Combustion features of boron-based composite solid propellants

Глотов, О. Г.; Poryazov, V. A.; Surodin, G. S.; Sorokin, I. V.; Krainov, D. A.

doi:10.1016/j.actaastro.2022.12.024

Cited by 12 publications

(1 citation statement)

References 24 publications

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“…O.G. Glotov et.al [16] studied computed statistics on the heat-ejected efficiency of the rocket fuel evaluated. The experimental data gained has been used to construct and validate theoretical models of metalized fuel combustion.…”

Section: Introductionmentioning

confidence: 99%

Investigation on solid propellant test and time calibration for complete combustion

Tigga,

G.,

P.S.N.

2023

E3S Web Conf.

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A solid propellant is simple and reliable rocket fuel. Once ignited, the propellant cannot be stopped since they burn until they run out. Solid fuel rockets are widely used in military applications such as missiles, model rockets, boosters for satellite launchers and so on because they can be stored for long periods of time without degrading the propellant. The primary objective of this research is to study the burnout mass of solid propellants using various propellants and catalysts. Potassium Nitrate (KNO3) was chosen as an oxidant in the experiment because of its compatibility with other ingredients and low-cost affordability. KNO3 was used as an oxidizer in a 65% ratio with 34% of the fuel and 1% of the catalyst. KNO3, fuel ingredients like Fructose, Glucose and Lactose with catalysts Copper and Aluminum were taken in powdered form. Cylindrical stainless steel with one closed end was taken to fill the cavity, and a concentric hole was made for constant burning. This propellant-filled chamber is fixed strongly in a position so that it does not propel during fuel combustion when thrust is formed. The obtained result shows that the longest burnout mass was secured by burning Glucose with Copper powder and KNO3 for 136 s when compared to the shortest burnout mass was secured by burning Lactose with Aluminum powder and KNO3 mixture to 57 s. The highest temperature of the mixture was Lactose with Copper powder and KNO3 resulted in 518 °C when compared to the lowest temperature of the mixture was Glucose with Copper powder and KNO3 was 211.75 °C.

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Section: Introductionmentioning

confidence: 99%

Investigation on solid propellant test and time calibration for complete combustion

Tigga,

G.,

P.S.N.

2023

E3S Web Conf.

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Preparation and characteristics of boron‐based composite micro‐units encapsulated by potassium perchlorate

Qin,

Liu,

Zeng

et al. 2024

Propellants Explo Pyrotec

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To improve the ignition and combustion performance of boron (B), the B@ potassium perchlorate (KP) composite micro‐units are successfully prepared by recrystallization of solvent evaporation. The morphology and structural composition show that B@KP composite micro‐units are formed by the gentle recrystallization of KP at the heterogeneous interface between B particles and solvents. It is shown by thermal analysis that the initial thermal decomposition temperature of KP is reduced by 49 °C due to the reduction of particle size. In addition, the heat of 420 J/g released by the thermal decomposition of KP is beneficial to the evaporation of the oxide boron (B2O3) film on the surface of B, which reduces the initial oxidation temperature of B by 185 °C and improves the ignition performance of B. Interestingly, the oxygen (O2) released by the thermal decomposition of KP quickly reacts with B to release heat of 3608 J/g, which improves the combustion performance of B. The optimal mass ratio of B to KP is 1: 5, which results in the ignition delay time of 641 ms, a reduction of 19 ms compared to the physical mixed sample. The ignition delay times of other samples are 724 ms, 680 ms and 650 ms respectively, and B could not be ignited successfully. In the combustion process, all samples emit a bright green flame of B combustion, and even a fierce combustion flame like a mushroom cloud appears. In a word, the B@KP composite micro‐units have great potential for application in solid propellants.

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Research on the oxidation process of micro-boron below the melting point temperature

He,

2024

Acta Astronautica

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Combustion features of boron-based composite solid propellants

Cited by 12 publications

References 24 publications

Investigation on solid propellant test and time calibration for complete combustion

Investigation on solid propellant test and time calibration for complete combustion

Preparation and characteristics of boron‐based composite micro‐units encapsulated by potassium perchlorate

Research on the oxidation process of micro-boron below the melting point temperature

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