An alternative ADN based monopropellant mixed with tetraglyme

Kim, Ju Won; Baek, Seungkwan; Jung, Yeon Soo; Yoon, Wonjae; Ban, Hong Seop; Kwon, Sejin

doi:10.1016/j.actaastro.2020.09.007

Cited by 12 publications

(3 citation statements)

References 10 publications

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“…This could be due to the promotion of ADN decomposition by H 2 O in the liquid propellant. It is also reported in the Reference [39] that ammonia solution is used as a stabilizer in LMP‐103 to make heat generation more stable.…”

Section: Resultsmentioning

confidence: 96%

Insight into thermal decomposition behavior of ammonium dinitramide‐based liquid propellant through reactive molecular dynamics simulations

Meng,

Zhang,

Guo

et al. 2023

Propellants Explo Pyrotec

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The thermal decomposition characteristics and fuel oxidation mechanism of ammonium dinitramide (ADN)‐based liquid propellant are of great practical significance, but it is difficult to detect the whole intermediates and products using traditional experimental methods. In this paper, the thermal decomposition of ADN‐based liquid propellant at different temperatures (1500, 2000, 2500, and 3000 K) was simulated using the reactive molecular dynamics method. The effect of temperature on the thermal decomposition of propellant and the distribution of the main products were investigated. The results showed that the temperature played a role in promoting the decomposition of propellant. The main products of ADN‐based liquid propellant were N2, H2O, NH3, HNO3, ⋅NHO, CH2O, CO2, and NO2, while their evolution and generation pathways were also described in detail. The initial decomposition of ADN was the breakage of N−H bonds in ⋅NH4 or N−N/N−O bonds in ⋅N(NO2)2, and methanol generated free radicals by dehydrogenation. There was no direct chemical reaction between ADN and methanol, and the interaction was accomplished through the generation and consumption of free radicals. H2O provided a large amount of ⋅H and ⋅HO leading to a lower activation energy of ADN in propellant than that from reference. The overall reaction mechanism of the liquid propellant was deduced. The results would help to further investigate the reaction mechanism of ADN‐based liquid propellants.

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Section: Resultsmentioning

confidence: 96%

Insight into thermal decomposition behavior of ammonium dinitramide‐based liquid propellant through reactive molecular dynamics simulations

Meng,

Zhang,

Guo

et al. 2023

Propellants Explo Pyrotec

View full text Add to dashboard Cite

show abstract

“…We are considering a similar fuel composition to that of LMP-103S for the 1 N monopropellant thruster. Additionally, numerous studies on ADN-based monopropellants have been published by various research groups [12,13,[17][18][19][20][21][22][23][24][25], which helps to set the parameters for thruster development. We can also gain valuable insights that can minimize the time required for development.…”

Section: Introductionmentioning

confidence: 99%

Reactor Structure for the Decomposition of ADN-Based Monopropellant

Yoon,

Bhosale,

Yoon

2023

Aerospace

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Ammonia dinitramide (ADN)-based liquid monopropellants are considered to be environmentally friendly alternatives to the toxic and carcinogenic hydrazine-based propellants. Hence, Space Solutions Co., Ltd. is developing a 1N ADN-based liquid monopropellant thruster by conducting a combustion performance in different types of reactors. Various parameters, such as preheating temperature and the size of thermal and catalyst beds, were examined. The results showed that the decomposition of the propellant in a Pt-LHA catalyst bed, which was used in the Type-1 reactor, resulted in insufficient combustion at low preheating temperatures. Furthermore, increasing the preheating temperature led to partial reaction of the propellant, but resulted in low combustion efficiency due to disintegration of the catalyst. However, when a thermal bed (STS ball) was used in addition to the catalyst bed (Pt-LHA) in the Type-2 and Type-3 reactors, the combustion efficiency was improved, with a minimal pressure drop of 0.2 bar. It was also confirmed that the catalyst was not damaged even after repeated operations. In conclusion, this study suggests that the propellant needs to vaporize before decomposing on the catalyst bed to achieve optimal combustion efficiency.

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“…In the past few decades, traditional hydrazine-based liquid propellants have dominated the space propulsion field [ 1 ]. However, in the long-term use process, many problems such as low specific impulse, flammability and explosion, environmental pollution, biological hazards, expensive launch equipment, and sustainable use have become increasingly prominent [ 2 , 3 , 4 ]. Due to the current global energy shortage and increasingly serious environmental problems, green and high-performance propellants have attracted more and more attention, and at the same time, higher requirements have been placed on the research and development of aerospace propellants [ 5 ].…”

Section: Introductionmentioning

confidence: 99%

Transmissive Mode Laser Micro-Ablation Performance of Ammonium Dinitramide-Based Liquid Propellant for Laser Micro-Thruster

Zheng

Mao

et al. 2023

Micromachines

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The transmissive mode laser micro-ablation performance of near-infrared (NIR) dye-optimized ammonium dinitramide (ADN)-based liquid propellant was investigated in laser plasma propulsion using a pulse YAG laser with 5 ns pulse width and 1064 nm wavelength. Miniature fiber optic near-infrared spectrometer, differential scanning calorimeter (DSC) and high-speed camera were used to study laser energy deposition, thermal analysis of ADN-based liquid propellants and the flow field evolution process, respectively. Experimental results indicate that two important factors, laser energy deposition efficiency and heat release from energetic liquid propellants, obviously affect the ablation performance. The results showed that the best ablation effect of 0.4 mL ADN solution dissolved in 0.6 mL dye solution (40%-AAD) liquid propellant was obtained with the ADN liquid propellant content increasing in the combustion chamber. Furthermore, adding 2% ammonium perchlorate (AP) solid powder gave rise to variations in the ablation volume and energetic properties of propellants, which enhanced the propellant enthalpy variable and burn rate. Based on the AP optimized laser ablation, the optimal single-pulse impulse (I)~9.8 μN·s, specific impulse (Isp)~234.9 s, impulse coupling coefficient (Cm)~62.43 dyne/W and energy factor (η)~71.2% were obtained in 200 µm scale combustion chamber. This work would enable further improvements in the small volume and high integration of liquid propellant laser micro-thruster.

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An alternative ADN based monopropellant mixed with tetraglyme

Cited by 12 publications

References 10 publications

Insight into thermal decomposition behavior of ammonium dinitramide‐based liquid propellant through reactive molecular dynamics simulations

Insight into thermal decomposition behavior of ammonium dinitramide‐based liquid propellant through reactive molecular dynamics simulations

Reactor Structure for the Decomposition of ADN-Based Monopropellant

Transmissive Mode Laser Micro-Ablation Performance of Ammonium Dinitramide-Based Liquid Propellant for Laser Micro-Thruster

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