助推段火箭发动机喷焰红外辐射特性数值计算

doi:10.12382/bgxb.2023.0546

摘要/Abstract

摘要：

助推段火箭发动机尾喷焰具有显著的红外辐射特性,成为天基红外预警系统重点关注的对象。以三组元固体发动机为研究对象,建立连续流域和过渡流域的尾喷焰反应流场计算模型,采用两级助推段质心弹道法确定飞行弹道,通过反向寻优法完备发动机型谱参数,基于等效单喷管法简化流场计算,基于窄谱带法和视在光线法计算尾喷焰的红外辐射特性。研究结果表明:复燃效应使得尾喷焰红外辐射光谱强度升高约20倍,谱带积分强度升高约10倍;尾喷焰红外光谱存在2.7μm和4.3μm的特征峰值;低空流域的光谱强度较高,且不同谱带内积分强度随高度的升高呈现出波动规律和暗区现象;助推段尾喷焰辐射强度差值高达3个量级,尤其在4.3μm较为明显。所得成果可为火箭在助推段的探测和识别提供一定的理论参考。

关键词: 火箭发动机, 三组元推进剂, 助推段, 尾喷焰, 红外辐射

Abstract:

Rocket engine exhaust plume during the boost phase is a main object captured by space-based infrared early warning systems due to its significant infrared radiation features. A tripropellant solid rocket engine is taken as the research object. The calculation models of exhaust plume flow fields in continuous and rare regimes are established.The flight trajectory is determined considering the two-stage boost phase.The design parameters of engines are evaluated by the reverse optimization method, and the calculation of flow field is simplified by using an equivalent single nozzle method.The infrared radiation characteristics of rocket exhaust plume are predicted based on the statistical narrow band method and the line-of-sight approach.The results show that the afterburning effect makes the infrared radiation intensity of the plume increase by about 20 times and the in-band radiance increase by about 10 times. There exist two characteristic peaks in 2.7μm and 4.3μm bands in the infrared spectrum of exhaust plume. The spectral intensity of low-altitude exhaust plume is relatively high, and the integrated intensity within different spectral bands exhibits fluctuation patterns and trough region with the increase in altitude. The difference of the in-band radiances of exhaust plume in the boost phase is up to three orders of magnitude, especially in 4.3μm band.This work can provide a theoretical reference for the detection and recognition of rocket in the boost phase.

Key words: rocket engine, tripropellant, boost phase, exhaust plume, infrared radiation

中图分类号:

TN219

张腾, 牛青林, 柳云峰, 高文强, 董士奎. 助推段火箭发动机喷焰红外辐射特性数值计算[J]. 兵工学报, 2024, 45(7): 2228-2239.

ZHANG Teng, NIU Qinglin, LIU Yunfeng, GAO Wenqiang, DONG Shikui. Numerical Calculation of Infrared Radiation Characteristics of Rocket Engine Exhaust Plume in Boost Phase[J]. Acta Armamentarii, 2024, 45(7): 2228-2239.

图/表 15

图1 超音速射流纹影试验与数值计算结果对比(上为实验纹影结果,下为CFD仿真结果)

Fig.1 Comparison of supersonic jet schlieren test and numerically calculated results(upper: test schlieren imaging result, and below: CFD simulated result)

图2 Black Brant喷焰辐射光谱计算结果对照

Fig.2 Comparison of calculated spectral intensities of Black Brant plume

图3 计算域及网格划分

Fig.3 Computational domain and grid distributions

图4 不同网格数下的尾喷焰轴线温度

Fig.4 Temperatures of exhaust plume on axis under different grid numbers

表1 一、二级火箭发动机性能参数[2]

Table 1 Performance parameters of 1st and 2nd stage engines[2]

