Assessment of combustion characteristics and mechanism of a HAN-based liquid monopropellant

Chang, Yi-Ping; Kuo, Kenneth K.

doi:10.2514/6.2001-3272

Cited by 10 publications

(7 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The SHP163 composition does not have such a critical pressure and its burning rate is markedly lower than that of the control solution without methanol especially at the operating pressures of RCS thrusters (p < 1.5 MPa). A sudden increase in the linear burning rate was also reported for other HAN-based solutions [3,6,7] but these compositions differed in critical pressure. …”

Section: Burning Ratementioning

confidence: 63%

“…5 MPa. The break point in the curve of the burning rate is associated in [6] with a change in the burning mechanism. In another paper, Chang et al [7] showed that the combustion characteristics of HAN/AN/H 2 O/methanol solutions in the range of 0.74-7.3 MPa were influenced by the content of water and methanol and the pressure dependence of the burning rate also had a break point corresponding to a change in the combustion mechanism.…”

Section: Introductionmentioning

confidence: 99%

“…Chang and Kuo [6] assessed the combustion characteristics and mechanism of a HAN-glycine-water solution at pressures of 1.5-14. 5 MPa.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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

View full text Add to dashboard Cite

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.

show abstract

Section: Burning Ratementioning

confidence: 63%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

View full text Add to dashboard Cite

show abstract

“…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%

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

Izato¹,

Koshi²,

Miyake³

2017

Cent. Eur. J. Energ. Mater.

View full text Add to dashboard Cite

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.

show abstract

“…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

View full text Add to dashboard Cite

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.

show abstract

Assessment of combustion characteristics and mechanism of a HAN-based liquid monopropellant

Cited by 10 publications

References 7 publications

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

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

Decomposition Pathways for Aqueous Hydroxylammonium Nitrate Solutions: a DFT Study

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

Contact Info

Product

Resources

About