Research on Construction and Experimental Verification of Heat Transfer-PyrolysisModel for Phenolic Resin-Based Composite Materials

LI Dong; LIU Yunzhao; CHEN Xin; YANG Yunhua; LIU Hongyu

doi:10.7652/xjtuxb202408006

您当前的位置：

首页 >

文章列表页 >

Research on Construction and Experimental Verification of Heat Transfer-PyrolysisModel for Phenolic Resin-Based Composite Materials

更新时间：2025-07-28

- Research on Construction and Experimental Verification of Heat Transfer-PyrolysisModel for Phenolic Resin-Based Composite Materials
- Vol. 58, Issue 8, Pages: 49-59(2024)
- 作者机构：
  
  1. 西安交通大学热流科学与工程教育部重点实验室,西安,710049
  2. 航天材料及工艺研究所先进功能复合材料技术重点实验室,北京,100076
  3. 中国运载火箭技术研究院空间物理重点实验室,北京,100076
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202408006
  CLC： TK121
- Online First：10 August 2024，
  
  Published：2024
- 稿件说明：
移动端阅览
LI Dong, LIU Yunzhao, CHEN Xin, et al. Research on Construction and Experimental Verification of Heat Transfer-PyrolysisModel for Phenolic Resin-Based Composite Materials[J]. 2024, 58(8): 49-59.
DOI：

LI Dong, LIU Yunzhao, CHEN Xin, et al. Research on Construction and Experimental Verification of Heat Transfer-PyrolysisModel for Phenolic Resin-Based Composite Materials[J]. 2024, 58(8): 49-59. DOI： 10.7652/xjtuxb202408006.

摘要

针对现有酚醛树脂基复合材料传热-热解模型忽略产物气体渗流可压缩效应的问题

建立了考虑热解气体可压缩流动的酚醛树脂基复合材料传热-热解模型。通过可压缩压力耦合方程组半隐式方法

求解完整的Navier-Stocks方程

以实现对热解气体可压缩流动的模拟

而非现有模型普遍采用的不可压缩Darcy方程; 改进了热解度的计算方式

提高了孔隙动态演化时热解区域材料物性插值的准确性。以一种酚醛树脂基复合材料——酚醛气凝胶复合材料为例

通过热质量试验数据

推导了热解动力学模型。测量了完全热解前后材料的关键计算输入参数。通过10 kPa低气压热试验测得了1 000 ℃加热下材料的背温。结果表明:酚醛气凝胶复合材料存在200～550 ℃、550～800 ℃、800～1 200 ℃共3个主要热解区间; 完全热解前、后

材料孔隙率分别为0.568、0.484

渗透率分别为10

-13

、10

-12

-2

。计算模型与试验结果吻合较好

最大相对误差为9.2%; 热解气体向舱内渗流形成富集区域的现象对材料隔热有负面影响

但低导热系数和产物气体热阻塞作用仍使材料具备优异的防隔热性能。

Abstract

A heat transfer-pyrolysis model considering the compressible flow of pyrolysis gas was established for phenolic resin-based composite materials to address the issue of neglecting the compressible effect of product gas permeation in the existing models. In order to simulate the compressible flow of pyrolysis gas

the compressible semi-implicit method for pressure linked equations(SIMPLE)was employed to solve the complete Navier-Stocks

equations

rather than the incompressible Darcy equation commonly used in the existing models. The calculation method of pyrolysis degree was improved to enhance the accuracy of material property interpolation in the pyrolysis region during the dynamic evolution of pore structure. A phenolic resin-based composite material

phenolic aerogel composite material

was taken as an example. The pyrolysis kinetics model was derived from thermogravimetric experimental data. Key calculation input parameters of the material are measured before and after complete pyrolysis. The back temperature of the material under heating at 1 000 ℃ was measured through a 10 kPa low-pressure thermal test. The results indicated that the phenolic aerogel composite material had three main pyrolysis intervals: 200—550 ℃

550—800 ℃

and 800—1 200 ℃. Before complete pyrolysis

the porosity was 0.568

and the permeability was 10

-13

-2

. After complete pyrolysis

these values were 0.484

and 10

-12

-2

respectively. The calculation model showed good agreement with experimental results

with a maximum relative error of 9.2%. The phenomenon of pyrolysis gas permeating into the cabin and forming enrichment areas negatively affected the thermal insulation of the material. However

the low thermal conductivity and the thermal blocking effect of product gas still endowed the material with excellent thermal insulation performance.

