Field-emission electric propulsion
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Field-emission electric propulsion (FEEP) is an advanced electrostatic space propulsion concept, a form of ion thruster, that uses a liquid metal as a propellant – usually either caesium, indium, or mercury.[1]
A FEEP device consists of an emitter and an accelerator electrode. A potential difference of the order of 10 kV is applied between the two, which generates a strong electric field at the tip of the metal surface. The interplay of electric force and the liquid metal's surface tension generates surface instabilities, which give rise to Taylor cones on the liquid surface.[2] At sufficiently high values of the applied field, ions are extracted from the cone tip by field evaporation or similar mechanisms, which then are electrically accelerated to high velocities – typically 100 km/s or more. Although the ion exhaust velocity is high, their mass is very low, resulting in very weak acceleration forces. Their benefit comes from sustained acceleration forces over long time periods.[3]
Due to its very low thrust (in the micronewton (μN) to millinewton (mN) range), FEEP thrusters are primarily used for microradian, micronewton attitude control on spacecraft, such as in the ESA/NASA LISA Pathfinder scientific spacecraft. The FEEP thruster was also slated for installation on Gravity Field and Steady-State Ocean Circulation Explorer spacecraft,[4] but the Gridded ion thruster was used instead.[5] The first FEEP thruster operated in space was the IFM Nano Thruster, successfully commissioned in Low Earth Orbit in 2018.[6]
Basic concept
[edit]Field emission electric propulsion (FEEP) is an electrostatic propulsion method based on field ionization of a liquid metal, and subsequent acceleration of the ions by a strong electric field. Sharp features such as needles are used to enhance and concentrate the strength of this electric field. The needle is coated in the liquid metal, maximising the acceleration of the ions.[7]
FEEP is currently the object of interest in the scientific community, due to its unique features: sub-μN to mN thrust range, near instantaneous switch on/switch off capability, and high-resolution throttleability (better than one part in 104), which enables accurate thrust modulation in both continuous and pulsed modes.[8] Presently baseline for scientific missions onboard drag-free satellites, this propulsion system has also been proposed for attitude control and orbit maintenance on commercial small satellites and constellations.
A separate electron source is required to keep the spacecraft electrically neutral.
Liquid-metal propellants
[edit]This type of thruster can accelerate a large number of different liquid metals or alloys. The best performance (in terms of thrust efficiency and power-to-thrust ratio) can be obtained using high atomic weight alkali metals, such as cesium (Cs, 133 amu) and rubidium (Rb, 85.5 amu). These propellants have a low ionization potential (3.87 eV for Cs and 4.16 eV for Rb), low melting point (28.7 °C for Cs and 38.9 °C for Rb) and very good wetting capabilities.[9]
These features lead to low power losses due to ionization and heating and the capability to use capillary forces for feeding purposes, i.e., neither pressurised tanks nor valves are required. Moreover, alkali metals have the lowest attitude to form ionized droplets or multiply-charged ions, thus leading to the best attainable mass efficiency. The actual thrust is produced by exhausting a beam consisting mainly of singly-ionized cesium or rubidium atoms, produced by field evaporation at the tip of the emitter.
An accelerating electrode (accelerator) is placed directly in front of the emitter. This electrode consists of a metal (usually stainless steel) plate where two sharp blades are machined. When thrust is required, a strong electric field is generated by the application of a high voltage difference between the emitter and the accelerator. Under this condition, the free surface of the liquid metal enters a regime of local instability, due to the combined effects of the electrostatic force and the surface tension. A series of protruding cusps, or "Taylor cones" are thus created. When the electric field reaches a value in the order of 109 V/m, the atoms at the tip of the cusps spontaneously ionize and an ion jet is extracted by the electric field, while the electrons are rejected in the bulk of the liquid. An external source of electrons (neutralizer) provides negative charges to maintain global electrical neutrality of the thruster assembly.
Slit emitter
[edit]Liquid metal ion sources (LMIS) based on field ionization or field evaporation were introduced in the late '60s and quickly became widespread as simple, cheap ion sources for a number of applications, and in 1972 the European Space Agency started development on an electric propulsion system based on the field emission principle using liquid metal ion sources.[10] The use of LMIS operated on gallium, indium, alkali metals or alloys has also been standard practice in secondary ion mass spectrometry (SIMS) since the 1970s.
