同轴式喉栓变推力发动机喉栓受力特性

于海旭; 邓恒; 白阳; 贾胜锡; 王昭; 樊建龙

doi:10.13224/j.cnki.jasp.20250429

同轴式喉栓变推力发动机喉栓受力特性

doi: 10.13224/j.cnki.jasp.20250429

于海旭^{1, 2,},
邓恒^{1, 2,*, ,},
白阳^{1, 2},
贾胜锡^{1, 2},
王昭^{1, 2},
樊建龙^{1, 2}

1.
中国兵器工业集团有限公司西安现代控制技术研究所，西安 710065
2.
陆空基信息感知与控制全国重点实验室，西安 710065

详细信息

作者简介:
于海旭（1992-），男，工程师，博士，研究领域为固体火箭发动机设计。E-mail：yuhaixu0314@163.com

通讯作者:
邓恒（1979-），男，正高级工程师，博士，研究领域为固体火箭发动机设计。E-mail：DengHeng163@163.com

中图分类号: V435
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出版历程
- 收稿日期: 2025-09-14
- 网络出版日期: 2026-04-18

Load on pintle in a coaxial pintle variable thrust solid rocket motor

Yu Haixu^{1, 2
,},
Deng Heng^{1, 2,*
, ,},
Bai Yang^{1, 2},
Jia Shengxi^{1, 2},
Wang Zhao^{1, 2},
Fan Jianlong^{1, 2}

1.
China North Industries Group Corporation Limited，Xi’an Modern Control Technology Research Institute，Xi’an 710065，China
2.
National Key Laboratory of Land and Air Based Information Perception and Control，Xi’an 710065，China

摘要

摘要:
为了研究同轴式喉栓变推力发动机的喉栓在流场中的受力情况，通过数值仿真，研究了不同型面喉栓在多种典型工况下的受力特性。计算结果表明：在起飞级工况下，喉栓所承受的最大载荷与发动机推力相当，且不同型面喉栓之间的受力差异并不显著；在续航级的巡航和末尾加速阶段，凹型面受力分别为凸型面的63%和51%，锥型面的受力介于两者之间。当主动调节喉栓位置时，随着燃烧室压力的升高，喉栓的受力呈现明显的线性增长特征。当燃烧室压力出现波动时，喉栓受力也会随压力变化而呈线性变化。通过本文提出的尾部凹槽设计方法优化凸型面喉栓外形后，最大载荷可降低95%。
- 喉栓 /
- 变推力 /
- 受力分析 /
- 喉栓型面 /
- 伺服机构 /
- 固体火箭发动机
Abstract:
To investigate the load on the pintle in a coaxial thrust variable solid rocket motor, this study numerically analyzes the force acting on pintles with different profiles under various typical operating conditions. The results show that during takeoff stage, the maximum load on pintles matches the engine thrust, with no significant differences observed between profiles. In cruise and final acceleration phases of the sustenance stage, concave-profile pintles bear 63% and 51% of the load compared to convex-profile counterparts, while conical-profile pintles experience intermediate loads. When actively adjusting pintle positions, the load increases linearly with rising combustion chamber pressure. Pressure fluctuations within the combustion chamber also cause proportional linear variations in pintle loads. The force on the pintle can be significantly reduced by optimizing its shape. After adding a groove to the tail of the convex surface pintle, the maximum load can be reduced by 95%.
- pintle /
- variable thrust /
- load analysis /
- pintle profile /
- servo mechanism /
- solid rocket motor

HTML

图 1 变推力发动机内弹道示意图

Figure 1. Internal ballistics of a pintle variable thrust SRM

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图 2 喉栓及喷管结构示意图

Figure 2. Schematic diagram of the pintle and nozzle

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图 3 喷管等效喉部面积随喉栓位移的变化规律

Figure 3. Equivalent throat area of different s

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图 4 仿真与文献[27]结果对比

Figure 4. Comparison of present results and experiment results in Ref. [27]

