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Journal of Projectiles, Rockets, Missiles and Guidance >

2023 , Vol. 43 >Issue 2: 80 - 87

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2023.02.014

Optimization of Thrust Model of Pintle Control Nozzle

  • CHEN Xiaoli ,
  • NIU Lu ,
  • PAN Kewei ,
  • WANG Zhixin ,
  • CHEN Haoran
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  • Shanghai Space Propulsion Technology Research Institute,Shanghai 201109,China

Received date: 2022-08-31

  Online published: 2025-02-24

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Abstract

The geometric throat area calculation model, theoretical thrust model and 3-D simulation model are established for the pintle control thrust nozzle. Through the numerical simulation of the flow field in the nozzle, the variation of the geometric throat area, outlet mass flow rate and nozzle thrust with the position of the pintle is studied. It is found that the theoretical thrust is quite different from the numerical calculation results, so the thrust model is optimized. Firstly, the calculation method of aerodynamic equivalent throat area is established, and the variation of aerodynamic equivalent throat area with the position of the pintle and working condition is studied. The calculation model of equivalent throat area is optimized, which can better fit the change of aerodynamic equivalent throat area with the position of pintle. Based on this, the thrust model of the nozzle in the over-expansion state is revised, and the optimized thrust model is consistent with the simulation results. Finally, the nozzle thrust under different positions of the pintle and inlet pressures is obtained through cold air test, which verified the accuracy of the thrust model.

Key words： pintle flow regulation nozzle; thrust model; numerical simulation; equivalent throat; thrust test

Cite this article

CHEN Xiaoli , NIU Lu , PAN Kewei , WANG Zhixin , CHEN Haoran . Optimization of Thrust Model of Pintle Control Nozzle[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2023 , 43(2) : 80 -87 . DOI: 10.15892/j.cnki.djzdxb.2023.02.014

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