A mathematical model to predict transient burning rate and pressure decay rates for extinction of composite propellants

Suhas, H.K.; Bose, Tarit K.

doi:10.1016/0010-2180(77)90020-7

Cited by 11 publications

(3 citation statements)

References 12 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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“…one must resort to the flame 79 description method. Zel'dovich et al have shown that their method can be easily extended to incorporate consideration of in-depth radiation absorption.…”

Section: )mentioning

confidence: 99%

Transient Burning of Solid Propellants

1984

Fundamentals of Solid-Propellant Combustion

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Transient burning behavior of solid propellants often occurs under a rapid pressure excursion and is caused by the finite relaxation times required for the solid and/or gas phases to adjust their temperature profiles.The instantaneous burning rate under transient conditions may therefore d i f f e r significantly from the steady-state value corresponding to the instantaneous pressure.The purpose of this chapter is: 1) to report the state-of-the-art on transient burning studies; 2) to explain the detailed mechanism of transient burning; 3) to classify the existing theories to facilitate more direct comparison; 4) to point out the limitations of each model and its general validity; and 5) to summarize the important experimental observations and theoretical results.Various studies indicate that the transient burning e f f e c t is high for higher values of pressurization rates, temperature sensitivity, surface heat release, surface activation energy, and burning rate exponent and lower values of propellant initial temperature and strand burn rate. Nomenclature A = pre-exponential factor in Arrhenius equation a = burning rate constant in steady burning relation, r 0 =a(p) n

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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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A mathematical model to predict transient burning rate and pressure decay rates for extinction of composite propellants

Cited by 11 publications

References 12 publications

Nonlinear Burning Stability of Solid Propellants.

Nonlinear Burning Stability of Solid Propellants.

Transient Burning of Solid Propellants

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

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