一级或二级	编号	推进剂质量/ kg	推进剂配比	发动机质量比	地面比冲/ (N·s·kg^-1)	真空比冲/ (N·s·kg^-1)	喷管数量	喷管膨胀比	最大推力/ kN	工作时间/ s	燃烧室压力/ MPa	喷口直径/ m	喉部直径/ m
一级	M55A-1	20800	70%AP 14%HTBN 16%Al	0.915	2316	2626	4	10	912	61.6	4.923	0.5580	0.1968
二级	SR19-AJ-1	6426	70%AP 14%CTPB 16%Al	0.886	2471	2823	1	24.8	270	65.2	3.109	1.2195	0.2449

表2 发动机喷口参数

Table 2 Parameters of nozzle exit plane

性能参数	T/K	p/MPa	Ma	CO₂ 摩尔分数 $Y C O 2$	CO摩尔分数 Y_CO	H₂摩尔分数 $Y H 2$	H₂O摩尔分数 $Y H 2 O$	HCl摩尔分数 Y_HCl	H摩尔分数 Y_H	OH摩尔分数 Y_OH	N₂摩尔分数 $Y N 2$	Al₂O₃摩尔分数 $Y A l 2 O 3$
一级	2119.87	0.07383	3.027	0.01833	0.21360	0.31744	0.13641	0.15112	0.00222	0.00013	0.08433	0.07560
二级	1807.70	0.01441	3.599	0.02046	0.24545	0.32193	0.10326	0.15415	0.00055	0.00001	0.07718	0.07681

表2 发动机喷口参数

Table 2 Parameters of nozzle exit plane

性能参数	T/K	p/MPa	Ma	CO₂ 摩尔分数 $Y C O 2$	CO摩尔分数 Y_CO	H₂摩尔分数 $Y H 2$	H₂O摩尔分数 $Y H 2 O$	HCl摩尔分数 Y_HCl	H摩尔分数 Y_H	OH摩尔分数 Y_OH	N₂摩尔分数 $Y N 2$	Al₂O₃摩尔分数 $Y A l 2 O 3$
一级	2119.87	0.07383	3.027	0.01833	0.21360	0.31744	0.13641	0.15112	0.00222	0.00013	0.08433	0.07560
二级	1807.70	0.01441	3.599	0.02046	0.24545	0.32193	0.10326	0.15415	0.00055	0.00001	0.07718	0.07681

图5 助推段弹道

Fig.5 Boost-phase trajectory

表3 典型弹道点对应的来流参数

Table 3 Flow parameters for representative ballistic points

T/s	H/km	v/(m·s^-1)	T/K	p/Pa
34	10	690	223.252	26499.9
48	20	1150	216.65	5529.31
58	30	1590	226.509	1197.03
67	40	1795	250.35	287.144
77	50	2080	270.65	79.7791
85	60	2359	247.021	21.9587
93	70	2683	219.585	5.2209
99	80	2982	198.639	1.05247
106	90	3327	186.867	0.183593
112	100	3730	195.081	0.0320113
118	110	4120	240	0.00710407
123	120	4630	360	0.00253827

图6 不同高度下的尾喷焰温度云图

Fig.6 Temperature contours of exhaust plume atdifferent altitudes

图7 不同高度下的尾喷焰CO2摩尔分数云图

Fig.7 Contours of CO2 mole fraction of exhaust plume at different altitudes

图8 复燃尾喷焰不同高度下的光谱强度

Fig.8 Spectral radiation intensities of exhaust plume with afterburning at different altitudes

图9 复燃效应对光谱强度的增量曲线

Fig.9 Incremental profiles of spectral radiation intensity with afterburning

图10 无复燃条件下的红外辐射积分强度

Fig.10 Integrated radiances of exhaust plume without afterburning

图11 有复燃条件下的红外辐射积分强度分布

Fig.11 Integrated radiances of exhaust plume with afterburning

图12 典型高度下2.7μm(左)和4.3μm(右)波段的辐射强度分布云图

Fig.12 Intrinsic radiation intensity contours of plume in 2.7μm (left) and 4.3μm (right) bands at representative altitudes

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