Enabling microsatellite maneuverability: A survey of microsatellite propulsion technologies

Legge, Robert S.; Clements, Emily; Shabshelowitz, Adam

doi:10.1109/mwsym.2017.8059082

Cited by 9 publications

(2 citation statements)

References 4 publications

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“…Other important factors for evaluating propulsion system design are the dry mass of the propulsion system elements, the complexity of the system, its compactness and volume, its power consumption, and its safety in terms of propellant toxicity and the level of propellant storage pressurization. Given the total propulsion system volume (V p ), the volumetric impulse measure is the ratio of how much total impulse (I tot ) is delivered per unit volume of the propulsion system [4].…”

Section: Propulsion Performancementioning

confidence: 99%

Propulsion Technologies for CubeSats: Review

Alnaqbi,

Darfilal,

Swei

2024

Aerospace

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This paper explores the wide-ranging topography of micro-propulsion systems that have been flown in different small satellite missions. CubeSats, known for their compact size and affordability, have gained popularity in the realm of space exploration. However, their limited propulsion capabilities have often been a constraint in achieving certain mission objectives. In response to this challenge, space propulsion experts have developed a wide spectrum of miniaturized propulsion systems tailored to CubeSats, each offering distinct advantages. This literature review provides a comprehensive analysis of these micro-propulsion systems, categorizing them into distinct families based on their primary energy sources. The review provides informative graphs illustrating propulsion performance metrics, serving as beneficial resources for mission planners and satellite designers when selecting the most suitable propulsion system for a particular mission requirement.

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Section: Propulsion Performancementioning

confidence: 99%

Propulsion Technologies for CubeSats: Review

Alnaqbi,

Darfilal,

Swei

2024

Aerospace

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“…Third, the CNT fully-printed electron sources could be used as neutralizers in pico and nanosatellite electric propulsion [57]; a summary of key parameters of selected reported pico and nanosatellite electric thrusters is shown in table 4 [58][59][60][61]. For in-orbit manoeuvres, electric propulsion is preferred over chemical propulsion because it uses more efficiently the propellant (the speed of the jet in a chemical rocket is limited by the amount of energy generated by the chemical reaction, while the speed of the beam in an electric rocket can be arbitrarily increased using a suitable bias voltage [62]). Most electric thrusters emit a positive beam to provide thrust to the spacecraft, hence requiring a source of electrons to keep overall charge neutrality; however, in a nanosatellite, the standard hollow cathode technology is not attractive because it consumes propellant at a flow rate comparable (or even larger) than the propellant used to produce thrust.…”

Section: Fowler-nordheim (Fn) Analysis Field Emitted Current Follow T...mentioning

confidence: 99%

Fully 3D-printed carbon nanotube field emission electron sources with in-plane gate electrode

Perales-Martínez

Velásquez–García

2019

Nanotechnology

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We report the design, fabrication, and experimental characterization of the first fully additively manufactured carbon nanotube (CNT) field emission electron sources. The devices are created via direct ink writing (DIW)—one of the least expensive and most versatile additive manufacturing methods, capable of creating monolithic multi-material objects. The devices are 2.5 cm by 2.5 cm glass substrates coated with two imprints, i.e. a trace made of a CNT ink (the emitting electrode), symmetrically surrounded on both sides by a trace made of Ag microparticle ink (the in-plane extractor gate). The CNT ink is a mixture of (–COOH)-functionalized multiwalled CNTs (MWCNTs), N,N-Dimethylformamide, and ethyl cellulose. Optimization of the formulation of the CNT ink resulted in a MWCNT concentration equal to 0.82 wt% and in imprints with an electrical resistivity equal to 0.78 Ω cm. 3D-printed devices having CNT imprints with active length equal to 25 mm (a single, straight trace with 174.5 μm gap between adjacent Ag microparticle imprints) and 135 mm (a square-loop spiral with 499 μm gap between Ag microparticle adjacent imprints) were characterized in a triode configuration (i.e. using an external anode electrode) at ∼2.5 × 10–7 Torr, yielding emission currents as large as 120 μA (60 μA cm−2), start-up voltages as low as 62 V and gate transmission as high as 99%. The low-cost cold cathode technology is compatible with compact applications such as miniaturized mass spectrometry, handheld x-ray generation, and nanosatellite electric propulsion.

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