High-temperature superconductor-based power and propulsion system architectures as enablers for high power missions. (December 2022)

• Record Type: Journal Article
• Authors: Collier-Wright, Marcus; Bögel, Elias; Betancourt, Manuel La Rosa; Herdrich, Georg; Behnke, Alexander; Massuti Ballester, Bartomeu; Große, Veit
• Is Part Of: Acta astronautica. Volume 201(2022)
• Page Start: 198
• Page End: 208
• Publication Date: 2022-12
• Subjects: Electric propulsion -- Superconductors -- Power system -- Spacecraft subsystem; Astronautics -- Periodicals; Outer space -- Exploration -- Periodicals; Astronautics; Periodicals; 629.405
• DOI: 10.1016/j.actaastro.2022.08.035
• Languages: English
• ISSNs: 0094-5765

Abstract

Abstract: The increasing competitiveness of electric propulsion systems (EPS) for primary spacecraft propulsion has paved the way for higher payload mass fractions by offering significantly higher specific impulses than chemical systems. Concurrently, High-Temperature Superconductors (HTS) have reached an unprecedented level of industrial maturity in recent years, and considering their low masses, compactness, and high current densities, they offer the potential to act as a disruptive technology in several spaceflight applications such as power management systems, re-entry and radiation shielding as investigated in the EU-funded MEESST project, as well as EPS. In the latter case, efforts are already ongoing to develop an HTS-enhanced Applied-Field Magnetoplasmadynamic (AF-MPD) thrusters for high power mission applications. The Tsiolkovsky equation infers that the payload mass fraction increases indefinitely with increased Specific Impulse ( I sp ), however, in the case of electric propulsion, the dependence of thrust on the available power complicates this issue when transfer time is a primary driver. Here, the Tsiolkovsky equation becomes inadequate and considering a non-dimensional version of the Tsiolkovsky equation in terms of the mission Δ V and transfer time, the EPS thrust efficiency, and the specific mass of the power system becomes necessary. This paper first discusses the recent advances in HTS and their suitability for spaceflight, before reviewing The development of power system technologies is reviewed and a conceptual power system architecture incorporating HTS is presented. These technologies are analysed using a non-dimensional Tsiolkovsky approach and their impacts on the overall payload mass fraction are assessed. For high-power missions (>100 kW), the use of HTS is shown to have a highly beneficial impact on the mass of the power system. Correspondingly, this enables higher payload mass fractions achievable at increased specific impulse operation, thus strengthening the case for high-power, high- I sp EPS technologies such as AF-MPDT. Highlights: First mass fraction optimisation performed for a superconductor-based spacecraft. Demonstration of potential for increasing mass fraction when using superconductors. AF-MPDT are shown to be a good fit for high power scenarios based on optimum Isp .