consortium is composed of academic experts to perform the research activities on ECRA, including alternative propellants, along with experienced industrial partners to quantify its disruptive advantages on the propulsion subsystem and its market positioning. ECRA’s advantages as an electric thruster technology can be a disruptive force in a mostly cost-driven satellite market. It would increase European competitiveness, help develop low-cost satellite missions such as constellations, provide end-of-life propulsion, and pave the way for future emerging electric propulsion technologies. The 36 months MINOTOR project requests a total EC grant of 1 485 809 M€ for an experienced consortium of 7 partners from 4 countries: ONERA (FR, Coordinator), industries Thales Alenia Space (BE), Thales Microelectronics (FR), SNECMA (FR), Universities Carlos III (ES) and Giessen (GE), and SME L-up (FR).

CHEOPS proposes to develop three different Hall Effect Thruster electric propulsion systems: a dual mode EPS for GEO applications, a low power for LEO applications and a >20 kW high thrust EPS for exploration applications. Each of these will be developed according to market needs and drivers applying incremental technology changes to existing EPS products. The development approach will follow the ESA ECSS approach and the dual mode and low power are targeting a System PDR review with 42 months from the project start. Development will cover the following elements: thruster, cathode, PPU and FMS. The project is perfectly aligned to the SRC guidelines published with the call. Through a detailed development plan the project will demonstrate their ability to achieve by the end of CHEOPS Phase II (2023) the following: a) TRL7-8 for dual mode and low power b) high power HET EPS TRL6. Common transverse activities will include advanced numerical design tools for electric propulsion which will further the understanding of the observable behaviour and interactions with the satellite platform and predict performances of a given design. This includes alternative propellants and the ability to estimate the system lifetime. Finally significant progress will be made in establishing a HET performances measurement standard and developing advanced non-intrusive tests for measuring thruster erosion. The CHEOPS consortium is led by SNECMA and is comprised of representatives of the biggest European Prime satellite makers, the full EPS supply chain and supported by academia.

To prepare future large satellite missions, replace obsolete networks or introduce new on-board technological advances, Europe must offer to its satellite industry a competitive and highly reliable European dual mode Hall-effect Electric Propulsion System able to provide sufficient power to perform both orbit raising (7kW) and station keeping (3kW) duties. Based on CHEOPS Phase I results, CHEOPS MEDIUM POWER will perform incremental developments on system and sub-system levels in order to achieve TRL6/7 by 2025. CHEOPS MEDIUM POWER will further mature the different system elements (Thruster Unit, PPU, FMS) by addressing the following key challenges: non-recurring and recurring cost reduction in terms of design, manufacturing, test qualification and time to deliver, as well as propellent efficiency in order to increase valuable payload and generate revenues. These advancements will fit into a less than 10kg thruster working between 300 and 450V. CHEOPS MEDIUM POWER will deliver for the thruster unit an optimised design for a very high thrust and improved lifecycle durations. On an industrial level the project aims at reduced fabrication cycles, improved quality, leaner manufacture, faster assembly lead times, and improved tolerance management. The Power processing unit will be optimised by removing unnecessary functions and re-selecting cheaper key components with at least constant reliability levels. The project’s scope extends to FMS level where space qualifiable COTS will be used to provide maximum mission suitability for variable number of thrusters per satellite. CHEOPS MEDIUM POWER will have a medium-term impact on the European space industry and its overall competitiveness, but also on the satellite design and manufacturing paradigm in the long term.