狭缝喷管高度补偿性能数值仿真研究

于海旭; 魏志军; 张旭东; 龚笋根

doi:10.13224/j.cnki.jasp.20220316

狭缝喷管高度补偿性能数值仿真研究

doi: 10.13224/j.cnki.jasp.20220316

1.
北京理工大学宇航学院，北京 100081
2.
中国船舶集团有限公司昆明海威机电技术研究所，昆明 650236

详细信息

作者简介:
于海旭（1992-），男，博士生，主要从事高度补偿喷管研究。E-mail：yuhaixu0314@163.com

通讯作者:
魏志军（1967-），男，教授，博士，主要从事固体火箭发动机研究。E-mail：wzj@bit.edu.cn

中图分类号: V430
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出版历程
- 收稿日期: 2022-05-09
- 网络出版日期: 2024-08-15

Numerical simulation study on altitude compensating performance of a slot nozzle

1.
School of Aerospace Engineering，Beijing Institute of Technology，Beijing 100081，China
2.
Haiwei Electromechanical Technology Institute of Kunming，China State Shipbuilding Corporation Limited，Kunming 650236，China

摘要

摘要:
狭缝式通风喷管（以下简称狭缝喷管）是一种高度补偿喷管。为研究其高度补偿性能及影响规律，本文以扩张比40的钟形喷管为基础，设计了3种尺寸的狭缝喷管，并进行了数值仿真研究，得到了工作高度和狭缝宽度对流场特性及比冲性能的影响规律。并通过外弹道计算，得到了狭缝喷管对一级火箭完整工作过程的总冲增益。计算结果表明：相比于同扩张比的钟形喷管，狭缝喷管在低空具有比冲增益效果，但在高空存在比冲损失，狭缝宽度越大，低空的增益和高空的损失都越大；狭缝喷管的临界补偿高度只与狭缝位置有关，而与狭缝宽度无关；在喷管扩张段的合适位置，设置合适宽度的狭缝，可以显著提高一级火箭总冲性能，在航天飞机固体助推器和某微纳卫星运载火箭两种应用场景下，总冲增益分别为1.8%和3.0%，相当于平均比冲分别提高5.0 s和8.0 s。
- 狭缝喷管 /
- 高度补偿 /
- 比冲 /
- 总冲 /
- 外弹道
Abstract:
A vented nozzle with slots (slot nozzle) is a kind of altitude compensating nozzle. In order to study its altitude compensating performance and influence, three sizes of slit nozzles were designed based on a bell nozzle with expansion ratio of 40, and numerical simulation was carried out to obtain the influences of altitude and slit width on the flow field characteristics and specific impulse. And through external ballistic calculation, the total impulse gain on the whole working process of the first stage rocket was obtained. The results showed that compared with the bell nozzle with the same expansion ratio, the slot nozzle had specific impulse gain at low altitude, but specific impulse loss at high altitude. The wider slot width indicated the greater gain at low altitude and the bigger loss at high altitude. The critical compensating height was related only to the slit position, but not to the slit width. The total impulse of the first-stage rocket can be significantly improved by setting slots of appropriate width at the appropriate position. In these two application scenarios of the Solid Rocket Booster and Nanosat Launch Vehicle, the total impulse gain was 1.8% and 3.0%, respectively, which was equivalent to an average specific impulse increase of 5.0 s and 8.0 s, respectively.
- slot nozzle /
- altitude compensating /
- specific impulse /
- total impulse /
- external ballistic

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图 1 狭缝喷管结构示意图

Figure 1. Scheme diagram of slot nozzle structure

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图 2 仿真与文献[17]结果对比

Figure 2. Comparison of present results and experiment results in Reference [17]

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图 3 边界条件

Figure 3. Boundary conditions

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图 4 壁面y⁺分布

Figure 4. Nozzle wall y⁺ curve

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图 5 低空工况狭缝喷管和钟形喷管流场对比

Figure 5. Comparison of flow field between slot nozzle and bell nozzle at low altitude

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图 6 钟形喷管海平面工况马赫数云图

Figure 6. Mach contour of bell nozzle at sea level

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图 7 狭缝喷管和钟形喷管壁面压力分布对比

Figure 7. Comparison of wall pressure distributions between slot nozzle and bell nozzle

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图 8 高空工况狭缝喷管和钟形喷管流场对比

Figure 8. Comparison of flow field between slot nozzle and bell nozzle at high altitude

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图 9 通过两道狭缝的气体流率

Figure 9. Flow rate through two slots

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图 10 狭缝喷管和钟形喷管的比冲曲线

Figure 10. Specific impulse comparison between slot nozzle and bell nozzle

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图 11 25 km工况狭缝喷管和钟形喷管内壁面压力分布

Figure 11. Inner wall pressure distributions of slot nozzle and bell nozzle at 25 km

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图 12 3种狭缝喷管内壁面压力分布对比

Figure 12. Comparison of wall pressure distributions of three kinds of slot nozzles

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图 13 3种狭缝喷管通过狭缝的气体流率对比

Figure 13. Comparison of flow rates through slots of three kinds of slot nozzles

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图 14 3种狭缝喷管与钟形喷管比冲对比

Figure 14. Specific impulse comparison of slot nozzles and the bell nozzle

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图 15 3种狭缝的效率对比

Figure 15. Comparison of efficiency of the slots

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图 16 飞行器受力示意图

Figure 16. Schematic diagram of rocket force condition

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表 1 钟形喷管参数

Table 1. Parameters of the bell nozzle

参数	数值
喉部半径 r/mm	15
扩张比 A_e/A_t	40
扩张段长度 L/mm	225
喉部上游半径 r_u/mm	22.5
喉部下游半径 r_d/mm	6
初始扩张角 ${\theta _1}$/（°）	32
出口扩张角 ${\theta _2}$/（°）	9

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表 2 燃气参数

Table 2. Parameters of gas

参数	数值
比定压热容 c_p/（J/（kg·K））	1840
比热比 k	1.18
相对分子量 M/10⁻³ （kg/mol）	20.11
总温 T₀/K	3300
总压 p₀/MPa	5

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表 3 算例设置

Table 3. Calculated cases

类型	参数	计算工况/km
狭缝喷管	狭缝宽度0.1r	0、1、2、5、7、10、15、20、25
	狭缝宽度0.5r	0、1、2、5、7、10、15、20、25
	狭缝宽度1.0r	0、1、2、3、4、5、6、8、10、15、20、25
钟形喷管	扩张比40	0、5、10、15、20、25
钟形喷管	扩张比7.25	0、5、10、15、20、25

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表 4 SRB外弹道计算结果

Table 4. External ballistic calculation results of SRB

喷管	总冲/ 10⁹ （N·s）	总冲增益/ %	末高度/ km	末速度/ （m/s）
钟形（A_e/A_t=7.25）	1.3		48.7	1080.1
0.1r狭缝喷管	1.41	1.71	46.1	1122.4
0.5r狭缝喷管	1.41	1.78	47.1	1120.1
1.0r狭缝喷管	1.41	1.68	47.8	1115.8

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表 5 NLV外弹道计算结果

Table 5. External ballistic calculation results of NLV

喷管	总冲/ 10⁶ （N·s）	总冲增益/ %	末高度/ km	末速度/ （m/s）
钟形（A_e/A_t=7.25）	2.93		79.7	2389.0
0.1r狭缝喷管	3.02	2.99	79.6	2608.4
0.5r狭缝喷管	3.01	2.76	80.3	2572.2
1.0r狭缝喷管	3.00	2.41	80.6	2537.6

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参考文献(20)

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