触发激励下固体火箭发动机声腔特性实验

doi:10.12382/bgxb.2024.0162

摘要/Abstract

摘要：

为研究外部激励对固体火箭发动机稳定性的影响,搭建脉冲触发下固体火箭发动机声腔特性模型实验系统,开展固体火箭发动机轴向和径向空腔激励实验,分析节流孔径和触发方式对声腔振幅和衰减系数的影响。喉部节流工况下燃烧室中激发6阶以上轴向振荡,获取了各阶振荡固有频率和衰减系数。研究结果表明:利用互相关分析测得燃烧室声速接近604.2m/s,基于实测声速的频率预示误差为10.1%;振荡按衰减快慢可划分为两个阶段,脉冲器输入发动机压力振荡频率及发动机各阶模态振荡幅值均随节流孔径增大而增大,同时第1阶段衰减变快,而第2阶段衰减变慢,第1阶段在燃烧室头部轴向激励产生的振荡衰减快于径向激励,非线性特征更强。

关键词: 固体火箭发动机, 固有频率, 衰减系数, 脉冲触发, 互相关分析

Abstract:

In order to study the influence of external excitation on the stability of solid rocket motor,an experimental model system for the acoustic property of solid rocket motor is built,and the axial and radial excitation experiments of solid rocket motor are carried out.The influences of throttle aperture and trigger mode on the experimental results are studied.The natural frequency and attenuation coefficient of each order oscillation are obtained.The acoustic speed in the combustion chamber measured by cross-correlation analysis is 604.2m/s,and the frequency error predicated upon the measured acoustic speed is 10.1%.The oscillation of the system can be divided into two stages according to the attenuation speed.When the throttling aperture increases,the frequency of pressure oscillation input into the motor by a pulser and the oscillation amplitude of each mode increase,and the first-stage attenuation becomes faster,while the second-stage attenuation becomes slower.The oscillation attenuation of the axial excitation is faster than that of the radial excitation on the combustion chamber head in the first stage,and it has stronger nonlinear characteristics.

Key words: solid rocket motor, natural frequency, attenuation coefficient, pulse triggering, cross-correlation analysis

中图分类号:

TJ301

曾佳进, 李军伟, 李强, 李涛, 张文昊, 卢健程, 王宁飞. 触发激励下固体火箭发动机声腔特性实验[J]. 兵工学报, 2025, 46(2): 240162-.

ZENG Jiajin, LI Junwei, LI Qiang, LI Tao, ZHANG Wenhao, LU Jiancheng, WANG Ningfei. Experimental Study on Acoustic Property of Solid Rocket Motor under Pulse Triggering[J]. Acta Armamentarii, 2025, 46(2): 240162-.

图/表 21

图1 固体火箭发动机声腔特性实验系统

Fig.1 Experimental setup of radial excitation of solid rocket motor

图2 发动机与脉冲器的装配图(单位:mm)

Fig.2 Assembly drawing of motor and pulser (Unit:mm)

图3 脉冲触发器

Fig.3 Pulse trigger

图4 触发激励实验系统实物

Fig.4 Physical diagram of trigger excitation experimental system

表1 实验工况

Table 1 Test cases

工况	激励方式	药量/g	孔径/mm	脉冲器压力/MPa
1	径向	5	5	52.0
2	轴向	5	6	53.0
3	轴向	5	6	51.6
4	轴向	5	4	51.0

图5 测点P1~P4压力信号比较

Fig.5 Comparison of pressure signals at measuring points P1~P4

图6 径向激励下测点P3和P4互相关分析

Fig.6 Cross-correlation analysis of measuring points P3 and P4 under radial excitation

图7 发动机声腔频率特性

Fig.7 Frequency characteristics of acoustic cavity in solid rocket motor

表2 发动机内振荡模态实测频率

Table 2 The mode frequency of oscillation in the motor

模态	测点P₃		测点P₄
模态	频率/Hz	PSD	频率/Hz	PSD
1	475	0.0240	487	0.02620
2	962	0.0100	937	0.01140
3	1462	0.0062	1462	0.01190
4	1950	0.0058	1975	0.00690
5	2450	0.0051	2387	0.00338
6	2925	0.0038

图8 1阶特征频率仿真结果

Fig.8 Simulated results of the first-order eigenfrequency

图9 燃烧室和喷管入口振荡信号和衰减系数拟合

Fig.9 Oscillation signals and attenuation coefficients at combustion chamber head and nozzle inlet

图10 各阶模态衰减曲线及其拟合

Fig.10 Modal attenuation curves of all orders and their fitting

图11 径向激励实验中各阶模态衰减系数和振荡幅值

Fig.11 Attenuation coefficient and oscillation amplitude of each mode in radial excitation experiment

图12 不同节流孔径下测点P2时频曲线

Fig.12 Time-frequency curves at measuring point 2 under different throttling apertures

图13 轴向激励实验中压力振荡

Fig.13 Pressure oscillation curve in axial excitation experiment

图14 功率谱密度对比

Fig.14 Comparison of power spectral densities

图15 轴向激励实验各阶衰减系数与幅值对比

Fig.15 Attenuation coefficient and oscillation amplitude of each order in the axial excitation experiment

表3 第1阶段的衰减系数与衰减幅值比例

Table 3 The ratio of attenuation coefficient to attenuation amplitude in the first stage

测点	工况	触发方向	孔径/mm	p'_max/MPa	α₁/(s^-1)	R₁	Δp'/%	Δt/ms
P₃	2	轴向	6	1.21	-379.37	0.9914	79.00	4.10
	1	径向	5	0.81	-270.26	0.9955	67.26	4.13
	4	轴向	4	0.30	-323.16	0.9781	72.60	4
P₄	2	轴向	6	1.73	-631.67	0.9851	89.01	3.53
	1	径向	5	1.07	-442.28	0.9624	80.16	3.54
	4	轴向	4	0.42	-430.96	0.982	78.00	3.45

表4 第2阶段的衰减系数与衰减幅值比例

Table 4 The ratio of attenuation coefficient to attenuation amplitude in the second stage

测点	工况	触发方向	孔径/mm	α₂/(s^-1)	R₂	Δp'/%	Δt/ms
P₃	2	轴向	6	-58.6	0.9760	92.77	36.66
	1	径向	5	-66.43	0.9950	91.90	36.80
	4	轴向	4	-78.51	0.9790	92.10	36.30
P₄	2	轴向	6	-59.50	0.9703	90.41	36.88
	1	径向	5	-67.43	0.9968	91.91	36.96
	4	轴向	4	-73.09	0.9813	88.42	36.50

图16 压力最大振幅与节流孔径关系

Fig.16 Relationship between maximum pressure oscillation amplitude and throttle aperture

图17 衰减系数与节流孔径之间关系

Fig.17 Relationship between attenuation coefficient and throttle aperture

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