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图 5 起飞工况马赫数云图

Figure 5. Contours of Mach number under takeoff conditions

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图 6 巡航工况马赫数云图

Figure 6. Contours of Mach number under cruise conditions

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图 7 巡航工况喷管壁面压力分布

Figure 7. Pressure distribution of nozzle wall under cruise conditions

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图 8 巡航工况喉栓表面压力分布

Figure 8. Pressure distribution of pintles under cruise conditions

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图 9 末尾加速工况马赫数云图

Figure 9. Contours of Mach number under final acceleration conditions

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图 10 末尾加速工况喉栓表面压力分布

Figure 10. Pressure distribution of pintles under final acceleration conditions

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图 11 压力主动调节过程中推力和喉栓受力的变化

Figure 11. Variation of thrust and pintle load with pressure adjustment

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图 12 燃烧室压力波动对发动机推力和喉栓受力的影响

Figure 12. Variation of thrust and pintle load with pressure fluctuatin

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图 13 喉栓受力示意图

Figure 13. Force on pintle

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图 14 喉栓结构优化后的流场

Figure 14. Flow field after structure optimization

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图 15 喉栓优化前后受力对比

Figure 15. Comparison of pintle load before and after optimization

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表 1 续航级工况表

Table 1. Parameters of gas

总压/MPa 推进剂燃速/（mm/s）喷管等效喉部面积/mm²

1.2 8.1 1017.9
2 11.1 824.5
4 16.8 524.6
6 21.4 530.9
8 25.4 475.3

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表 2 燃气参数表

Table 2. Parameters of gas

参数量值

比热比γ 1.16

相对分子质量M/（g/mol） 27.17

总温T₀/K 3000

总压p₀/MPa 起飞级 12

续航级 1.2～8

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表 3 起飞工况推力和喉栓受力

Table 3. Thrust and pintle load under takeoff conditions

p_c/MPa 型面 F/kN F_p/kN

12 凹型面 54.29 −47.45

锥型面 54.23 −46.42

凸型面 54.13 −43.59

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表 4 巡航工况推力和喉栓受力

Table 4. Thrust and pintle load under different cruise conditions

p_c/MPa 型面 F/N F_p/N

1.2 凹型面 505.27 −1380.35

锥型面 601.90 −2045.13

凸型面 500.98 −2193.77

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表 5 末尾加速工况推力和喉栓受力

Table 5. Thrust and pintle load under final acceleration conditions

p_c/MPa 型面 F/N F_p/N

8 凹型面 5124.22 −5456.16

锥型面 5075.23 −8322.45

凸型面 5042.43 −10613.93

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参考文献(28)

