Numerical studies on erosive burning in cylindrical solid propellant grain

Srinivasan, K.; Narayanan, S.; Sharma, Om P.

doi:10.1007/s00231-007-0280-5

Cited by 14 publications

(7 citation statements)

References 15 publications

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“…Yet they found that for various propellants, the parameters can be close. With the recommended parameters, the expression can be considered universal with good accuracy [13,14].…”

Section: Mukunda-paul Expressionmentioning

confidence: 99%

An Approach to Analysing Erosive Characteristics of Two-Channel Combustion Chambers

Bao

Hui

et al. 2019

International Journal of Aerospace Engineering

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To acquire the erosive characteristics of two-channel combustion chambers, a quasi-one-dimensional internal ballistics model is proposed. Combining the model with two different erosive burning models, the modified L-R expression, and the Mukunda-Paul expression, the flow parameters and the internal ballistics performance of a test solid rocket motor are computed. The results show good agreement with experimental data. According to the results, the more severe the erosion is, the earlier, longer, and gentler the tail-off stage becomes. During the tail-off stage, the dramatic drop of pressure leads to a low normal burning rate and makes it easier for erosion burning to occur. For this reason, notable erosive burning might appear during tail-off if the case-to-throat area ratio is extremely low. The results also show that flows in the inner channel and the outer channel are similar but not identical. This leads to different erosive burning behaviours in the two channels. Also, the two erosive burning rate models involved in this paper are compared. It seems that the M-P expression provides better results than the modified L-R expression does, since it reveals the threshold phenomena. Besides, the M-P expression has great advantages for its universality for most propellants and different SRM geometries.

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“…Yet they found that for various propellants, the parameters can be close. With the recommended parameters, the expression can be considered universal with good accuracy [13,14].…”

Section: Mukunda-paul Expressionmentioning

confidence: 99%

An Approach to Analysing Erosive Characteristics of Two-Channel Combustion Chambers

Bao

Hui

et al. 2019

International Journal of Aerospace Engineering

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“…From the main parameters that affect the erosive burning, decrease the port diameter of the grain by making a modified grain with different port diameter 34, 15, 12.5 and 10 mm respectively to show the effect of the decreased diameter with the same length 108 mm. By decreasing the port diameter the velocity of gases parallel to the burning surface increased, which causes erosive burning in the propellant [9,10], by using composite propellant consist of ammonium Perchlorate (68-70 %) aluminum powder (16-18 %) and binder (13-15 %). This increase in the beginning of the propellant burning is due to using the greater mass of the black powder.…”

Section: Experiments Of 2 Inch Motorsmentioning

confidence: 99%

Parameters Affecting the Erosive Burning of Solid Rocket Motor

2018

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Increasing the velocity of gases inside solid rocket motors with low port-to-throat area ratios, leading to increased occurrence and severity of burning rate augmentation due to flow of propellant products across burning propellant surfaces (erosive burning), erosive burning of high energy composite propellant was investigated to supply rocket motor design criteria and to supplement knowledge of combustion phenomena, pressure, burning rate and high velocity of gases all of these are parameters affect on erosive burning. Investigate the phenomena of the erosive burning by using the 2’inch rocket motor and modified one. Different tests applied to fulfil all the parameters that calculated out from the experiments and by studying the pressure time curve and erosive burning phenomena.

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“…However, when the flow rate of the combustion gas in the propellant grain port exceeds a certain value, it affects the combustion rate of the propellant. This phenomenon is termed "erosive burning" [3]. Such erosion combustion occurs mainly at the initial stage of operation of the rocket motor and occurs more frequently if the pressure and initial temperature of the propellant are higher.…”

Section: Introductionmentioning

confidence: 99%

Properties of Composite Solid Propellants Containing α‐FeOOH

Park

Choi

Park

2020

Propellants Explo Pyrotec

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The initial viscosities of propellants based on yellow iron oxide and red iron oxide were similar. Furthermore, it was confirmed that the thermal decomposition rate of the material to which yellow iron oxide was added was higher than that of the material to which red iron oxide was added; in particular, the pressure index at high pressure was low. From analyzing the combustion properties of the actual test motor, it was concluded that erosion and combustion mainly occur in the initial stage of operation of the rocket motor, and are mitigated due to the low initial pressure in the propellant containing yellow iron oxide. The mechanical properties of the propellant with yellow iron oxide were slightly better compared to those of the propellants with red iron oxide. The analysis revealed that the crystallinity, volatility, thermal decomposition, and mechanical properties of yellow iron oxide were unchanged with natural aging for 10 years. Thus, yellow iron oxide can exhibit the same performance even after prolonged aging for 10 years when applied in a rocket motor.

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Numerical studies on erosive burning in cylindrical solid propellant grain

Cited by 14 publications

References 15 publications

An Approach to Analysing Erosive Characteristics of Two-Channel Combustion Chambers

An Approach to Analysing Erosive Characteristics of Two-Channel Combustion Chambers

Parameters Affecting the Erosive Burning of Solid Rocket Motor

Properties of Composite Solid Propellants Containing α‐FeOOH

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