Combustion Characteristics of Energetic HAN/Methanol-Based Monopropellants

Chang, Yi-Ping; Josten, Keith; Kuo, Kenneth K.; Reed, Brian D.

doi:10.2514/6.2002-4032

Cited by 17 publications

(7 citation statements)

References 14 publications

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“…The SHP163 composition does not have such a critical pressure and its burning rate is markedly lower than that of the control solution without methanol especially at the operating pressures of RCS thrusters (p < 1.5 MPa). A sudden increase in the linear burning rate was also reported for other HAN-based solutions [3,6,7] but these compositions differed in critical pressure. …”

Section: Burning Ratementioning

confidence: 57%

“…The break point in the curve of the burning rate is associated in [6] with a change in the burning mechanism. In another paper, Chang et al [7] showed that the combustion characteristics of HAN/AN/H 2 O/methanol solutions in the range of 0.74-7.3 MPa were influenced by the content of water and methanol and the pressure dependence of the burning rate also had a break point corresponding to a change in the combustion mechanism.…”

Section: Introductionmentioning

confidence: 97%

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Combustion characteristics of a hydroxylammonium nitrate based liquid propellant. Combustion mechanism and application to thrusters

Katsumi

Kodama

Matsuo

et al. 2009

Combust Explos Shock Waves

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A new composition of hydroxylammonium nitrate based solution containing ammonium nitrate, methanol, and water was developed for monopropellant in a reaction control system (RCS) as an alternative to conventional hydrazine. In comparison with hydrazine, this solution has a 20% higher specific impulse, 1.4 times higher density, and lower freezing point and toxicity. The linear burning rate of the solution is moderate at the operating pressures of RCS thrusters. It was found that the linear burning rate had some characteristics whose mechanisms had not been understood. The combustion mechanism of this solution was investigated. The burning behavior was observed using a medium speed camera, and a temperature profile for the combustion wave was measured with a 2.5 µm diameter thermocouple. From these results, the instability of the liquid-gas interface may trigger a sudden increase in the burning rate, and methanol was found to be effective in reducing the bubble growth rate in the solution. The reactivity of several catalysts was evaluated in an opencup test, and the S405 catalyst for hydrazine showed the best performance among them. Thruster tests were conducted using the S405 catalyst with variation in the propellant mass flow rate, catalyst bed configuration, and length-to-diameter ratio of the combustor. As a result, parameters were determined that ensured long operating time. The model thruster operated stably for up to 100 sec with a specific impulse I sp = 240 sec, which corresponds to a 90% efficiency.

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Section: Burning Ratementioning

confidence: 57%

Section: Introductionmentioning

confidence: 97%

Combustion characteristics of a hydroxylammonium nitrate based liquid propellant. Combustion mechanism and application to thrusters

Katsumi

Kodama

Matsuo

et al. 2009

Combust Explos Shock Waves

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“…propellants [34,36]. Methanol has been found to decrease linear burn rate in HAN-fuel mixtures [37], a result confirmed by Amrousse [34]. The lower burn rate of methanol-based propellants can be explained by the boiling point-burn rate model proposed by Katsumi [29] for HAN-water mixture because methanol lowers the boiling temperature of the propellant [37].…”

Section: Han-fuel Mixture Burn Ratementioning

confidence: 88%

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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“…The main limitation to the development of these as monopropellants has been excessive combustion temperatures. 12,13 Sweden, however, has recently flight tested an ADN-based thruster capable of handling combustion temperatures exceeding 1900 K. 12 T Downloaded by KUNGLIGA TEKNISKA HOGSKOLEN KTH on July 30, 2015 | http://arc.aiaa.org | DOI: 10.2514/6.2012-975…”

Section: Introductionmentioning

confidence: 97%

Dual-Mode Propellant Properties and Performance Analysis of Energetic Ionic Liquids

Berg

Rovey

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Imidazole-based energetic ionic liquids capable of dual-mode chemical monopropellant or bipropellant and electric electrospray rocket propulsion are investigated. A literature review of ionic liquid physical properties is conducted to determine an initial set of ionic liquids that show favorable physical properties for both modes, followed by numerical and analytical performance simulations. Of the ionic liquids considered in this study, [Bmim][dca], [Bmim][NO 3 ], and [Emim][EtSO 4 ] meet or exceed the storability properties of hydrazine and their electrochemical properties are comparable to [Emim][Im], the current state-of-the-art electrospray propellant. Simulations show that these liquids do not perform well as chemical monopropellants, having 10-22% lower specific impulse due to their lack of oxidizing species. The ionic liquids show acceptable bipropellant performance when burned with standard oxidizers, having specific impulse 6-12% lower than monomethylhydrazine and nitrogen tetroxide combination. Considering these ionic liquids as a fuel component in a binary monopropellant mixture with hydroxyl ammonium nitrate shows 1-3% improved specific impulse over some green monopropellants, while retaining a higher molecular weight, reducing the number of electrospray emitters required to produce a given thrust level. More generally, ionic liquids with oxidizing anions perform well as chemical monopropellants while retaining high molecular weight desirable for electrospray propulsion missions. Nomenclature E max= maximum electric field e = fundamental charge F = thrust g o = acceleration of gravity I d = density specific impulse I emit = current flow per emitter I i = output current associated with charged particle emission I sp = specific impulse K = electrical conductivity MW = molecular weight m i = mass of particle i emit m = mass flow rate per emitter tot m = total mass flow rate N emit = number of emitters P c = chamber pressure P e = nozzle exit pressure Q = volume flow rate q = particle charge R = gas constant R A = ion fraction T c = combustion temperature 2 T m = melting temperature V acc = electrostatic acceleration potential V e = exit velocity x i = mass fraction of species i ΔH 0 f = heat of formation δ av = average specific gravity ε = dielectric constant, or nozzle expansion ratio ε o = permittivity of free space γ = ratio of specific heats, or surface tension φ(ε) = proportionality coefficient ρ = density ρ i = density of species i ρ n = density of species n

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Combustion Characteristics of Energetic HAN/Methanol-Based Monopropellants

Cited by 17 publications

References 14 publications

Combustion characteristics of a hydroxylammonium nitrate based liquid propellant. Combustion mechanism and application to thrusters

Combustion characteristics of a hydroxylammonium nitrate based liquid propellant. Combustion mechanism and application to thrusters

Linear burn rate of green ionic liquid multimode monopropellant

Dual-Mode Propellant Properties and Performance Analysis of Energetic Ionic Liquids

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