[1]	邓恒, 李志浩, 张时空, 等. 基于零维内弹道模型的变推力发动机喉栓型面设计与工作特性研究[J]. 推进技术, 2022, 43(11): 210513. Deng Heng, Li Zhihao, Zhang Shikong, et al. Pintle profile design method based on zero-dimensional interior ballistic model and performance for variable thrust motor[J]. Journal of Propulsion Technology, 2022, 43(11): 210513. (in Chinese doi: 10.13675/j.cnki.tjjs.210513 Deng Heng, Li Zhihao, Zhang Shikong, et al. Pintle profile design method based on zero-dimensional interior ballistic model and performance for variable thrust motor[J]. Journal of Propulsion Technology, 2022, 43(11): 210513. (in Chinese) doi: 10.13675/j.cnki.tjjs.210513
[2]	陈晓丽, 牛禄, 潘科玮, 等. 喉栓式可调喷管推力模型优化研究[J]. 弹箭与制导学报, 2023, 43(2): 80-87. Chen Xiaoli, Niu Lu, Pan Kewei, et al. Optimization of thrust model of pintle control nozzle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2023, 43(2): 80-87. (in Chinese Chen Xiaoli, Niu Lu, Pan Kewei, et al. Optimization of thrust model of pintle control nozzle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2023, 43(2): 80-87. (in Chinese)
[3]	王佳兴, 魏志军, 王宁飞. 变推力固体火箭发动机非稳态影响因素研究[J]. 北京理工大学学报, 2011, 31(9): 1018-1022, 1121. Wang Jiaxing, Wei Zhijun, Wang Ningfei. Research on non-steady characters of thrust controllable solid rocket motor with pintle[J]. Transactions of Beijing Institute of Technology, 2011, 31(9): 1018-1022, 1121. (in Chinese Wang Jiaxing, Wei Zhijun, Wang Ningfei. Research on non-steady characters of thrust controllable solid rocket motor with pintle[J]. Transactions of Beijing Institute of Technology, 2011, 31(9): 1018-1022, 1121. (in Chinese)
[4]	张淑慧, 胡波, 孟雅桃. 推力可控固体火箭发动机应用及发展[J]. 固体火箭技术, 2002, 25(4): 12-15. Zhang Shuhui, Hu Bo, Meng Yatao. Application and development of controllable solid rocket motor[J]. Journal of Solid Rocket Technology, 2002, 25(4): 12-15. (in Chinese Zhang Shuhui, Hu Bo, Meng Yatao. Application and development of controllable solid rocket motor[J]. Journal of Solid Rocket Technology, 2002, 25(4): 12-15. (in Chinese)
[5]	CAUBET P, BERDOYES M. Innovative ArianeGroup controllable solid propulsion technologies[C]//AIAA Propulsion and Energy 2019 Forum. AIAA, 2019: AIAA2019-3878.
[6]	苗禾状. 喉栓式可控固体火箭发动机推力调节研究[D]. 哈尔滨: 哈尔滨工程大学, 2009. MIAO Hezhuang. The study on the performance of pintle controlled thrust solid rocket motor[D]. Harbin: Harbin Engineering University, 2009. (in Chinese MIAO Hezhuang. The study on the performance of pintle controlled thrust solid rocket motor[D]. Harbin: Harbin Engineering University, 2009. (in Chinese)
[7]	李娟, 王占利, 郑凯, 等. 喉栓式推力可调固体火箭发动机动态响应特性数值分析[J]. 固体火箭技术, 2009, 32(1): 48-52. Li Juan, Wang Zhanli, Zheng Kai, et al. Numerical analysis on dynamic response characteristics of pintle-controlled solid rocket motor[J]. Journal of Solid Rocket Technology, 2009, 32(1): 48-52. (in Chinese Li Juan, Wang Zhanli, Zheng Kai, et al. Numerical analysis on dynamic response characteristics of pintle-controlled solid rocket motor[J]. Journal of Solid Rocket Technology, 2009, 32(1): 48-52. (in Chinese)
[8]	李耿, 武婷文, 王周成, 等. 推力可调喉栓式固体火箭发动机瞬态特性研究[J]. 固体火箭技术, 2025, 48(2): 216-224. Li Geng, Wu Tingwen, Wang Zhoucheng, et al. Transient characteristics of pintle variable thrust solid rocket motor[J]. Journal of Solid Rocket Technology, 2025, 48(2): 216-224. (in Chinese doi: 10.7673/j.issn.1006-2793.2025.02.006 Li Geng, Wu Tingwen, Wang Zhoucheng, et al. Transient characteristics of pintle variable thrust solid rocket motor[J]. Journal of Solid Rocket Technology, 2025, 48(2): 216-224. (in Chinese) doi: 10.7673/j.issn.1006-2793.2025.02.006
[9]	唐金兰, 胡博, 李进贤, 等. 非同轴喉栓式推力调节喷管性能影响因素分析[J]. 弹箭与制导学报, 2013, 33(4): 123-126. Tang Jinlan, Hu Bo, Li Jinxian, et al. The analysis of non-coaxial pintle control nozzle thrust performance and influence factor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(4): 123-126. (in Chinese doi: 10.3969/j.issn.1673-9728.2013.04.034 Tang Jinlan, Hu Bo, Li Jinxian, et al. The analysis of non-coaxial pintle control nozzle thrust performance and influence factor[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2013, 33(4): 123-126. (in Chinese) doi: 10.3969/j.issn.1673-9728.2013.04.034
