Consolidation of milli-Newton FEEP Thruster Technology based on Porous Tungsten Multiemitters

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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“…Compared to previous simulation models (e.g. [17]), the space charge density at the point of origin is included.…”

Section: Ion Trajectory Simulation Modelmentioning

confidence: 99%

“…Based on these measurements, Vasiljevich made numerical simulations of ion trajectories and calculated the beam divergence. Here the ions started at 50 µm distance from the needle tip [17].…”

Section: Introductionmentioning

confidence: 99%

IFM Nano Thruster performance studied by experiments and numerical simulations

Mühlich

Seifert

Aumayr

2020

J. Phys. D: Appl. Phys.

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“…formation flight of scientific spacecraft [3]. In order to emit ions at an Isp of up to 5,000 s at a dynamic thrust range from 1 μN to 1 mN, a so called crown emitter is being used, that has been developed by FOTEC for the ESA NGGM mission [4,5,6,7]. This emitter was initially developed to enable fixed formation flight missions and therefore combines a large thrust range with outstanding accuracy (see Figure 1).…”

Section: Introductionmentioning

confidence: 99%

Development of A Low Cost PPU For Feep Electric Propulsion Using Cots Components

et al. 2017

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In the frame of the development of an electric-propulsion thruster for Micro-and Nanosatellites, FOTEC has put forward the in-house development of a low cost PPU, capable of driving the thruster with up to 10 kV emitter and -10 kV extractor voltage. After 5 generations of development, the PPU currently used in a thruster testing and qualification campaign has achieved 85% total efficiency including high voltage multiplier stages and protection circuitry. The PPU includes the functionality of the step-up conversion for emitter and extractor, propellant heating and neutralizer-operation within a volume of 90 x 94 x 78 mm, at a weight of less than 230 g and a total cost in production of less than € 1,000. This low cost approach using COTS components is targeting constellations and mega-constellations and is certainly the other extreme compared to the conventional design approach for spacecraft PPUs. In the light of the ongoing discussions of a change in the philosophy of designing spacecraft, going from fail-safe components to a "mass production" strategy which aims for fail-safety by redundancy. This paper also gives a starting point for the discussion on how a possible tradeoff between cost and reliability can be achieved.

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New materials and processes for field emission ion and electron emitters

Jang

2013

CEAS Space J

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Consolidation of milli-Newton FEEP Thruster Technology based on Porous Tungsten Multiemitters

Cited by 8 publications

References 5 publications

IFM Nano Thruster performance studied by experiments and numerical simulations

IFM Nano Thruster performance studied by experiments and numerical simulations

Development of A Low Cost PPU For Feep Electric Propulsion Using Cots Components

New materials and processes for field emission ion and electron emitters

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