Thermal decomposition of han-based liquid propellants

Lee, Hyung Sik; Litzinger, Thomas A.

doi:10.1016/s0010-2180(01)00322-4

Cited by 33 publications

(19 citation statements)

References 26 publications

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“…The energy barrier was calculated to be 80.4 kJ/mol. The resulting HNO is known to decompose to N 2 O and H 2 O in an exothermic reaction [8]. This series can be summarized as a single global reaction:…”

Section: Hono + Nh 2 Oh/nh 3 Oh + Reactionsmentioning

confidence: 99%

“…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].…”

Section: Introductionmentioning

confidence: 99%

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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: Hono + Nh 2 Oh/nh 3 Oh + Reactionsmentioning

confidence: 99%

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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“…Such propellants have been used in liquid propellant guns and electro-thermal chemical guns. A number of researches have been conducted on the ignition and combustion of LP1845 and LP1846 at home and abroad [1][2][3][4][5][6][7][8]. In recent years, micro-miniature chemical thrusters [9,10], which adopt HAN-based liquid propellants, have become a hot topic in the field of spaceflight.…”

Section: Introductionmentioning

confidence: 99%

Study on electrical ignition and micro-explosion properties of HAN-based monopropellant droplet

Yan-huang

et al. 2010

Front. Energy Power Eng. China

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In order to study the electrical ignition characteristics of hydroxylammonium nitrate (HAN)-based liquid propellant, an experimental device for the electrical heating ignition of a liquid propellant droplet was designed. By using a high speed camera system, the ignition properties of the LP1846 single droplet were observed at different electrical heating speeds. The results show that when the LP1846 droplet is electrified, it mainly goes through an evaporization process, a periodic expansion and contraction process, a stronger thermal decomposition process, and an ignition and combustion process. The periodic expansion and contraction process accompanies the droplet micro-explosion phenomenon, and the micro-explosion mechanism is formed mainly due to the overheated water component in LP1846. When peak load voltage is from 80 to 140 V/s, the ignition delay of the LP1846 droplet is linearly shortened from 0.82 to 0.62 s, but the flame is lighter. Based on the above experiments, a simplified model of the electrical heating ignition of the LP1846 single droplet is established.

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“…[1,2] The most currently proposed and studied hydrazine substitutes are energetic aqueous ionic liquids and a representative mixture contains hydroxylammonium nitrate (or NH 3 OH + NO 3 -, HAN) as oxidizer, water and a fuel. [3][4][5] Nevertheless, the use of such mixtures involves more drastic conditions than for hydrazine, due to the high temperature reached during the decomposition (up to 1400°C) and the need of frequent restarts that involve a preheating of the catalyst (300-400°C). Therefore, a high catalytic activity at low temperature (20-200°C) associated with a high thermal stability of shape formed catalysts remain critical parameters for the future development of new engines.…”

mentioning

confidence: 99%

“…These catalysts have been evaluated for the decomposition of HAN/water solutions in a lab-made constant volume batch reactor, [9] and lead to decomposition at very low temperatures, less than 60°C, [10] whereas the thermal decomposition temperature is in the range 115-120°C. [4] Another key point concerns the long-term stability of the catalysts, particularly in the presence of a large amount of propellant.…”

mentioning

confidence: 99%

Facile Catalytic Decomposition at Low Temperature of Energetic Ionic Liquid as Hydrazine Substitute

Courthéoux¹,

Amariei²,

Rossignol³

et al. 2005

Eur J Inorg Chem

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Platinum supported on doped alumina catalysts were prepared and evaluated for the decomposition of NH 3 OHNO 3 / water energetic liquid. Powdered and shaped catalysts remain active after 23 injections at 45°C.Energetic liquid compounds known as monopropellants are used for propulsion and gas generator purposes. For example, the orbit and attitude control of satellites is obtained through small thruster engines using the catalytic decomposition of hydrazine, N 2 H 4 , on supported iridium catalysts. The high toxicity of hydrazine induces high costs and its replacement by a less toxic propellant is of current interest. [1,2] The most currently proposed and studied hydrazine substitutes are energetic aqueous ionic liquids and a representative mixture contains hydroxylammonium nitrate (or NH 3 OH + NO 3 -, HAN) as oxidizer, water and a fuel. [3][4][5] Nevertheless, the use of such mixtures involves more drastic conditions than for hydrazine, due to the high temperature reached during the decomposition (up to 1400°C) and the need of frequent restarts that involve a preheating of the catalyst (300-400°C). Therefore, a high catalytic activity at low temperature (20-200°C) associated with a high thermal stability of shape formed catalysts remain critical parameters for the future development of new engines. Previous studies performed by our group have revealed that platinum supported on thermally stable Si-doped alumina displays a good activity at low temperatures [6,7] The powder or shaped Si-doped alumina (xerogel) are obtained by sol-gel procedure and were demonstrated to be stable at high temperature (1200°C, 5 h); [8] the metallic phase (10 wt.-% Pt) is added by the wet impregnation procedure. These catalysts have been evaluated for the decomposition of HAN/water solutions in a lab-made constant volume batch reactor, [9] and lead to decomposition at very low temperatures, less than 60°C, [10] whereas the thermal decomposition temperature is in the range 115-120°C.[4] Another key point concerns the long-term stability of the catalysts, particularly in the presence of a large amount of propellant.[ In this paper, we present the activity of powdered and shaped (spheres) catalysts for successive HAN/water injections. These successive injections were carried out to simulate the pulse mode of the satellite thrusters. The catalysts (160 mg) are preheated at 45°C during 1 h, then 100 μL (150 mg) of a binary 79 wt.-% HAN/water mixture (i.e. 1.23 mmol) was injected manually 23 times, using a syringe, in the constant volume reactor (167 cm 3 ). Each injection is made after the thermal re-equilibration (approximately 4 min); the number of injections is limited by the pressure gauge and by the size of the sample holder.The evolution of pressure and temperature (catalyst and gas phase) as a function of time during the successive injections using the sphere-shaped catalyst are represented in part a of Figure 1. Each peak corresponds to the decomposition following the injection, with an ignition delay of about 0.5 s; the catalysts ...

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Thermal decomposition of han-based liquid propellants

Cited by 33 publications

References 26 publications

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

Study on electrical ignition and micro-explosion properties of HAN-based monopropellant droplet

Facile Catalytic Decomposition at Low Temperature of Energetic Ionic Liquid as Hydrazine Substitute

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