[10]	唐金兰, 宋慧敏, 李进贤, 等. 基于动网格的喉栓式推力可调喷管内流场数值模拟[J]. 固体火箭技术, 2014, 37(5): 634-639. Tang Jinlan, Song Huimin, Li Jinxian, et al. Numerical simulation of pintle-controlled nozzle flow field based on dynamic grid[J]. Journal of Solid Rocket Technology, 2014, 37(5): 634-639. (in Chinese doi: 10.7673/j.issn.1006-2793.2014.05.009 Tang Jinlan, Song Huimin, Li Jinxian, et al. Numerical simulation of pintle-controlled nozzle flow field based on dynamic grid[J]. Journal of Solid Rocket Technology, 2014, 37(5): 634-639. (in Chinese) doi: 10.7673/j.issn.1006-2793.2014.05.009
[11]	马宝印, 李军伟, 王兴起, 等. 针栓变推力固体火箭发动机动态响应特性研究[J]. 推进技术, 2020, 41(10): 2161-2172. Ma Baoyin, Li Junwei, Wang Xingqi, et al. Simulation on dynamic response characteristics of pintle variable thrust solid rocket motor[J]. Journal of Propulsion Technology, 2020, 41(10): 2161-2172. (in Chinese doi: 10.13675/j.cnki.tjjs.190784 Ma Baoyin, Li Junwei, Wang Xingqi, et al. Simulation on dynamic response characteristics of pintle variable thrust solid rocket motor[J]. Journal of Propulsion Technology, 2020, 41(10): 2161-2172. (in Chinese) doi: 10.13675/j.cnki.tjjs.190784
[12]	李春杰, 李军伟, 田忠亮, 等. 针栓烧蚀对变推力固体发动机内弹道的影响[J]. 航空学报, 2025, 46(14): 131519. Li Chunjie, Li Junwei, Tian Zhongliang, et al. Influence of pintle ablation on internal ballistics of variable thrust solid motor[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(14): 131519. (in Chinese Li Chunjie, Li Junwei, Tian Zhongliang, et al. Influence of pintle ablation on internal ballistics of variable thrust solid motor[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(14): 131519. (in Chinese)
[13]	周战锋, 胡春波, 李江, 等. 变推力固体火箭发动机喉栓烧蚀试验研究[J]. 固体火箭技术, 2009, 32(2): 163-166, 170. Zhou Zhanfeng, Hu Chunbo, Li Jiang, et al. Experimental investigation of erosion performance of pintle in thrust-controllable SRM[J]. Journal of Solid Rocket Technology, 2009, 32(2): 163-166, 170. (in Chinese Zhou Zhanfeng, Hu Chunbo, Li Jiang, et al. Experimental investigation of erosion performance of pintle in thrust-controllable SRM[J]. Journal of Solid Rocket Technology, 2009, 32(2): 163-166, 170. (in Chinese)
[14]	代晓松, 王一白, 刘宇, 等. 固体轨控发动机针栓喷管热化学烧蚀特性[J]. 兵器装备工程学报, 2018, 39(1): 195-200. Dai Xiaosong, Wang Yibai, Liu Yu, et al. Pintle nozzle thermochemical erosion characteristics in solid rocket orbit-control motors[J]. Journal of Sichuan Ordnance, 2018, 39(1): 195-200. (in Chinese Dai Xiaosong, Wang Yibai, Liu Yu, et al. Pintle nozzle thermochemical erosion characteristics in solid rocket orbit-control motors[J]. Journal of Sichuan Ordnance, 2018, 39(1): 195-200. (in Chinese)
[15]	成沉, 鲍福廷, 刘旸, 等. 喉栓式变推力固体火箭发动机压强控制模型分析[J]. 固体火箭技术, 2013, 36(6): 748-752. Cheng Chen, Bao Futing, Liu Yang, et al. Analysis of fluid dynamic control model for pintle controlled solid rocket motor[J]. Journal of Solid Rocket Technology, 2013, 36(6): 748-752. (in Chinese Cheng Chen, Bao Futing, Liu Yang, et al. Analysis of fluid dynamic control model for pintle controlled solid rocket motor[J]. Journal of Solid Rocket Technology, 2013, 36(6): 748-752. (in Chinese)
[16]	成沉. 喉栓式固体变推力发动机推力调控方法及性能仿真研究[D]. 西安: 西北工业大学, 2017. CHENG Chen. Thrust control method and performance simulation of pintle controlled solid rocket motor[D]. Xi’an: Northwestern Polytechnical University, 2017. (in Chinese CHENG Chen. Thrust control method and performance simulation of pintle controlled solid rocket motor[D]. Xi’an: Northwestern Polytechnical University, 2017. (in Chinese)
[17]	杨慧欣, 王旭, 李响. 基于深度学习的固体姿轨控发动机性能预示方法[J/OL]. 北京航空航天大学学报, 2024-08-13. https://kns.cnki.net/kcms/detail/11.2625.V.20201030.1042.002.html.
