Combustion Wave Structure of Hydroxylammonium Nitrate Aqueous Solutions

Katsumi, Toshiyuki; Hori, Keiichi; Matsuda, Ryuta; Inoue, T.

doi:10.2514/6.2010-6900

Cited by 17 publications

(10 citation statements)

References 2 publications

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“…Catalyst beds and associated heating systems add significantly to the inert mass of the spacecraft and the highwattage preheat requirement presents a significant disadvantage for small spacecraft where power budgets are extremely limited. Finally, due to very slow reaction kinetics [13] at moderate pressures (2000-3000 kPa) system latencies associated with IL-based propellants are significant for moderate chamber pressures and may limit the usefulness of IL-propellants for reaction control systems.…”

Section: On the Need For Reduced Hazard Spacepropulsion Propellantsmentioning

confidence: 99%

Direct Ignition of a High Performance Hydrogen Peroxide Hybrid Rocket with 3-D Printed Fuel

A¹

2019

Int J Astronaut Aeronautical Eng

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Development of a high-performing hybrid rocket system that employs 90% hydrogen peroxide and 3-D printable thermoplastic materials is reported. Traditionally, high-grade peroxide has been employed as a monopropellant using noble-metal catalysts to initiate thermal decomposition. Catbeds beds are expensive, heavy, and contribute no propulsive mass to the system. Catbeds exhibit limited operational lifetimes, and are often rendered inactive due to the high temperatures of thermal decomposition. The presented alternative thermallydecomposes the injected peroxide stream using an electrostatic ignition system, where as a moderate electric field is introduced to the additively layered ABS fuel grain. Electrostatic arcs are induced within the 3-D printed surface features, and produce sufficient pyrolyzed fuel vapor to induce spontaneous combustion when a flow of gaseous oxygen is introduced. Heat released is sufficient to thermally decompose the injected peroxide stream. The liberated heat and oxygen from decomposition drive full combustion along the length of the fuel grain. Gaseous oxygen pre-leads as small as 250 ms reliably initiate combustion. Multiple on-demand relights are provided with this system. Achieved laboratory specific impulse values exceed 215 s under ambient conditions, with a projected vacuum value exceeding 300 s. Density specific impulse values exceeding 4000 N-s/liter are achievable with this system.

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Section: On the Need For Reduced Hazard Spacepropulsion Propellantsmentioning

confidence: 99%

Direct Ignition of a High Performance Hydrogen Peroxide Hybrid Rocket with 3-D Printed Fuel

A¹

2019

Int J Astronaut Aeronautical Eng

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“…Finally, due to very slow reaction kinetics [16] at moderate pressures (2000-3000 kPa) system latencies associated with IL-based propellants are significant for moderate chamber pressures and may limit the usefulness of IL-propellants for reaction control systems.…”

Section: Introductionmentioning

confidence: 99%

Advantages of Using Additive Manufacturing to Build "Green" Fuels for Hybrid Propulsion

A¹

2017

Int J Astronaut Aeronautical Eng

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Unfortunately, hydrazine is a powerful reducing agent that poses serious biological and environmental concerns. Hydrazine is extremely destructive to living tissues, and is a known human carcinogen. The US Environmental Protection Agency (EPA) classifies hydrazine as "highly toxic". Hydrazine possesses a high vapor pressure and boils readily at room temperature. Thus, there exists significant risk of respiratory contamination and special servicing procedures that employ full-pressure Self-Contained Atmospheric Protective Ensemble (SCAPE) suits are required [3]. Although procedures are in place to allow hydrazine to be managed safely on tightly controlled military reservations and at government-operated launch facil

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“…Multiple researchers including 1) Lee and Litzinger, 61 2) Pan et al, 62 3) Vosen, 63 4) Kondrikov et al, 64 and 5) Katsumi and Hori 65 have studied the decomposition rates for aqueous HAN-solutions and HAN-based propellant solutions. There is considerable disagreement amongst the published results; however, there exists a general consensus that high pressures exhibit a suppressing effect on the HAN solution decomposition rates for pressures above 10 MPa.…”

Section: N Han Solution Decomposition Ratesmentioning

confidence: 98%

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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Combustion Wave Structure of Hydroxylammonium Nitrate Aqueous Solutions

Cited by 17 publications

References 2 publications

Direct Ignition of a High Performance Hydrogen Peroxide Hybrid Rocket with 3-D Printed Fuel

Direct Ignition of a High Performance Hydrogen Peroxide Hybrid Rocket with 3-D Printed Fuel

Advantages of Using Additive Manufacturing to Build "Green" Fuels for Hybrid Propulsion

Development and Testing of a Green Monopropellant Ignition System

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