Technical Report on Hydroxylamine Nitrate

Harlow, Donald G.; Felt, Rowland E.; Agnew, S. F.; Barney, G.S.; McKibben, J.M.; Garber, R.W.; Lewis, Margie

doi:10.2172/1374990

Cited by 23 publications

(19 citation statements)

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“…As such, there have been many experimental and theoretical studies concerning the combustion behaviour of the so-called next generation HAN-based propellants [4][5][6][7][8][9][10][11]. Previous research has demonstrated that some HAN-based solutions exhibit extremely high burning rates, and this property has limited the usefulness of such solutions in certain applications [3][4][5][6] because overly high burning rates can sometimes lead to serious accidents [12][13][14]. Therefore, the development of advanced techniques to control the combustion of HAN-based propellants is essential.…”

Section: Introductionmentioning

confidence: 99%

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

Izato¹,

Koshi²,

Miyake³

2017

Cent. Eur. J. Energ. Mater.

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Hydroxylammmonium nitrate (hydroxylamine nitrate, HAN) is one of the most promising candidates as a replacement for commonly used liquid mono-propellants such as hydrazine. The reaction pathways involved in the initial and the catalytic decomposition of HAN in aqueous solution were determined using quantum chemistry calculations incorporating solvent effects. Optimized structures were obtained for the reactants, products and transition states at the ωB97XD/6-311++G(d,p)/SCRF = (solvent = water) level of theory and the total electron energies of these structures were calculated at the CBS-QB3 level of theory. In the initial decomposition, the ion-neutral NH3OH + -HNO3 reaction, the neutral-neutral NH3O-HNO3 reaction and the HNO3 self-decomposition pathways were all found to have reasonable energy barriers, with values of 91.7 kJ/mol, 88.7 kJ/mol and 89.8 kJ/mol, respectively. The overall reaction resulting from any of these pathways can be written as: HAN → HONO + HNO + H2O. The ionic reaction is dominant during the initial decomposition of HAN in aqueous solution because NH3OH+ and NO3 -are the major species in such solutions. We also developed six catalytic mechanisms and each of these schemes provided the same global reaction: NH2OH + HONO → N2O + 2H2O. The t-ONONO2 oxidizing scheme is the most plausible based on the energy barrier results.

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Section: Introductionmentioning

confidence: 99%

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

Izato¹,

Koshi²,

Miyake³

2017

Cent. Eur. J. Energ. Mater.

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“…However, HAN-based solutions often exhibit extremely high burning rates, which sometimes leads to serious accidents [1]. These problems have hindered the practical use of HAN-based solutions.…”

Section: Introductionmentioning

confidence: 99%

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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“…36) Figure 11 plots the solution energy density as a function of HAN mass concentration. 60 The combustion chamber temperature is calculated using calorically perfect fluid assumptions,…”

Section: Combustion Chamber Enthalpy Balancementioning

confidence: 99%

Development and Testing of a Green Monopropellant Ignition System

Whitmore

Merkley²,

Eilers³

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Green" propellants based on Ionic-liquids (ILs) like Ammonium DiNitramide and Hydroxyl Ammonium Nitrate have recently been developed as reduced-hazard replacements for hydrazine. Compared to hydrazine, ILs offer up to a 50% improvement in available density-specific impulse. These materials present minimal vapor hazard at room temperature, and this property makes IL's potentially advantageous for "ride-share" launch opportunities where hazards introduced by hydrazine servicing are cost-prohibitive. Even though ILs present a reduced hazard compared to hydrazine, in crystalline form they are potentially explosive and are mixed in aqueous solutions to buffer against explosion. Unfortunately, the high water content makes IL-propellants difficult to ignite and currently a reliable "cold-start" capability does not exist. For reliable ignition, IL-propellants catalyst beds must be pre-heated to greater than 350 C before firing. The required preheat power source is substantial and presents a significant disadvantage for SmallSats where power budgets are extremely limited. Design and development of a "micro-hybrid" ignitor designed to act as a "drop-in" replacement for existing IL catalyst beds is presented. The design requires significantly lower input energy and offers a smaller overall form factor. Unlike single-use "squib" pyrotechnic ignitors, the system allows the gas generation cycle to be terminated and reinitiated on demand. Nomenclature= ignitor nozzle exit area, cm 2 A surf = droplet surface area, cm 2 a = Van der Waal parameter, kPa-m 6 /kg-mol 2 B flux = HAN decomposition mass flux, g/s-cm 2 b = Van der Waal parameter, m 3 /kg-mol = ignitor discharge coefficient C p ign = ignitor exhaust products specific heat at constant pressure, J/kg-K = HAN-solution injector discharge area, cm 2 C pc = mean specific heat of gaseous products in chamber, J/kg-K C p HAN = specific heat of pure HAN, J/kg-K C p H2O = specific heat of pure water, J/kg-K = HAN-solution specific heat, J/kg-K D droplet = atomized HAN-solution droplet size, mm f = HAN mass fraction in solution 2 H c = total enthalpy of gaseous products in chamber, J = chamber enthalpy rate, W = enthalpy rate of injected HAN-solution, W = total output enthalpy rate of ignitor, W h ign = specific output enthalpy of ignitor, J/kg L chamber = HAN decomposition length, cm L vap H2O = latent heat of vaporization of water, J/g M HAN = moles of HAN in solution or collected in chamber M H2O = moles of water in solution or collectrd in chamber M ign = moles of ignotor exhaust products collected in chamber M w = generic m,olecular weight term, kg/kg-ml M W HAN = molecular weight of pure HAN, 96.04 kg/kg-mol M W H2O = molecular weight of pure water, 18.02 kg/kg-mol M W HAN/H2O = molecular weight of HAN-solution m c = total fluid mass collected in chamber, g m HAN = total HAN mass collected in chamber, g m ign = total ignitor product mass collected in chamber, g m H2O = total water mass collected in chamber or mass of water in atomozed solution droplet, g = vaporization mass flo...

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Technical Report on Hydroxylamine Nitrate

Cited by 23 publications

References 0 publications

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

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

Development and Testing of a Green Monopropellant Ignition System

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