Combustion Behavior and Flame Structure of XM46 Liquid Propellant

Chang, Yi-Ping; Boyer, Eric; Kuo, Kenneth K.

doi:10.2514/2.5836

Cited by 27 publications

(6 citation statements)

References 9 publications

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“…[EtSO4] propellant linear burn rate with HANamine propellants [33,35,36] trajectories and maneuvers that would be impossible otherwise [1][2][3][4][5]. The chemical mode is wellsuited for time-sensitive maneuvers, such as orbit insertion, rendezvous or debris avoidance, while the electric mode is useful for long, high ∆ maneuvers such as orbital stationkeeping and interplanetary transfer.…”

Section: Fig 17 Comparison Of 59%han-41%[emim]mentioning

confidence: 99%

“…HAN-fuel mixtures have been extensively studied, first in the context of liquid gun propellant (LGP) research and later as a substitute for hydrazine in space propulsion application. Suitable fuel components, which must be ionic or highly polar to ensure miscibility with HAN, include nitrate salts of aliphatic amines (triethanolammonium nitrate (TEAN) [35] and ethylammonium nitrate (EAN) [33] in particular), zwitterions (amino-acids such as choline [11] and glycine [36]), and alcohols (methanol [34,36]), with water being a frequent additive. Literature results from these studies are presented in Fig.…”

Section: Han-fuel Mixture Burn Ratementioning

confidence: 99%

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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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Section: Fig 17 Comparison Of 59%han-41%[emim]mentioning

confidence: 99%

Section: Han-fuel Mixture Burn Ratementioning

confidence: 99%

Linear burn rate of green ionic liquid multimode monopropellant

Rasmont

Broemmelsiek

Rovey

2020

Combustion and Flame

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“…The lower water content may also facilitate the thermal decomposition since the heat release from the initiation reactions has to vaporize the water and increase the sensible enthalpy of the decomposition products to achieve full ignition, i.e., gas phase combustion. 27 Smaller water concentration reduces the proportion of energy necessary for heating and vaporizing the water allowing for higher reaction temperatures, and thus, an accelerated ignition process.…”

Section: Characterization Of the Thruster Performancementioning

confidence: 99%

A novel electrolytic ignition monopropellant microthruster based on low temperature co-fired ceramic tape technology

Yetter

2009

Lab Chip

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A planar 2-D liquid monopropellant microthruster fabricated from low temperature co-fired ceramic tapes and ignited by electrolysis is reported. The volume of the combustion chamber was 820 nL (0.82 mm(3)). Silver electrodes were screen printed and positioned on the top and bottom surfaces of the combustion chamber. A DC voltage potential applied across the electrodes was used to initiate decomposition of hydroxylammonium nitrate (HAN) based liquid monopropellants. A thrust output of 150 mN was obtained using a voltage input of 45 V. Measured ignition energies were as small as 1.9 J. Ignition delays, as short as a few hundred milliseconds, were found dependent on the type of HAN-based propellant and the voltage potential.

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“…These properties are counterproductive for achieving high-performance EP propellants. Thus, to achieve an ideal MMP propellant, several promising formulations have been considered in the recent literature, including HAN or AN mixed with water, , nitrate salts, zwitterions, , alcohols, and other ILs. , Despite preliminary success of these IL-containing mixtures, even for simple, two-ion “double salt ILs” (DSILs), there remain many gaps in understanding fundamental thermophysical properties and their dependence on ion structure, ion fraction, and ideal or non-ideal mixing behavior. , …”

Section: Introductionmentioning

confidence: 99%

Structural Properties of HEHN- and HAN-Based Ionic Liquid Mixtures: A Polarizable Molecular Dynamics Study

Parmar,

Depew,

Wirz

et al. 2023

J. Phys. Chem. B

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Molecular dynamics simulations of binary mixtures comprising 2-hydroxyethylhydrazinium nitrate (HEHN) and hydroxylammonium nitrate (HAN) were conducted using the polarizable APPLE&P force field to investigate fundamental properties of multimode propulsion (MMP) propellants. Calculated densities as a function of temperature were in good agreement with experiments and similar simulations. The structural properties of neat HEHN and HAN–HEHN provided insights into their inherent, protic nature. Radial distribution functions (RDFs) identified key hydrogen bonding sites located at N–H···O and O–H···O within a first solvation shell of approximately 2 Å. Angular distribution functions further affirmed the relatively strong nature of the hydrogen bonds with nearly linear directionality. The increased hydroxylammonium cation (HA+) mole fraction shows the influence of competitively strong hydrogen bonds on the overall hydrogen bond network. Dominant spatial motifs via three-dimensional distribution functions along with nearly nanosecond-long hydrogen bond lifetimes highlight the local bonding environment that may precede proton transfer reactions.

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Combustion Behavior and Flame Structure of XM46 Liquid Propellant

Cited by 27 publications

References 9 publications

Linear burn rate of green ionic liquid multimode monopropellant

Linear burn rate of green ionic liquid multimode monopropellant

A novel electrolytic ignition monopropellant microthruster based on low temperature co-fired ceramic tape technology

Structural Properties of HEHN- and HAN-Based Ionic Liquid Mixtures: A Polarizable Molecular Dynamics Study

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