脉冲触发对固体火箭发动机内弹道和瞬态流场特性的影响

doi:10.12382/bgxb.2024.0013

摘要/Abstract

摘要：

为研究脉冲触发对固体火箭发动机内弹道及瞬态流场特性的影响,利用数值计算方法建立脉冲触发器内弹道模型、发动机侵蚀燃烧模型以及动态流场仿真模型,对固体火箭发动机脉冲触发过程进行瞬态流场仿真。研究结果表明:与实验结果相比,压强预示误差小于5%;脉冲触发使得燃烧室内横向气流速度增大,靠近脉冲端的推进剂发生了侵蚀燃烧,侵蚀燃烧对压强抬升的贡献高达44%;脉冲触发时,越靠近脉冲入口的推进剂受侵蚀燃烧越严重,侵蚀比最大可达7.32;改变脉冲药量研究发现,脉冲药量越大,发动机压强峰值越大,压强抬升率和脉冲结束后的衰减率越大。

关键词: 固体火箭发动机, 脉冲触发, 侵蚀燃烧, 流场仿真

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

中图分类号:

V435+.11

卢健程, 李军伟, 张文昊, 曾佳进, 牛俊博, 王宁飞. 脉冲触发对固体火箭发动机内弹道和瞬态流场特性的影响[J]. 兵工学报, 2025, 46(1): 240013-.

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-.

图/表 30

图1 脉冲发动机图

Fig.1 Diagram of pulse solid rocket motor

图2 脉冲器结构示意图

Fig.2 Schematic diagram of pulser

图3 进行脉冲器点火实验后的黄铜膜片

Fig.3 Brass diaphragm after pulser firing test

表1 黑火药物性参数[24]

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

图4 脉冲触发实验系统图

Fig.4 Schematic diagram of pulse triggering experimental system

图5 流场二维结构示意图

Fig.5 Two-dimensional structure diagram of flow field

图6 仿真计算流程

Fig.6 Simulation calculation process

图7 计算流场网格示意图(12万数量级网格)

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

图8 各数量级网格仿真压强对比

Fig.8 Simulation pressure comparison of different numbers of grids

表2 各数量级网格仿真压强峰值

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

图9 实验压强

Fig.9 Experimental pressure

图10 脉冲器内弹道计算结果

Fig.10 Calculated results of internal ballistic of pulser

图11 实验压强与仿真压强对比

Fig.11 Comparison of experimental pressure and simulated pressure

图12 实验2压强曲线

Fig.12 Pressure curve for Experiment 2

图13 实验2实验压强与仿真压强对比

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

图14 流场速度云图(20ms)

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

图15 不同时刻燃烧室局部速度云图

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

图16 局部压强云图(20ms)

Fig.16 Local pressure contour (20ms)

图17 燃烧室速度流线图

Fig.17 Velocity streamlines pattern of combustion chamber

图18 燃烧室头部空腔轴线上速度与压强分布

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

图19 推进剂表面压强及轴线速度曲线

Fig.19 Propellant surface pressure and axial velocity curves

图20 不同时刻径向速度分布(X=70mm)

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

图21 不同时刻推进剂表面侵蚀比

Fig.21 Propellant surface erosion ratios at different times

表3 计算工况

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

图22 脉冲器模拟内弹道数据

Fig.22 Internal ballistic data simulated by pulser

图23 不同脉冲药量point1处压强数据

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

图24 不同脉冲药量的速度云图(20ms)

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

图25 轴线上速度与压强分布(20ms)

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

图26 轴线上速度与推进剂表面侵蚀比(20ms)

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

图27 各脉冲药量推进剂燃气流量(20ms)

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

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