A comprehensive erosive-burning model for double-base propellants in strong turbulent shear flow

Wu, Xin‐Ping; Kumar, M.; Kuo, Kenneth K.

doi:10.1016/0010-2180(83)90006-8

Cited by 18 publications

(10 citation statements)

References 13 publications

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“…It is found that the threshold velocity is lower for the low-energy propellant than for the high-energy propellant. Wu et al [21] has developed a comprehensive aerothermochemical model of erosive burning of doublebase propellants. They have taken account for both chemical kinetics and diffusion effects in the gas phase.…”

Section: Introductionmentioning

confidence: 99%

Study of Maximum Pressure Rise with Erosive Burning in Multi‐Grain Tubular Solid Propellant

Ropia

Upadhyay

Kalal

et al. 2020

Propellants Explo Pyrotec

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In the present study, the mathematical prediction with the Paul‐Mukunda model is carried out for maximum pressure rise with erosive burning in multi‐grain solid rocket propellant. For this study, a cluster of 7 tubular solid double‐base propellant grains is selected. The erosive burning model has given a fair idea of the maximum pressure rise in rocket motors. The maximum pressure rise due to the erosive burning effect is quite a lot higher than without the erosive burning effect. The erosive burning model helps in studying maximum pressure rise for various configurations of propellant grains. It is found that lowering the outer diameter (OD) of propellant grains is giving low maximum pressure in rocket motor in comparison to increasing the inner diameter (ID) of propellant grains. Ap/At (port area to throat area) ratio is maintained same for both the cases. Although in both the cases predicted maximum flow velocity of propellant gases is almost same. It shows that keeping the same Ap/At ratio and erosive burning effect, the maximum pressure is reduced significantly by lowering OD of propellant grains than increasing the ID of the propellant grains in rocket motor. This study will help to reduce the maximum pressure rise in rocket motors for safe working.

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Section: Introductionmentioning

confidence: 99%

Study of Maximum Pressure Rise with Erosive Burning in Multi‐Grain Tubular Solid Propellant

Ropia

Upadhyay

Kalal

et al. 2020

Propellants Explo Pyrotec

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“…Rocket propellants may be divided into two general classes, double-base propellants and composite propellants. The principle components of the double base propellants are nitrocellulose and an explosive plasticizer, usually nitroglycerin, [6][7][8][9], while the composite propellants are made by embedding a finely divided solid oxidizing agent in a binder. Regarding the latter composite propellant, oxidizing agents which have been used extensively include ammonium nitrate, sodium nitrate, potassium nitrate, ammonium perchlorate, and potassium perchlorate.…”

Section: Introductory Remarksmentioning

confidence: 99%

An Overview of Solid Propellant Combustion Modeling

Hegab

2007

International Conference on Aerospace Sciences and Aviation Tec

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An overview of theoretical and experimental work concerning the burning process in rocket propellant is presented. The current study has emphasized Ammonium Perchlorate (AP) / Hydroxyl Terminated Poly-Butadiance, (HTPB) composites rocket propellant. These propellants are widely used in a variety of rocket systems ranging from small tactical missiles to the large boosters that propel the space shuttle into orbit. A detailed review for the chemical kinetics, numerical and experimental models for the burning of the monomodal, bimodal, and multimodal propellants is introduced. Effects of propellant compositions, time-dependent pressure fluctuations, temperature, fuel-binder types, on the burning rate are reviewed and discussed. The result of the current study shows the effect of pressure and the AP particle sizes on the burning rate, the complex flame structure, and the morphology of the combustion surface.

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“…1 This approach was not adopted in the species is obtained from the chemical equilibrium present study because of the extraordinary code (CEC76).T Detailed procedures are described numerical effort required to solve the evolution in Refs. 4 and 5.…”

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confidence: 99%