Characterization of Electrospray Thrusters with HAN-Based Monopropellants for Multimode Propulsion Applications

Bruno, Amelia; Schroeder, Madeleine; Lozano, Paulo

doi:10.2514/6.2022-2490

Cited by 4 publications

(1 citation statement)

References 11 publications

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“…This contradiction suggests that the EILs electrospray may be affected by more factors; hence, it is a more complicated and erratic physical process. The group of Lozano et al tested two HAN-based monopropellants, ASCENT and GEM, and concluded that the microthruster firing the above EILs has a higher onset voltage and specific impulse . Despite all, there is an urgent need for detailed investigations to deeply comprehend the intricacies of the passively fed EILs electrospray.…”

Section: Introductionmentioning

confidence: 99%

Multiplexed Electrospray Emission of Green Energetic Ionic Liquids from Wedge-Shaped Porous Emitters

Su,

Yao,

Zhuo

et al. 2023

Energy Fuels

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Section: Introductionmentioning

confidence: 99%

Multiplexed Electrospray Emission of Green Energetic Ionic Liquids from Wedge-Shaped Porous Emitters

Su,

Yao,

Zhuo

et al. 2023

Energy Fuels

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Green Monopropellants: State-of-the-Art

Nosseir,

Cervone,

Amrousse

et al. 2024

Space Technology Library

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Multimodal electrospray thruster for small spacecraft: design and experimental characterization

Mallalieu,

Jugroot

2024

J Electr Propuls

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Electrospray thrusters are a promising electric micropropulsion technology which could be used to meet the propulsion needs of nanosatellites, or for fine attitude control of larger spacecraft. Multimodal propulsion is the integration of two or more propulsion modes into a system which utilizes a common propellant. Indeed, spacecraft mission simulations and models have shown that this type of multimode propulsion capacity is exciting because of the flexibility and adaptability it provides mission designers and planners. A single spacecraft would have potential to execute drastically different mission profiles, and the exact mission could even be determined post-launch. The current paper investigates a micro-propulsion system which combines a droplet and ion mode electrospray emitter into a unified multimodal system (using an ionic liquid as the common propellant for both systems). The high relative thrust droplet mode emitter was fabricated from P3 borosilicate glass while the high efficiency ion mode emitter, Carbon Xerogel dense porous substrate, was fabricated in-house. To characterize the multimodal thruster, a full beam and time-of-flight (ToF) experimental setup were developed at the RMC Advanced Propulsion and Plasma Exploration Laboratory (RAPPEL) and experiments were conducted using a custom vacuum chamber. The ion mode emitter, with a beam comprised purely of ions had an onset voltage around 1400 V with an estimated thrust performance of 0.14 $$\mu N$$ μ N and specific impulse of 4040 s. For droplet mode, with a mixed beam comprised of around 17$$\%$$ % droplets and 83$$\%$$ % ions, an onset voltage of 1375 V with an estimated performance of thrust at 14 $$\mu N$$ μ N and specific impulse of 140 s were measured. The prototype thruster demonstrates how various electrospray emitters could be combined into a multimodal system to provide flexibility and adaptability in providing effective thrust for small satellites.

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Characterization of Electrospray Thrusters with HAN-Based Monopropellants for Multimode Propulsion Applications

Cited by 4 publications

References 11 publications

Multiplexed Electrospray Emission of Green Energetic Ionic Liquids from Wedge-Shaped Porous Emitters

Multiplexed Electrospray Emission of Green Energetic Ionic Liquids from Wedge-Shaped Porous Emitters

Green Monopropellants: State-of-the-Art

Multimodal electrospray thruster for small spacecraft: design and experimental characterization

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