Experimental Research and Numerical Simulation of Coupling Combustion of Pulsed Jet and AP/HTPB Propellant

doi:10.3969/j.issn.1000-1093.2018.08.007

Abstract

Abstract: An AP/HTPB two-dimensional sandwich combustion model is established to study the oscillating combustion process of AP/HTPB under the action of pulsed jet. A two-step total package reaction is used for the gas phase zone. The effect of pulsed jet is simulated by user defined functions (UDF). In the coupling combustion experiment of AP/HTPB and igniter, the numerical simulation is carried out at the pulse frequency of 125-500 Hz, and the peak value of heat flux is 1.9-3.9 MW/m². The results show that the gas-phase thermal feedback is weak relative to the pulsed jet in the initial stage of oscillating combustion. X component (NH₄ClO₄) is periodically changed because of the leading effect of pulsed jet. After the gas phase temperature rises, the gas phase thermal feedback is stronger than the effect of pulsed jet, the outflow effect is lost, and the AP/HTPB combustion is stabilized. The increase in heat flux density of ignition jet significantly inhibits the oscillating combustion of AP/HTPB, and the increase in ignition jet frequency has weaker inhibitory effect on AP/HTPB oscillating combustion.Key

Key words: compositesolidpropellant, ammoniumperchlorate, hydroxyl-terminatedpolybutadiene, pulsedjet, oscillatingcombustion, couplingcombustion

CLC Number:

V512⁺.3

YE Zhen-wei， YU Yong-gang. Experimental Research and Numerical Simulation of Coupling Combustion of Pulsed Jet and AP/HTPB Propellant[J]. Acta Armamentarii, 2018, 39(8): 1507-1514.

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第39卷
第8期2018 年8月兵工学报ACTA
ARMAMENTARIIVol.39No.8Aug.2018

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