Matthew Robinson, Dr Angelo Grubisic, Dr Federico Romei and Christopher Ogunlesi
Space Propulsion 2018
14/05/18 → 18/05/18
Seville, Spain
Introduction
The potential of an all-electric spacecraft is enhanced by the possibility of a single integrated propellant supply. A common propellant choice is xenon. This creates new performance demands for a high-temperature xenon resistojet, elevating the hot gas temperature requirement to a minimum of 2400 K to achieve 80 s ISP, or 3300 K for 95 s, compared to the current state of the art at 48 s [1]. This represents significant materials and design challenges – beyond the flow kinetics, a major practical challenge facing the high-temperature resistojet technology is retaining structural integrity at the very high operating temperatures, whilst minimizing viscous and radiative heat losses. The University of Southampton has identified a technical solution to this problem and advanced thermofluid multiphysics simulations are currently ongoing as part of a current collaboration with Surrey Satellite Technology Limited (SSTL), alongside an iterative design process and experimental campaign to reach the performance possible from a high-temperature resistojet.
Discussion
This paper presents an experimental campaign on a novel high-temperature resistojet heat exchanger manufactured through selective laser melting (SLM) of 316L stainless steel, to validate the manufacturing approach. The heat exchanger is produced as a single-piece component including an integrated convergent-divergent nozzle, significantly reducing the time and cost of manufacture.
Environmental and endurance testing will be performed on the component, including: thermal cycle life testing; vibration testing; and cleanliness testing. This will allow a comparison between conventionally, and additively manufactured resistojet heat exchangers.
These tests will be combined with a novel process of high-resolution micro-Computed Tomography (μ-CT), applied as a tool for volumetric non-destructive inspection, since the complex geometry of the thruster does not allow internal inspection. The results in this paper will be used in an iterative process to further improve the design of the STAR (Super-high Temperature Additive-manufactured Resistojet). The paper will also include the testing of Inconel and refractory alloys via the same methods.
Conclusion
A high-temperature xenon resistojet is an enabling technology for an all-electric spacecraft. This paper presents an experimental campaign on additive-manufactured prototypes as a precursor to the development of the refractory metal high-temperature thruster. The data presented will be used to validate the design and manufacturing approach, and inform the next stage of development of the STAR.