Bionic phase-change transpiration cooling structure for morphing flight: Heat-mass transfer mechanism and modeling

JING Xize; SHI Shengbo; LI Maoyuan; LIANG Jun

doi:10.7638/kqdlxxb-2025.0099

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Bionic phase-change transpiration cooling structure for morphing flight: Heat-mass transfer mechanism and modeling

更新时间：2026-05-28

- Bionic phase-change transpiration cooling structure for morphing flight: Heat-mass transfer mechanism and modeling
- Vol. 43, Issue 7, Pages: 83-92(2025)
- 作者机构：
  
  1. 西北工业大学航天学院,西安,710072
  2. 北京机电工程总体设计部,北京,100854
  3. 北京理工大学先进结构技术研究院,北京,100081
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2025.0099
  CLC： V19;V435+.14;TB381
- Published：2025
- 稿件说明：
移动端阅览
荆希泽, 时圣波, 李茂源, 等. 面向变体飞行的仿生相变发汗冷却结构：热质传递机理及模型[J]. 空气动力学学报, 2025, 43(7): 83−92.

JING Xize, SHI Shengbo, LI Maoyuan, et al. Bionic phase-change transpiration cooling structure for morphing flight: Heat-mass transfer mechanism and modeling[J]. 2025, 43(7): 83-92.
荆希泽, 时圣波, 李茂源, 等. 面向变体飞行的仿生相变发汗冷却结构：热质传递机理及模型[J]. 空气动力学学报, 2025, 43(7): 83−92. DOI： 10.7638/kqdlxxb-2025.0099

JING Xize, SHI Shengbo, LI Maoyuan, et al. Bionic phase-change transpiration cooling structure for morphing flight: Heat-mass transfer mechanism and modeling[J]. 2025, 43(7): 83-92. DOI： 10.7638/kqdlxxb-2025.0099.

摘要

新一代航天运输系统具备跨空域、宽速域、重复使用、智能飞行等技术特征，传统刚性热防护系统因形变能力有限，难以满足高温变构工况下的热防护需求。借鉴植物叶脉脉序输送路径，融合柔性材料大变形特性与微通道毛细驱动机制，提出了一种自适应-自驱动柔性相变冷却结构，实现了冷却过程的高效性和均匀性。开展了地面热考核试验，在170  kW/m

热流下，结构可将壁面温度维持在130℃，验证了自驱动发汗冷却的可行性。建立了液-气-固多相传热传质耦合分析模型，阐明了冷却通道几何参数对结构冷却效果的影响规律：相比通道直径，通道角度对结构冷却效率的影响更显著，冷却效率随角度增加而降低。重点研究了典型变构工况下结构变形与温度响应、冷却消耗量之间的关联关系，发现大变形下结构表面温度波动5%，冷却剂流量对通道直径呈现高敏感性。本研究可为新一代变构飞行器热防护系统设计提供新的技术路径。

Abstract

Next-generation space transportation systems exhibit advanced technical features

including trans-atmospheric flight

broad speed regimes

reusability

and intelligent operation. However conventional rigid thermal protection systems are constrained by limited deformation capabilities

preventing them from simultaneously fulfilling thermal insulation and structural morphing requirements under high-temperature and large-deformation scenarios. To address this challenge

an adaptive-self-driven flexible phase-change transpiration cooling str

ucture was proposed

inspired by the fractal transport pathways of leaf venation. This design integrated the large-strain capacity of flexible materials with capillary-driven microchannel mechanisms

achieving efficient and uniform cooling performance. Ground thermal testing under moderate heat flux conditions (170 kW/m

) demonstrated the structure's self-driving capability and cooling efficiency

with surface temperatures maintained below 130°C

validating the feasibility of phase-change transpiration cooling. A coupled heat and mass transfer model was developed by integrating surface tension theory in microchannels with liquid-gas-solid multi-phase heat transfer mechanisms

quantifying the influence of geometric parameters (e.g.

channel diameter and branching angles) on cooling effectiveness. Model predictions aligned well with experimental data (error 10%)

providing theoretical support for the parametric design of flexible phase-change cooling structures. The correlation between structural deformation range

temperature response

and coolant consumption under representative morphing scenarios was systematically analyzed. Results showed that surface temperature fluctuations remained 5%

while coolant flow responses exhibited nonlinear characteristics

highlighting the structure's robust dynamic regulation capacity and offering new insights for flexible TPS design. This work provides an innovative technical pathway for thermal protection system design in next-generation morphing aerospace vehicles

enabling reliable operation in extreme high-temperature and structural deformation environments.

关键词

Keywords

references

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