Combustion behavior and flame structure of XM46 liquid propellant

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

doi:10.2514/6.2000-706

Cited by 3 publications

(5 citation statements)

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“…glass tube and allowing it to burn down into the tube. The burning rate as a function of pressure up to 18.2 MPa together with the data of a previous study 23 is shown in Fig. 4.…”

Section: Pressure Dependency Of Burning Ratementioning

confidence: 96%

“…To further elucidate the effect of different parameters on the burning-rate pressure exponent, one can write down a simpli ed energy ux balance equation that shows the transition across the control volume from a cold, unburned station to the top of reacting surface 23 :…”

Section: Controlling Mechanisms Of the Burning Rate Of Hangly26mentioning

confidence: 99%

“…In this study, the burning rate curve of HANGLY26 was extended beyond the pressure range reported earlier by Chang et al 23 In addition, the temperaturepro les of the combustionzone were measured at different pressures. The chemical analysis of the recovered liquid residues and the pyrolysis products of both fresh HANGLY26 and glycine were also performed to enhance the understanding of the reaction mechanism of this liquid propellant.…”

Section: Introductionmentioning

confidence: 99%

“…The speci c impulse I sp calculated from experiment data was in the range of 190-195 s. The exhaust plume was clean, and no carbonaceousresidue was found in the catalytic bed. Fundamental strand burner tests of HANGLY26 were performed by Chang et al 23 and compared with that of XM46 (60.8% HAN, 19.2% triethanolammonium nitrate, and 20% water by weight). The burning rate was found to be two orders of magnitude lower than that of XM46, but the ashback behavior of HANGLY26 was observedto be much lessseverethan thatof XM46.…”

Section: Introductionmentioning

confidence: 99%

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Assessment of Combustion Characteristics and Mechanism of Hydroxylammonium Nitrate-Based Liquid Monopropellant

Chang

Kuo

2002

Journal of Propulsion and Power

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The combustion characteristics and reaction mechanism of a HAN-based liquid monopropellant (HANGLY26, consisting of 60% HAN, 14% glycine, and 26% water by weight) were investigated. Combustion tests of liquid strands formed in test tubes were performed in an optically accessible strand burner. Fine-wire thermocouples were also installed in the strand to measure the temperature distribution of the reaction zone. The burning rate of HANGLY26 exhibited four burning rate regimes for pressures ranging from 1.5 to 18.2 MPa. No luminous ame was observed in any combustion tests. The temperatures of combustion products in the test tube were found to be near the water boiling points at pressures below 8.8 MPa. For pressures above 8.8 MPa, the product temperatures were found to be lower than the boiling points of water. Slope break points for burning rate vs pressure were found to coincide with those of concentration curves of recovered residues vs pressure. The observed slope breaks in burning rates are shown to be associated with the reaction mechanism changes between adjacent pressure regimes. Major species detected from the recovered liquid residues are nitrogen, nitric oxide, carbon dioxide, and formaldehyde. The pyrolysis of the fresh unburned liquid propellant was also studied. The results were compared with those of the recovered liquid residues.

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“…glass tube and allowing it to burn down into the tube. The burning rate as a function of pressure up to 18.2 MPa together with the data of a previous study 23 is shown in Fig. 4.…”

Section: Pressure Dependency Of Burning Ratementioning

confidence: 96%

Section: Controlling Mechanisms Of the Burning Rate Of Hangly26mentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Assessment of Combustion Characteristics and Mechanism of Hydroxylammonium Nitrate-Based Liquid Monopropellant

Chang

Kuo

2002

Journal of Propulsion and Power

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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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Viscous Analysis of Pulsating Hydrodynamic Instability and Thermal Coupling in Liquid-Propellant Combustion

Margolis

2001

AIAA Journal

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Combustion behavior and flame structure of XM46 liquid propellant

Cited by 3 publications

References 0 publications

Assessment of Combustion Characteristics and Mechanism of Hydroxylammonium Nitrate-Based Liquid Monopropellant

Assessment of Combustion Characteristics and Mechanism of Hydroxylammonium Nitrate-Based Liquid Monopropellant

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

Viscous Analysis of Pulsating Hydrodynamic Instability and Thermal Coupling in Liquid-Propellant Combustion

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