A model for the combustion and extinction of composite solid propellants during depressurization

Mongia, H. C.; Ambs, L. L.

doi:10.1016/0010-2180(74)90010-8

Cited by 12 publications

(2 citation statements)

References 9 publications

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“…However, several results implicitly contained in .-4 the numerical validations of the bifurcation diagrams (Figs. [50][51][52][53][54][55][56] and numerical simulations of the radiation pulses (Fig. 57-60) confirm the analytical predictions as to the upper dynamic instability and self-sustained oscillatory burning.…”

Section: -Concluding Remarkssupporting

confidence: 58%

Nonlinear Burning Stability of Solid Propellants.

Luca¹,

Riva²,

Zanotti³

1983

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Section: -Concluding Remarkssupporting

confidence: 58%

Nonlinear Burning Stability of Solid Propellants.

Luca¹,

Riva²,

Zanotti³

1983

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“…Thrust termination technology of rocket has been study by United and Russia and used in Minuteman and RT1 Missiles [5]. Mongia [6] and Suhas [7] have investigated the transient burning rate and critical pressure decay rate required to cause extinction of a steadily burning solid propellant subject to sudden depressurization and constructed some mathematical models to predict combustion behavior. Ciepluch [8] and Tahsini [9] have studied effect of rapid pressure decay on a burning, composite solid propellant charge by experimental method and found the relationship between extinguish state and chamber pressure decay rate and initial chamber pressure.…”

Section: Introductionmentioning

confidence: 99%

Rapid Depressurization Burning Behavior Prediction of Base Bleed Propellant Based on BP Neutral Network

Zhang

Zhou

2011

2011 3rd International Workshop on Intelligent Systems and Applications

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Base bleed propellant is an important component of the increasing rang projectile using base bleed technology. Unsteady strongly combustion leads to extinguish, reignition or critical state which produce an effect on rang dispersion. The burning behavior is determined by the initial pressure of combustion chamber and the maximum pressure decay rate, which was investigated by simulation experimental device in this study. A BP neural network prediction model of combustion state related to rapid depressurization was constructed. This prediction model is very easy to give the burning behavior according to the two pressure changing parameters. It is convenient to predict the base bleed unit combustion state at the moment of the projectile flying out of gun muzzle using this model in engineering practice.

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Non-linear analysis of solid propellant burning rate behavior

Wang

2000

Int. J. Numer. Meth. Fluids

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The parametric analysis of the thermal wave model of the non‐steady combustion of solid propellants is carried out under a sudden compression. First, to observe non‐linear effects, solutions are obtained using a computer under prescribed pressure variations. Then, the effects of rearranging the spatial mesh, additional points, and the time step on numerical solutions are evaluated. Finally, the behavior of the thermal wave combustion model is examined under large heat releases (H) and a dynamic factor (β). The numerical predictions show that (1) the effect of a dynamic factor (β), related to the magnitude of dp/dt, on the peak burning rate increases as the value of β increases. However, unsteady burning rate ‘runaway’ does not appear and will return asymptotically to apn, when β≥10.0. The burning rate ‘runaway’ is a numerical difficulty, not a solution to the models. (2) At constant β and m, the amplitude of the burning rate increases with increasing H. However, the increase in the burning rate amplitude is stepwise, and there is no apparent intrinsic instability limit. A damped oscillation of burning rate occurs when the value of H is less. However, when H>1.0, the state of an intrinsically unstable model is composed of repeated, amplitude spikes, i.e. an undamped oscillation occurs. (3) The effect of the time step on the peak burning rate increases as H increases. Copyright © 2000 John Wiley & Sons, Ltd.

show abstract

A model for the combustion and extinction of composite solid propellants during depressurization

Cited by 12 publications

References 9 publications

Nonlinear Burning Stability of Solid Propellants.

Nonlinear Burning Stability of Solid Propellants.

Rapid Depressurization Burning Behavior Prediction of Base Bleed Propellant Based on BP Neutral Network

Non-linear analysis of solid propellant burning rate behavior

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