[18]	王鹏宇, 王政涛, 武泽平, 等. 多工况下变推力固体发动机喉栓喷管型面一体化优化设计[J]. 固体火箭技术, 2022, 45(3): 337-342. Wang Pengyu, Wang Zhengtao, Wu Zeping, et al. Optimization design for contour of pintle nozzle for variable thrust solid rocket motor under multiple working conditions[J]. Journal of Solid Rocket Technology, 2022, 45(3): 337-342. (in Chinese Wang Pengyu, Wang Zhengtao, Wu Zeping, et al. Optimization design for contour of pintle nozzle for variable thrust solid rocket motor under multiple working conditions[J]. Journal of Solid Rocket Technology, 2022, 45(3): 337-342. (in Chinese)
[19]	王茹瑶, 宋岸忱, 王立民, 等. 基于TDLAS技术的喉栓式变推力发动机羽流速度特性[J]. 航空学报, 2023, 44(17): 128107. Wang Ruyao, Song Anchen, Wang Limin, et al. Plume velocity characteristics of pintle controlled solid rocket motor based on TDLAS technique[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 128107. (in Chinese Wang Ruyao, Song Anchen, Wang Limin, et al. Plume velocity characteristics of pintle controlled solid rocket motor based on TDLAS technique[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(17): 128107. (in Chinese)
[20]	侯晓, 付鹏, 武渊. 固体火箭发动机能量管理技术及其新进展[J]. 固体火箭技术, 2017, 40(1): 1-6, 23. Hou Xiao, Fu Peng, Wu Yuan. Energy management technology of SRM and its development[J]. Journal of Solid Rocket Technology, 2017, 40(1): 1-6, 23. (in Chinese Hou Xiao, Fu Peng, Wu Yuan. Energy management technology of SRM and its development[J]. Journal of Solid Rocket Technology, 2017, 40(1): 1-6, 23. (in Chinese)
[21]	Lee J H, Park B H, Yoon W. Parametric investigation of the pintle-perturbed conical nozzle flows[J]. Aerospace Science and Technology, 2013, 26(1): 268-279.
[22]	卢明聿, 张胜敏, 周战锋, 等. 喉栓体装配偏差引起流动变化及其受力分析[J]. 弹箭与制导学报, 2011, 31(6): 146-148. Lu Mingyu, Zhang Shengmin, Zhou Zhanfeng, et al. The study on the effect of flow and stress change caused by pintle assembly deviation[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011, 31(6): 146-148. (in Chinese Lu Mingyu, Zhang Shengmin, Zhou Zhanfeng, et al. The study on the effect of flow and stress change caused by pintle assembly deviation[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2011, 31(6): 146-148. (in Chinese)
[23]	武婷文, 王健儒, 白彦军, 等. 针栓式变推力固体火箭发动机中针栓所受载荷[J]. 航空动力学报, 2024, 39(7): 20220472. Wu Tingwen, Wang Jianru, Bai Yanjun, et al. Force on the pintle of pintle variable thrust solid rocket motor[J]. Journal of Aerospace Power, 2024, 39(7): 20220472. (in Chinese Wu Tingwen, Wang Jianru, Bai Yanjun, et al. Force on the pintle of pintle variable thrust solid rocket motor[J]. Journal of Aerospace Power, 2024, 39(7): 20220472. (in Chinese)
[24]	Boulahbal C, Milinovic M, Rezgui N. Nozzle flow gas-dynamical properties under dome deflector thrust vector system effect[J]. Thermal Science, 2019, 23(2 Part B): 1263-1277.
[25]	Pei Xinyan, Wu Zhiwen, Wei Zhijun, et al. Numerical investigation on internal regressing shapes of solid-fuel scramjet combustor[J]. Journal of Propulsion and Power, 2013, 29(5): 1041-1051.
[26]	于海旭, 魏志军, 张旭东, 等. 狭缝喷管高度补偿性能数值仿真研究[J]. 航空动力学报, 2024, 39(12): 20220316. Yu Haixu, Wei Zhijun, Zhang Xudong, et al. Numerical simulation study on altitude compensating performance of a slot nozzle[J]. Journal of Aerospace Power, 2024, 39(12): 20220316. (in Chinese Yu Haixu, Wei Zhijun, Zhang Xudong, et al. Numerical simulation study on altitude compensating performance of a slot nozzle[J]. Journal of Aerospace Power, 2024, 39(12): 20220316. (in Chinese)
[27]	Hunter C. Experimental, theoretical, and computational investigation of separated nozzle flows[R]. AIAA-1998-3107, 1998.
[28]	李军伟, 魏志军, 隋欣. 固体火箭发动机原理[M]. 北京: 北京理工大学出版社, 2023. Li Junwei, Wei Zhijun, Sui Xin. Fundamentals of solid propellant rocket motor[M]. Beijing: Beijing Institute of Technology Press, 2023. (in Chinese Li Junwei, Wei Zhijun, Sui Xin. Fundamentals of solid propellant rocket motor[M]. Beijing: Beijing Institute of Technology Press, 2023. (in Chinese)