Decomposition of a Double Salt Ionic Liquid Monopropellant in a Microtube for Multi-Mode Micropropulsion Applications

Berg, Steven P.; Rovey, Joshua L.

doi:10.2514/6.2017-4755

Cited by 15 publications

(5 citation statements)

References 24 publications

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“…These values are higher than the specific impulse predicted for the chemical propulsion mode (~180 seconds). 13 Although the highest specific impulse measured in this study is 412 seconds, this number could likely be improved through optimized thruster and feed system design. In order to gauge what might be possible, scaling laws can be used to extrapolate the data garnered in this study to possible specific impulse and thrust values.…”

Section: =̇0mentioning

confidence: 83%

“…The electrospray thruster experiment utilized to characterize electrospray performance is a well-characterized experiment that is currently in use at AFRL Kirtland 27,28 . The experiment consists of a capillary emitter electrospray source, which is effectively the same geometry as the chemical thruster microtube, Figure 1a, 13 but with a voltage applied between the needle tip and an extractor grid, Figure 1b. In order to characterize the performance of the electrospray emission mode, knowledge of the beam current and mass flow rate is required.…”

Section: Methodsmentioning

confidence: 99%

“…1 (1) where the length and diameter of the capillary and transport capillary are given in the previous section and the viscosity of the liquid propellant is 130 cP as found in a previous experiment. 13 The flow rate range achieved by the feed system is similar to that conducted for electrospray [Bmim][dca] in a capillary emitter. 27…”

Section: A Flow Rate Calibration-bubble Methodsmentioning

confidence: 99%

“…In a separate paper, the decomposition and performance of this propellant in the chemical, high-thrust mode thruster has been investigated. 13 Recent efforts have placed a greater emphasis on smaller spacecraft, specifically microsatellites (10-100 kg) and nanosatellites (1-10 kg), including the subset of cubesats. 14 Many different types of thrusters have been proposed to meet the stringent mass and volume requirements placed on spacecraft of this type.…”

Section: Introductionmentioning

confidence: 99%

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Electrospray of an Energetic Ionic Liquid Monopropellant for Multi-Mode Micropropulsion Applications

Berg¹,

Rovey²,

Prince³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

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The multi-mode chemical-electric propulsion capable energetic ionic liquid propellant [Emim][EtSO 4 ]-HAN is electrosprayed in a 100 μm capillary emitter to test the electricmode performance of the propellant. The ionic liquid exhibits stable electrospray emission in both cation and anion extraction modes at a nominal extraction voltage of 3400 V. Near field measurements of current and mass flow rate distribution are taken at flow rates from 0.19 nL/s to 3.06 nL/s. Total emission current, as measured by Faraday cup and integrated, increases from 754 nA to 3195 nA for cation emission and from 552 nA to 2012 nA for anion emission. The thrust and specific impulse at 0.19 nL/s flow rate is 1.08 μN and 412 seconds, respectively, with a beam power of 2.22 mW. At 3.06 nL/s, the thrust is 8.71 μN and the specific impulse is 204 seconds with a beam power of 8.85 mW. Extrapolation of the current data shows that specific impulse in excess of 1000 seconds is achievable through optimized feed system and emitter design.

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Section: =̇0mentioning

confidence: 83%

Section: Methodsmentioning

confidence: 99%

Section: A Flow Rate Calibration-bubble Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Electrospray of an Energetic Ionic Liquid Monopropellant for Multi-Mode Micropropulsion Applications

Berg¹,

Rovey²,

Prince³

et al. 2015

51st AIAA/SAE/ASEE Joint Propulsion Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…Following each test, the combustion gases are vented outside of the laboratory and the experiment can be repeated. [11,16], because it is more reliable and can be used with larger batches. The The standard error of the burn rate is calculated using equation 1, which is the definition of the error of the slope of a linear regression, assuming normally distributed error terms on the position datapoints.…”

Section: List Of Tablesmentioning

confidence: 99%

Linear burn rate of green ionic liquid multimode monopropellant

Rasmont

Broemmelsiek

Rovey

2020

Combustion and Flame

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Multimode space propulsion systems are being proposed that integrate high specific impulse electric propulsion and high thrust chemical propulsion. The most important attribute of this concept is a shared propellant capable of both modes of propulsion, which enables mission flexibility. One promising approach is a catalytic monopropellant thruster paired with an electrospray electric thruster. Previous research has identified a green double-salt ionic liquid consisting of 41% wt. 1-ethyl-3-methylimidazolium ethyl sulfate and 59% wt. hydroxylammonium nitrate as a promising propellant candidate. In this work, the burn rate of this monopropellant is measured through pressure-based and high-speed imaging methods in a fixedvolume chamber pressurized across a pressure range from 0.5 to 10 MPa. Its performance is benchmarked by 80% wt. hydroxylammonium nitrate-water and nitromethane propellants. The burn rate of the multimode monopropellant is found to follow an exponential law given by = 5.35 1.11 between 0.5 and 3 MPa and is approximately constant at 142 ± 29 mm/s between 3 and 10 MPa. This work was published during the AIAA Propulsion and Energy 2019 Forum:

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Dual-mode propulsion systems for SmallSats

Rovey,

Koizumi

2023

Next Generation CubeSats and SmallSats

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Decomposition of a Double Salt Ionic Liquid Monopropellant in a Microtube for Multi-Mode Micropropulsion Applications

Cited by 15 publications

References 24 publications

Electrospray of an Energetic Ionic Liquid Monopropellant for Multi-Mode Micropropulsion Applications

Electrospray of an Energetic Ionic Liquid Monopropellant for Multi-Mode Micropropulsion Applications

Linear burn rate of green ionic liquid multimode monopropellant

Dual-mode propulsion systems for SmallSats

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