4.6 Article

IFM Nano Thruster performance studied by experiments and numerical simulations

期刊

出版社

IOP Publishing Ltd
DOI: 10.1088/1361-6463/abc84c

关键词

COMSOL multiphysics; divergence angle; electric propulsion; Faraday cup (FC); FEEP thruster; liquid metal ion sources (LMIS); retarding potential analyser (RPA)

资金

  1. Austrian Research Promotion Agency (FFG) [874844]
  2. European Space Agency (ESA) [4000127152/19NL/HB, 4000116898/16/NL/EM]
  3. TU Wien Bibliothek

向作者/读者索取更多资源

Field emission electric propulsion thrusters are ideal for precise spacecraft control due to their low thrust range. Properties of the thruster ion beam and interactions with spacecraft components are crucial for precise control. Experimental analysis and ion trajectory simulations are used to optimize thruster geometries for performance, reliability, and longevity.
Field emission electric propulsion thrusters are characterised by their low thrust range, which makes them ideal for the precise control of spacecraft. Decisive for precise control are the properties of the thruster ion beam, which includes the beam divergence angle and the thrust vector. The analysis of these properties is also necessary in order to be able to estimate the interactions of the beam with components of the spacecraft. Due to such interactions, solar panels or electrical instruments on board the spacecraft could be damaged by sputtering effects. The spatial ion current density and energy distribution of a test crown emitter beam, with different specifications compared to the IFM Nano thruster, were examined experimentally with a diagnostic system, including Faraday cups and a retarding potential analyser. In addition to the analysis of the beam profile of an emitting crown, a single emitting needle was analysed. Based on these experimental analyses, an ion trajectory simulation model was developed to determine the theoretical ion current density distribution. This model includes the properties of a liquid metal ion source, where the ion trajectories start from their point of origin, the so-called Taylor cone jet cap. The benchmark of the model shows that the thrust vector and divergence angle correspond to the experimental results and shows the identical calculations for different thruster parameters, like emission current and electrode voltage. The simulation allows for the optimisation of existing and novel thruster geometries in terms of performance, reliability and longevity.

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