Effect of Initial Oxide Layer on Ignition and Combustion of Boron Powder

Ao, Wen; Wang, Yang; Li, Heping; Xi, Jun; Liu, Jianzhong; Zhou, Junhu

doi:10.1002/prep.201300079

Cited by 44 publications

(16 citation statements)

References 21 publications

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“…However, challenges in ignition and combustion lead to the inefficient release of the heat in a limited time 4. The ignition and combustion processes of boron particles have been extensively studied 5. The ignition temperature of boron is high because of its high melting and boiling points, which posts a challenge to its widespread use.…”

Section: Introductionmentioning

confidence: 99%

Preparation and Properties of Boron‐Based Nano‐B/NiO Thermite

Liu

Chen

et al. 2015

Propellants Explo Pyrotec

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Boron particles have several major burning problems, such as incomplete combustion, poor ignitability, and a complex burning process in solid propellants. It is documented that the low ignitability and combustion efficiency of boron are caused by the oxidation of its surface. In order to improve the combustion efficiency of boron particles, a precipitation method was employed to prepare nanometer‐sized NiO and coat it on boron particles. The morphology and coating results of the B/NiO nanocomposite thermite were characterized using different approaches such as SEM, X‐ray Diffraction (XRD), and EDS. The results indicated that the boron particles were well distributed and coated completely by nanocomposite NiO. The B/NiO nanocomposite thermite reaction process was tested by TG‐DTA. The results showed that the reaction temperature of B/NiO particles is about 30 °C lower than that of boron particles. The B/NiO thermite and boron powder were added to Mg/PTFE propellant to be measured for their respective combustion performance. The results showed that the burning rate of the B/NiO‐Mg/PTFE propellant increased by 22.8–25.2 %, mass burning rate by 26.7–30.8 %, and combustion temperature increased by 8–56 °C compared to the B‐Mg/PTFE propellant. The above results indicate that NiO coating of boron particles has a significant effect on the combustion behavior and increases the combustion performance of the propellant compared with uncoated particles.

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Section: Introductionmentioning

confidence: 99%

Preparation and Properties of Boron‐Based Nano‐B/NiO Thermite

Liu

Chen

et al. 2015

Propellants Explo Pyrotec

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“…However, challenges in ignition and self-propagation of the front lead to the inefficient release of the heat in a limited time [1]. The ignition and reaction processes of boron particles have been extensively studied [2]. Boron is considered to be an attractive high-energy metallic fuel for using as a fuel-rich composition because of its high gravimetric (58.28MJ.kg −1 ) and volumetric (136.38 kJ.cm −3 ) caloric value during reaction with oxygen [3].…”

Section: Introductionmentioning

confidence: 99%

Preparation and Properties of Boron-Based Nano-B/CuO Thermite

Liu¹,

Chen²,

Han³

et al. 2016

Kms

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We adopt precipitation to prepare the nanometer CuO and coat it on boron particles of micro-and nano-size. The morphology and coating result of B/CuO nanocomposite thermite were characterized using different techniques, such as scanning electron microscopy, X-ray diffraction, and energy-dispersive X-ray spectroscopy. The results indicated that the boron particles were coated completely by nanocomposite CuO and well distributed. The B/CuO nanocomposite thermite reaction process was tested by thermogravimetric/differential scanning calorimetry. The obtained reaction temperature of B/CuO particles is about 116.86∘ lower than that of boron particles.The B/CuO thermite and boron powder were added to Mg/PTFE propellant to be measured for their respective combustion performance. The results showed that the B/CuO-Mg/PTFE propellant burning rate increased by 12.87%, mass burning rate by 13.48%, and combustion temperature increased by 56.3 ∘ compared to the B-Mg/PTFE propellant. The above results indicate that the CuO coating of boron particles increases the combustion performance of propellant compared with uncoated particles.

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“…A high-power CO 2 laser is often used as a heat source to study the ignition and combustion of boron particles [10,11]. In the present paper, a CO 2 laser with a maximum output of 150 W was used to heat the samples placed in aluminum oxide crucibles and ignited in a pressurized and windowed combustion chamber.…”

Section: Laser Ignition Experimentsmentioning

confidence: 99%

Ignition and Combustion Performance of the Primary Condensed-phase Combustion Products from Boron-based Fuel-rich Propellants

Liu¹,

He²,

Wang³

et al. 2017

Cent. Eur. J. Energ. Mater.

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Abstract:The primary condensed-phase combustion products of a boron-based fuel-rich propellant were ignited using a high-power CO2 laser in a pressurized and windowed combustion chamber under variable pressure. The ignition and combustion performances were characterized using an ultraviolet-visible spectrometer and a high-speed camera. The experimental results showed that the combustion of the condensed-phase combustion products originate from the combustion of carbon, and boron may not take any part in the combustion process because of the formation of a thick boron oxide coating and agglomeration after the primary combustion process. Both particle size and the ingredients play an important role in the combustion reaction of the condensed-phase products. It was observed that a lower particle size and a higher boron carbide content are beneficial for the combustion reaction of the products; higher primary and secondary combustion pressures clearly improved the secondary combustion efficiency of the propellant in the combustion reaction.

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Effect of Initial Oxide Layer on Ignition and Combustion of Boron Powder

Cited by 44 publications

References 21 publications

Preparation and Properties of Boron‐Based Nano‐B/NiO Thermite

Preparation and Properties of Boron‐Based Nano‐B/NiO Thermite

Preparation and Properties of Boron-Based Nano-B/CuO Thermite

Ignition and Combustion Performance of the Primary Condensed-phase Combustion Products from Boron-based Fuel-rich Propellants

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