Effect of Pulse Triggering on Internal Ballistics and Transient Flow Field Characteristics of Solid Rocket Motor

doi:10.12382/bgxb.2024.0013

Abstract

Abstract:

The effect of pulse triggering on the internal ballistics and transient flow field characteristics of solid rocket motor (SRM) is studied.An internal ballistic model of pulse triggering,a erosion combustion model and a dynamic flow field simulation model are established by numerical calculation method.The transient flow field of solid rocket motor in the process of pulse triggering is simulated.The results show that,the pressure prediction error is less than 5% compared with the experimental result.The pulse triggering increases the velocity of transverse gas flow in the combustion chamber,and the propellant near the pulse end is burning with erosion,which contributes 44% to the pressure rise.When the pulse is triggered,the closer the propellant is to the pulse inlet,the more aggressive the erosive burning is,and the maximum erosion ratio can reach 7.32.The simulated results show that the higher the pulse charge is,the greater the peak pressure is,the higher the pressure rise rate is,and the higher the attenuation rate is after the pulse is terminated.

Key words: solid rocket motor, pulse triggering, erosive burning, flow field simulation

CLC Number:

V435+.11

LU Jiancheng, LI Junwei, ZHANG Wenhao, ZENG Jiajin, NIU Junbo, WANG Ningfei. Effect of Pulse Triggering on Internal Ballistics and Transient Flow Field Characteristics of Solid Rocket Motor[J]. Acta Armamentarii, 2025, 46(1): 240013-.

Figures/Tables 30

Fig.1 Diagram of pulse solid rocket motor

Fig.2 Schematic diagram of pulser

Fig.3 Brass diaphragm after pulser firing test

Table 1 Black powder material parameters[24]

比热比γ	密度ρ_h/ (g·cm^-3)	火药力/ (kJ·kg^-1)	燃温 T_f/K	气体常数 J/(kg·K)
1.28	1.0	291.2	2590	268.12

Fig.4 Schematic diagram of pulse triggering experimental system

Fig.5 Two-dimensional structure diagram of flow field

Fig.6 Simulation calculation process

Fig.7 Flow field grid diagram (120000-order grid)

Fig.8 Simulation pressure comparison of different numbers of grids

Table 2 Simulated peak pressures of different numbers of grids

网络数量级	4万	8万	12万	16万
峰值压强/MPa	10.492	10.451	10.38	10.382

Fig.9 Experimental pressure

Fig.10 Calculated results of internal ballistic of pulser

Fig.11 Comparison of experimental pressure and simulated pressure

Fig.12 Pressure curve for Experiment 2

Fig.13 Comparison of experimental pressure and simulated pressure in Experiment 2

Fig.14 Velocity contour of flow field(20ms)

Fig.15 Local velocity contours of combustion chamber at different times

Fig.16 Local pressure contour (20ms)

Fig.17 Velocity streamlines pattern of combustion chamber

Fig.18 Velocity and pressure distribution on the combustion chamber head cavity axis

Fig.19 Propellant surface pressure and axial velocity curves

Fig.20 Radial velocity distributions at different times (X=70mm)

Fig.21 Propellant surface erosion ratios at different times

Table 3 Working conditions of calculation

算例	1	2	3	4	5	6
脉冲药量/g	3	4	5	6	7	8

Fig.22 Internal ballistic data simulated by pulser

Fig.23 Pressure data at measuring point 1 of pulse charge

Fig.24 Velocity contours with different pulse charges (20ms)

Fig.25 Velocity and pressure distribution on the axis (20ms)

Fig.26 Axial velocity and propellant surface erosion ratio(20ms)

Fig.27 Propellant gas flow at each pulse charge (20ms)

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