Experimental and numerical investigations on the decomposition and combustion characteristics of composite propellant with Mg/Al particles additives

Zhu, Min; Chen, Xiong; Zhou, Changsheng; Xu, Jie; Musa, Omer; Xiang, Hengsheng

doi:10.1016/j.applthermaleng.2016.09.140

Cited by 43 publications

(7 citation statements)

References 19 publications

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“…The increase of combustion temperature will promote the mixing of pyrolytic oxidant and propellant gas. This can be seen from some previous studies [48]. Therefore, the propellant sample quickly reaches the thermal decomposition temperature, thus the total time for ignition occurs is reduced, and the final ignition delay time is reduced.…”

Section: Resultssupporting

confidence: 52%

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Zhang

Feng³

et al. 2021

Propellants Explo Pyrotec

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In order to understand the ignition and combustion characteristics of NEPE propellants under different pressure conditions and the agglomeration behavior of aluminum particles on the burning surface, the Al/NEPE propellant was tested on a sealed high-pressure laser ignition platform. Laser ignition experiments show that both ignition delay time and combustion time are inversely proportional to ambient pressure. With the increase of pressure, the reduction of ignition delay time and self-sustaining combustion time is reduced. The impact of pressure on ignition and combustion is very complex. We then analyze the effect of pressure on ignition delay time using a theoretical mechanism. High-speed microscopic images display the agglomeration of aluminum particles in propellants mainly through the following three processes: accumulation, aggregation, and agglomeration. It is also found that many aluminum particles are agglomerated on the surface, the aluminum droplet agglomerates formed on the combustion surface are separated from the combustion surface, and the agglomerates rupture and flow out of the liquid alumina during the combustion process. The phenomenon of secondary agglomeration is also observed. The microstructure and elemental composition of combustion products of aluminum particles in NEPE propellant were obtained by scanning electron microscopy (SEM) and energy dispersive spectrometer (EDS). The detection results confirmed some agglomeration phenomena. At 3.0 MPa, the combustion of the propellant sample is sufficient, and the aluminum particles are smooth spherical alumina particles. At 1.0 MPa, the combustion of the propellant sample is insufficient, and the aluminum particles are rough. The particle size under different pressure was analyzed by a laser particle size analyzer. The results show that increasing the pressure can reduce the average agglomeration size of aluminum particles and improve combustion efficiency. The number of large particle aggregates is more at 3 MPa. From the perspective of overall particle size results, within the same diameter interval, the percentage of particle number does not increase or decrease significantly with the increase of pressure.

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Section: Resultssupporting

confidence: 52%

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Zhang

Feng³

et al. 2021

Propellants Explo Pyrotec

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“…Experiments were carried out on the sealed high-temperature and high-pressure laser ignition platform [16]. The schematic diagram of the experiment system is shown in Figure 1.…”

Section: Methodsmentioning

confidence: 99%

Experimental Investigation on Laser Ignition and Combustion Characteristics of NEPE Propellant

Chen

Zhou

et al. 2017

Prop., Explos., Pyrotech.

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The ignition and combustion property of solid propellant is the main content in internal ballistic research, which has a great significance for propulsion application and combustion mechanism. In this study, the detailed gas‐phase reaction mechanism of Nitrate Ester Plasticized Polyether Propellant (NEPE) was developed. It is helpful to understand the intricate processes of solid‐propellant combustion. The factors which may have influences on ignition delay time and temperature distribution of propellant surface was analyzed by laser ignition experiment. Using high‐speed camera and an infrared thermometer, the ignition and combustion process and the surface temperature distribution of NEPE propellant under laser irradiation were measured. Laser heat flux, ambient pressure and initial temperature of NEPE propellant have an influence on the ignition delay time and the surface temperature. Results show that the ignition delay time decreases with the increase of laser heat flux, ambient pressure and initial temperature of NEPE propellant. At the same time, with the increase of laser heat flux, the influences of ambient pressure and initial temperature on the ignition delay time decrease. Besides, laser irradiation, ambient pressure and initial temperature have significant influences on the surface temperature distribution of the propellant.

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“…The importance of systematic research is also due to the well-known results on the complex effect of aluminum on the regularities of combustion of double-base [2] and composite modified propellants based on ammonium perchlorate [3][4][5] and ammonium nitrate [6]. Sufficient attention has been paid to the influence of AlÀ Mg alloys on the combustion [7][8] and decomposition [9] of composite propellant. In contrast, data for pyrotechnic systems are minimal.…”

Section: Introductionmentioning

confidence: 99%

Combustion Behavior of the Inorganic Nitrates‐Based Compositions. Part II: Effect of Al and Al‐Mg Alloy on Burning Rate

Denisyuk

Tuan

Sizov

2022

Propellants Explo Pyrotec

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The influence of metallic fuel (aluminum and aluminum‐magnesium alloy) on the burning rate of compositions based on inorganic nitrates (KNO3, NaNO3, CsNO3, Ba(NO3)2, Sr(NO3)2) was studied in a wide range of pressure (0.1–18 MPa). Samples have the same binder and differ in basic burning rate and flame temperature. Calculated flame temperature greatly depends on the Al and Al−Mg amount. The effect of metallic fuel on the burning rate of basic samples is complex. It depends not only on the properties of metals but also on the influence of cation nitrate on the burning rate of the basic sample and pressure combustion. Al and Al−Mg alloy have a different effect on the burning rate of the base samples. The efficiency of the metal on the combustion of base compositions is higher for low burning rate samples and samples with an increased oxidizer excess ratio. The lowest positive metal efficiency on the burning rate is observed for the fast‐burning KNO3 and CsNO3‐based compositions. At low pressure, Al−Mg alloy has a more significant effect than Al on the burning rate of the base samples. A slight increase in the burning rate for fast‐burning basic compositions is observed with the addition of a small amount of Al at atmospheric pressure. With a further rise of Al amount in the composition, the burning rate of the metalized sample becomes lower than the basic sample. With pressure growth, the metal effect on the burning rate increases due to a proportional change in the density of the resulting combustion products. As a result, metal combustion was more complete in the zone affecting the increase of burning rate.

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Experimental and numerical investigations on the decomposition and combustion characteristics of composite propellant with Mg/Al particles additives

Cited by 43 publications

References 19 publications

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Experimental Investigation on Combustion Characteristics and Agglomeration of Al/NEPE Propellants

Experimental Investigation on Laser Ignition and Combustion Characteristics of NEPE Propellant

Combustion Behavior of the Inorganic Nitrates‐Based Compositions. Part II: Effect of Al and Al‐Mg Alloy on Burning Rate

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