Catalyzed Ignition of Using Methane/Hydrogen Fuel in a Microtube for Microthruster Applications

Mento, Christopher; Sung, Chih-Jen; Ibarreta, Alfonso F.; Schneider, Steven J.

doi:10.2514/1.42592

Cited by 10 publications

(5 citation statements)

References 20 publications

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“…One type is the chemical microtube. [18][19][20] This type of thruster is simply a heated tube of diameter ~1 mm or less that may or may not consist of a catalytic surface material. Additionally, and ideally from a multi-mode system standpoint, there is no fundamental reason why this geometry could not be shared with the electrospray mode as capillary type emitters can be roughly the same diameter tube.…”

Section: Introductionmentioning

confidence: 99%

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: Introductionmentioning

confidence: 99%

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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“…Rhenium was found from the previous study to be a good candidate catalyst material. 9 Platinum was the material selected for the previous microtube thruster experiments [10][11][12] and is also a candidate for HAN propellant catalyst applications. 15 Titanium is selected for this study to provide a measure of thermal decomposition absent catalytic activity since it is known to be compatible with HAN propellants for long term storage.…”

Section: Methodsmentioning

confidence: 99%

“…8 , have been previously synthesized and assessed for thermal and catalytic decomposition in a microreactor. 9 This paper presents results of further experiments to characterize the decomposition of the [Emim][EtSO 4 ]-HAN monopropellant, specifically on catalytic surfaces relevant to application in a microtube thruster [10][11][12] or similar geometry such as channels in a monolith catalyst. The electrospray capabilities of the propellants have been investigated previously.…”

Section: Introductionmentioning

confidence: 99%

“…One type is the chemical microtube. [10][11][12] This type of thruster is simply a heated tube of diameter ~1 mm or less that may or may not consist of a catalytic surface material. Additionally, from a multi-mode system standpoint, there is no fundamental reason why this geometry could not be shared with the electrospray mode as capillary type emitters can be roughly the same diameter tube.…”

Section: Introductionmentioning

confidence: 99%

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Decomposition of a Double Salt Ionic Liquid Monopropellant on Heated Metallic Surfaces

Berg

Rovey

2016

52nd AIAA/SAE/ASEE Joint Propulsion Conference

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A monopropellant consisting of 59% hydroxylammonium nitrate and 41% 1-ethyl-3methylimidazolium ethyl sulfate by mass is tested for decomposition on heated platinum, rhenium, and titanium surfaces. It was found that the propellant decomposes at 165 o C on titanium, which is the decomposition temperature of HAN. The onset temperature for decomposition on platinum was 85 o C and on rhenium it was 125 o C. This suggests that platinum and rhenium act as catalysts for the decomposition of the monopropellant. From the experimental data, Arrhenius-type reaction rate parameters were calculated. The activation energy for platinum was 3 times less than that of titanium suggesting it could be a prime choice for catalyst material in further thruster development.

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“…26,27 Many different chemical propulsion systems have also been proposed, including a chemical microtube. [28][29][30] This propulsion system utilizes a heated tube with a typical diameter of 1 mm or less that could consist of a catalytic surface material. Additionally capillary type emitters used for an electrospray propulsion system can be roughly the same diameter tube, and there is therefore no fundamental reason why this geometry could not be shared within a multi-mode propulsive system.…”

Section: Introductionmentioning

confidence: 99%

Linear Burn Rate of Monopropellant for Multi-Mode Micropropulsion

Mundahl

Rovey

Berg

2018

2018 Joint Propulsion Conference

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Multi-mode micropropulsion is a potential game-changing technology enabling rapidly composable small satellites with unprecedented mission flexibility. Maximum mission flexibility requires propellant that is shared between the chemical and electric propulsion systems. Previous research has identified a promising monopropellant that is both readily catalytically exothermically decomposed (chemical mode) and electrosprayable (electric mode). In this work the linear burn rate of this monopropellant is determined to aid design of the microtube catalytic chemical thruster. A pressurized fixed volume reactor is used to determine the linear burn rate. Benchmark experiments use a 13 molar mixture of hydroxylammonium nitrate and water, and show agreement to within 5% of literature data. The multi-mode monopropellant is a double-salt ionic liquid consisting of 41% 1-ethyl-3methylimidazolium ethyl sulfate and 59% hydroxylammonium nitrate by mass. At the design pressure of 1.5 MPa the linear burn rate of this propellant used for designing the muli-mode propulsion system is 22.8 mm/s. Based on this result, the minimum flow rate required is 0.25 mg/s for a feed tube with a 0.1 mm inner diameter and 2500 mg/s for a feed tube with a 10 mm inner diameter. Nomenclature = linear burn rate Δ = change in position Δ = change in time = cross-sectional area of propellant container = mass of propellant used = density of propellant used

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Catalyzed Ignition of Using Methane/Hydrogen Fuel in a Microtube for Microthruster Applications

Cited by 10 publications

References 20 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

Decomposition of a Double Salt Ionic Liquid Monopropellant on Heated Metallic Surfaces

Linear Burn Rate of Monopropellant for Multi-Mode Micropropulsion

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