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Journal of Projectiles, Rockets, Missiles and Guidance >

2020 , Vol. 40 >Issue 2: 117 - 120

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2020.02.029

Coupled Numerical Simulation on Flow Field and Thermo-structure and Experiment Research of Composite Nozzle

  • WU Qiu 1, 2, 3 ,
  • JI Zheng 2, 3 ,
  • REN Quanbin 2, 3 ,
  • CHEN Linquan 2, 3 ,
  • ZHANG Ming 2, 3
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  • 1 Northwestern Polytechnical University, Xi’an 710072, China
  • 2 The 41st Institute of the Fourth Academy of CASC, Xi’an 710025, China
  • 3 National Key Lab of Combustion, Flow and Thermo-structure, Xi’an 710025, China

Received date: 2017-09-15

  Online published: 2025-05-30

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Abstract

In order to obtain the varieties of nozzle temperature and throat erosion by using pure-high temperature propellants and high-low temperature combined propellants. Coupled numerical simulation on flow field and Thermo-structure of composite nozzle and experiments were implemented. The simulation and experiments results indicated the low temperature propellants can bring down the nozzle structure temperature effectively. The low temperature propellants can also reduce the throat erosion effectively by hot-gas. The ablation rate using combined propellants decline 15.8% compared with pure-high temperature propellants.

Key words： high and low temperature combined propellants; flow field and thermo-structure; the temperature of nozzle out-surface; ablation rate

Cite this article

WU Qiu , JI Zheng , REN Quanbin , CHEN Linquan , ZHANG Ming . Coupled Numerical Simulation on Flow Field and Thermo-structure and Experiment Research of Composite Nozzle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2020 , 40(2) : 117 -120 . DOI: 10.15892/j.cnki.djzdxb.2020.02.029

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References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
张晓光, 王长辉, 刘宇, 等. 固体火箭发动机喉衬流场及热结构耦合分析[J]. 固体火箭技术, 2011, 34(5):579-583.

[2]
王天波, 薛谈顺, 周长省, 等. 复合结构喷管温度场及应力场数值模拟[J]. 弹道学报, 2012, 24(2):88-91.

[3]
胡海峰, 鲍福廷, 王艺杰, 等. 喷管分离流流动-热-结构顺序耦合数值模拟及试验研究[J]. 宇航学报, 2011, 32(7):1534-1541.

[4]
郑晓亚, 陈凤明, 蔡飞超. 复合喷管热结构耦合计算的一种策略[J]. 航空动力学报, 2011, 26(1):223-227.

[5]
陈林泉. 降低喉衬烧蚀的高低燃温推进剂组合装药技术研究[D]. 西安: 西北工业大学, 2010.

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