Chemical analysis of primary combustion products of boron-based fuel-rich propellants

Liu, Linlin; He, Guoqiang; Wang, Yinghong; Hu, Songqi

doi:10.1039/c5ra13693h

Cited by 37 publications

(9 citation statements)

References 23 publications

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“…10 In brief, each propellant pellet (strand) was placed at the bottom of the vessel with one end then ignited by a 12 V electric match. To mitigate the signicant impact of initial temperature on the linear burning rate, 28,29 all samples were ignited at 298 K. The side faces of each pellet were coated with a thin layer of epoxy resin to achieve parallel-layer combustion. Each formulation was measured in triplicate with the average values then used in data analysis.…”

Section: Burning Ratementioning

confidence: 99%

Effects of nitroguanidine on the thermal behavior and burning characteristics of 5-amino-1H-tetrazole-based propellants

Cao

Zhang

et al. 2017

RSC Adv.

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Section: Burning Ratementioning

confidence: 99%

Effects of nitroguanidine on the thermal behavior and burning characteristics of 5-amino-1H-tetrazole-based propellants

Cao

Zhang

et al. 2017

RSC Adv.

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“…Several methods and techniques have been studied to address low inherent regression. Boron improves solid grain regression rate by increasing the radiative heat flux from the diffusion of the fire zone back to the fuel surface [3]. Nanoscale aluminum has the same effect, but it has a much lower ignition temperature due to its high specific surface area, resulting in the energy release being closer to the fuel surface [4].…”

Section: Introductionmentioning

confidence: 99%

Electron spins coupling of coconut shell activated nanocarbons in solid propellant on improving to the thrust stability and specific impulses

Muda

Wardana

Hamidi

et al. 2018

JMES

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The role of activated coconut carbon in the combustion of solid propellant composed by ammonium perchlorate, aluminum, and hydroxyl terminated polybutadiene on improving to the thrust stability and specific impulses have been studied experimentally. Nanocarbons derived from coconut shells produces carbon compounds which dictates electron spin coupling sp2-sp3 when there is an increase in temperature until combustion occurs. Strong nanocarbon bonds require high temperatures and pressures to release bonds and bind oxygen. The results show that activated carbon plays a role in controlling the propellant combustion reaction and reduces thrust fluctuations. But the particle size plays a very decisive role. In micro size the activated carbon becomes a thermal load so thrust power decrease. At nano size the very wide contact area of the activated carbon accelerates the decomposition process to absorb large amounts of energy. While carbon nano as capacitors active side control the combustion reaction so that the exothermic process takes place more gradual and smoother that prolong burning time. As a result, there is an increase in heat flow that amplifies thrust stability and specific impulses.

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“…Amorphous boron (B) is used as a solid propellant and has a very high theoretical calorific value, yet it is not fully understood how this parameter contributes to the outstanding performance of B in practical applications as solid propellant [1]. One of the most critical factors affecting B performance is the generation and evolution of the surface oxide layer during the ignition and combustion processes [2,3].…”

Section: Introductionmentioning

confidence: 99%

Generation and Evolution of Surface Oxide Layer of Amorphous Boron during Thermal Oxidation: A Micro/nanofabricated Slice Measurement

Liang

Liu

et al. 2017

Propellants Explo Pyrotec

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The generation and evolution of the surface oxide layer of boron were thoroughly investigated due to the key role of the oxide layer in ignition and combustion of amorphous boron (B). Samples in different oxidation degrees were obtained by heating B particles until 600, 650, and 700 8C, using a temperature programmed thermobalance. A dual beam focused ion beam micro/nanofabricator was used to etch and cut the samples into thin slices (ca. 327 nm). The slices were observed under a scanning transmission electron microscope, accompanied with energy dispersive X-ray analysis. During the thermal oxidation process, B particles initially lost mass through dehydration. Then they began to get oxidized and gain weight markedly. The sample surface became more rough as the final temperature increased. Two different reaction modes took place in sequence during the thermal oxidation of the samples. Below 650 8C, the oxidation reaction occurred only on the surface of the particle (the surface reaction mode). However, when the samples were heated to 700 8C, the particle in-terior was also involved in the reaction (the global reaction mode), and a large number of pores were formed. The O content of the initial surface oxide layer was fairly high. The thickness distribution was uniform (average thickness 148.1 nm) and the two edges were both smooth. During the heating, the oxygen content of the surface oxide layer increased after an initial decrease. The average oxide layer thickness increased and the thickness distribution became irregular and unequal. The sample heated until 700 8C had an average surface oxide layer thickness of 379.3 nm, and the thickness span reached 354.3 nm. During the global reaction process (700 8C), the oxidation degree within the interior of the particle was lower than that on its surface. In the particle interior, pores near the center were smaller than those close to the edge, whereas the oxidation degree was uniformly distributed. Results in this work provide a deeper understanding of the surface oxide layer, which can potentially help improve the ignition and combustion features of B.Keywords: Amorphous boron · Thermal oxidation · Oxide layer · Slice · Dual beam focused ion beam micro/nanofabrication · Scanning transmission electron microscope · Energy dispersive X-ray spectrometry

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Chemical analysis of primary combustion products of boron-based fuel-rich propellants

Abstract: The content of solid primary products of boron-based fuel-rich propellants could be determined quantitatively through the analysis procedure.

Cited by 37 publications

References 23 publications

Effects of nitroguanidine on the thermal behavior and burning characteristics of 5-amino-1H-tetrazole-based propellants

Effects of nitroguanidine on the thermal behavior and burning characteristics of 5-amino-1H-tetrazole-based propellants

Electron spins coupling of coconut shell activated nanocarbons in solid propellant on improving to the thrust stability and specific impulses

Generation and Evolution of Surface Oxide Layer of Amorphous Boron during Thermal Oxidation: A Micro/nanofabricated Slice Measurement

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