Mechanism of propellant micro-jet cooling effects on high-temperature non-equilibrium aerodynamic heating

XING Xuwen; YANG Xiaofeng; LIU Lei; DU Yanxia

doi:10.7638/kqdlxxb-2024.0084

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Mechanism of propellant micro-jet cooling effects on high-temperature non-equilibrium aerodynamic heating

更新时间：2026-05-28

- Mechanism of propellant micro-jet cooling effects on high-temperature non-equilibrium aerodynamic heating
- Vol. 43, Issue 4, Pages: 20-29(2025)
- 作者机构：
  
  1. 空天飞行空气动力科学与技术全国重点实验室,绵阳,621000
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2024.0084
  CLC： V231.1+5
- Published：2025
- 稿件说明：
移动端阅览
邢旭雯, 杨肖峰, 刘磊, 等. 推进剂微射流冷却对高温非平衡气动热的影响机理[J]. 空气动力学学报, 2025, 43(4): 20−29.

XING Xuwen, YANG Xiaofeng, LIU Lei, et al. Mechanism of propellant micro-jet cooling effects on high-temperature non-equilibrium aerodynamic heating[J]. 2025, 43(4): 20-29.
邢旭雯, 杨肖峰, 刘磊, 等. 推进剂微射流冷却对高温非平衡气动热的影响机理[J]. 空气动力学学报, 2025, 43(4): 20−29. DOI： 10.7638/kqdlxxb-2024.0084

XING Xuwen, YANG Xiaofeng, LIU Lei, et al. Mechanism of propellant micro-jet cooling effects on high-temperature non-equilibrium aerodynamic heating[J]. 2025, 43(4): 20-29. DOI： 10.7638/kqdlxxb-2024.0084.

摘要

飞行器在高速飞行时，可利用自身携带的推进剂通过微孔射流实现冷却，达到主动热防护效果。但在高温非平衡流条件下，可压缩外流与微射流交汇、射流排挤/掺混/反应多过程交织，微射流冷却主导性机制和影响因素复杂。本文建立了微射流黏性壁面边界模型，开展了微射流作用下高温非平衡流场数值模拟，探讨了射流孔径、速度和孔间距对冷却效果的影响规律，发现高温非平衡流条件下推进剂微射流冷却由边界层排挤、多相催化弱化两个基本过程主导：（1）低温微射流喷出对边界层产生排挤作用，改变边界层剖面形态，降低紧邻壁面处的温度法向梯度，从而降低壁面法向导热，实现冷却；（2）低温氧分子工质微射流排挤近壁氧原子，弱化氧催化效应，导致催化热降低。参数化研究结果表明：质量流量不变，增大射流孔大小，降热率与冷却范围均下降；射流孔面积不变，增大微射流速度，降热率与冷却范围增大；质量流量不变，减小孔间距，展向平均降热率峰值减小，但孔下游冷却范围增大，呈现较均匀的冷却效果。以上研究可对未来微射流冷却主动热防护的设计与优化提供重要的理论支撑和技术参考。

Abstract

During high-speed flight

the aircraft can utilize its own propellant to cool through the micro-hole jet to achieve active thermal protection. However

under high-temperature non-equilibrium conditions

the interaction between the compressible external flow and micro-jets involves complex processes including jet extrusion

mixing

and reactions

making the dominant mechanisms and influencing factors of micro-jet cooling highly intricate. In this study

a viscous wall boundary model for micro-jets was established

and numerical simulations of high-temperature non-equilibrium flow fields under micro-jet effects were conducted. The influence of jet hole diameter

velocity

and spacing on cooling performance were investigated. The simulations reveal the impact mechanisms of micro-jets on chemical reaction boundary layers

wall heterogeneous catalysis

and aerodynamic heating characteristics. The findings indicate that propellant micro-jet cooling under high-temperature non-equilibrium flow conditions is dominated by two key processes: boundary layer crowding and heterogeneous catalytic weakening. Specifically

the low-temperature micro-jet ejection crowds the boundary layer

altering its profile and reducing the temperature gradient near the wall

thus decreasing wall-normal heat conduction and achieving cooling. Additionally

the crowding-out effect of the low-temperature micro-jet promotes the outward displacement of near-wall O atoms

weakening the oxygen catalytic effect and reducing catalytic heat. Further parametric study shows that when the mass flow rate is constant

the heat reduction rate and cooling range decrease with the increase of jet hole size. When the area of the jet hole is constant

the micro-jet velocity is increased

and the heat reduction rate and cooling range are increased. When the mass flow rate is constant and the hole spacing is reduced

the peak value of the spanwise average heat reduction rate decreases

but the cooling range downstream of the hole increases

showing a more uniform cooling effect. These findings provide crucial theoretical support and technical guidance for the design and optimization of active thermal protection systems utilizing micro-jet cooling in future high-speed vehicles.

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