While there exist different field emitter configurations, such as the needle, the capillary and slit emitter types, the principle of operation is the same in all cases. In the slit emitter, for example, a liquid metal propellant is fed by capillary forces through a narrow channel. The emitter consists of two identical halves made from stainless steel, and clamped or screwed together.[11] A nickel layer, sputter deposited onto one of the emitter halves, outlines the desired channel contour and determines channel height (a.k.a. slit height, typically 1–2 μm) and channel width (a.k.a. slit length, which ranges from 1 mm up to about 7 cm).[11] The channel ends at the emitter tip, formed by sharp edges that are located opposite a negative, or accelerator, electrode, and separated by a small gap (about 0.6 mm) from the emitter tip. An extraction voltage is applied between the two electrodes. The emitter carries a positive potential while the accelerator is at negative potential. The electric field being generated between the emitter and accelerator now acts on the liquid metal propellant.
The narrow slit width not only enables the capillary feed, but, when combined with the sharp channel edges directly opposite the accelerator, also ensures that a high electric field strength is obtained near the slit exit. The liquid metal column, when subjected to this electric field, begins to deform, forming cusps (Taylor cones), which protrude from the surface of the liquid. As the liquid cusps form ever sharper cones due to the action of the electric field, the local electric field strength near these cusps intensifies. Once a local electric field strength of about 109 V/m is reached, electrons are ripped off the metal atoms. These electrons are collected through the liquid metal column by the channel walls, and the positive ions are accelerated away from the liquid through a gap in the negative accelerator electrode by the same electric field that created them.
Slit emitters had been developed to increase the emitting area of the thruster in order to yield higher thrust levels and to avoid the irregular behaviour observed for single emitters. The substantial advantage of slit emitters over stacked needles is in the self-adjusting mechanism governing the formation and redistribution of emission sites on the liquid metal surface according to the operating parameters; in a stacked-needle array, on the contrary, the Taylor cones can only exist on the fixed tips, which pre-configure a geometrical arrangement that can only be consistent with one particular operating condition.
Other designs
[edit]Slit emitters with a wide variety of slit widths have been fabricated; currently, devices with slit widths between 2 mm and 7 cm are available. These devices, spanning a thrust range from 0.1 μN to 2 mN, are operated with cesium or rubidium.
The miniaturized FEEP module design with a crown-shape emitter to fit into the standard CubeSat chassis was reported in 2017.
The single-emitter FEEP design of 0.5 mN is commercially available,[12] and its arrayed version development is nearing completion as in 2018.[13]
References
[edit]- ^ Massotti, L. (2021). The Next Generation Gravity Mission and the qualifcation of the indium‑fed mN‑FEEP thruster. CEAS Space Journal. p. 2.
- ^ Basu, Sourav (2010). An analytical review on electric Propulsion system for space satellites. INCAS. p. 7.
- ^ DeFelice, David (7 December 2004). "NASA - Ion Propulsion: Farther, Faster, Cheaper". www.nasa.gov. Archived from the original on 11 November 2020. Retrieved 3 February 2023.
- ^ FEEP feasibility report (PDF). European Space Agency (ESA) (Report). Archived from the original (PDF) on 14 March 2004. Retrieved 26 September 2018.
- ^ "Gravity field and steady-state Ocean Circulation Explorer (GOCE)" (PDF). European Space Agency (ESA). Archived from the original (PDF) on 14 March 2004. Retrieved 26 September 2018.
- ^ Krejci, David. Demonstration of the IFM nano FEEP thruster in low Earth orbit. ResearchGate (Report). Retrieved 27 March 2019.
- ^ Massotti, L. (2021). The Next Generation Gravity Mission and the qualification of the indium‑fed mN‑FEEP thruster. CEAS Space Journal. p. 7.
- ^ Marcuccio, S.; Genovese, A.; Andrenucci, M. (September–October 1998). "Experimental performance of field emission microthrusters" (PDF). Journal of Propulsion and Power. 14 (5): 774–781. doi:10.2514/2.5340. Archived from the original (PDF) on 20 May 2013.
- ^ Kramida, A. (5 February 2023). "NIST Atomic Spectra Database (ver. 5.10), [Online]". NIST Atomic Spectra Database. Retrieved 5 February 2023.
- ^ Mitterauer, J. (1987). Liquid Metal Ion Soutces as Thrusters for Electric Space Propulsion. Journal de Physique Colloques. p. 173.
- ^ a b Mitterauer, J. (1987). Liquid Metal Ion Soutces as Thrusters for Electric Space Propulsion. Journal de Physique Colloques. p. 172.
- ^ "IFM Nano Thruster for CubeSats €30,000". Cubesat Shop.
- ^ "IFM 350 nano thruster - IOD". European Space Agency (ESA).
External links
[edit]- "FEEP – Field Emission Electric Propulsion". Alta SpA. Archived from the original on 7 July 2011.
- "FEEP thrusters". Nonequilibrium Gas and Plasma Dynamics Group. University of Michigan. Archived from the original on 21 February 2009.
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