关键词

Keywords

references

郭珂, 秦绪国, 杨依峰, 等. 再入飞行器关键技术发展与展望 [J]. 中国航天, 2023(8): 16-22.

GUO Ke, QIN Xuguo, YANG Yifeng, et al.Development and prospect of key technologies for re-entry vehicles [J]. Aerospace China, 2023(8): 16-22.

UYANNA O, NAJAFI H. Thermal protection systems for space vehicles: a review on technology development, current challenges and future prospects [J]. Acta Astronautica, 2020, 176: 341-356.

冯志海, 师建军, 孔磊, 等. 航天飞行器热防护系统低密度烧蚀防热材料研究进展 [J]. 材料工程, 2020, 48(8): 14-24.

FENG Zhihai, SHI Jianjun, KONG Lei, et al. Research progress in low-density ablative materials for thermal protection system of aerospace flight vehicles [J]. Journal of Materials Engineering, 2020, 48(8): 14-24.

赵云峰, 潘玲英. 航天先进结构复合材料及制造技术研究进展 [J]. 宇航材料工艺, 2021, 51(4): 29-36.

ZHAO Yunfeng, PAN Lingying. Research progress of aerospace advanced polymer matrix composites and manufacturing technology [J]. Aerospace Materials Technology, 2021, 51(4): 29-36.

FAHY W P, CHANG A, WU H, et al. Recent developments of ablative thermal protection systems for atmospheric entry [C]//AIAA Scitech 2021 Forum. Reston, VA, USA: AIAA, 2021: AIAA 2021-1474.

STACKPOOLE M, GASCH M, VENKATAPATHY R, et al. The state of the art: ablative thermal protection systems [EB/OL].(2022-03-24)[2023-11-12]. https://ntrs.nasa.gov/citations/20220004752.

程海明, 洪长青, 张幸红. 低密度烧蚀材料研究进展 [J]. 哈尔滨工业大学学报, 2018, 50(5): 1-11.

CHENG Haiming, HONG Changqing, ZHANG Xinghong.An overview on low-density ablators [J]. Journal of Harbin Institute of Technology, 2018, 50(5): 1-11.

师建军, 孔磊, 王筠, 等. 先进树脂基轻质烧蚀防热复合材料 [J]. 西北工业大学学报, 2018, 36(S1): 93-97.

SHI Jianjun, KONG Lei, WANG Yun, et al. Advanced lightweight ablative thermal protection composites based on novel hybrid resins [J]. Journal of Northwestern Polytechnical University, 2018, 36(S1): 93-97.

谢永旺, 夏雨, 许学伟, 等. 航天飞行器热防护系统研究概况及其发展趋势 [J]. 空天技术, 2022(4): 73-86.

XIE Yongwang, XIA Yu, XU Xuewei, et al. Research status of thermal protection system for spacecraft and its development trend [J]. Aerospace Technology, 2022(4): 73-86.

HUANG Jie, GUO Jin, HUANG Haiming, et al. Components of thermal protection mechanism of carbon/phenolic composites exposed to severe aerodynamic heat [J]. Polymer Composites, 2023, 44(1): 136-147.

张斌, 许爱军, 代国宝, 等. 美国X-43A高超声速飞行器先进制造技术分析 [J/OL]. 战术导弹技术: 1-5[2024-01-09]. https://doi.org/10.16358/j.issn.1009-1300.20220567.

ZHANG Bin, XU Aijun, DAI Guobao, et al. Analysis of advanced manufacturing technology for X-43A hypersonic vehicle in USA [J/OL]. Tactical Missile Technology: 1-5[2024-01-09]. https://doi.org/10.16358/j.issn.1009-1300.20220567.

国义军, 石卫波, 曾磊, 等. 高超声速飞行器烧蚀防热理论与应用 [M]. 北京: 科学出版社, 2019.

MCMANUS H L N, SPRINGER G S. High temperature thermomechanical behavior of carbon-phenolic and carbon-carbon composites: Ⅰ Analysis [J]. Journal of Composite Materials, 1992, 26(2): 206-229.

HARPALE A, SAWANT S, KUMAR R, et al. Ablative thermal protection systems: pyrolysis modeling by scale-bridging molecular dynamics [J]. Carbon, 2018, 130: 315-324.

WANG Yeqing, RISCH T K, KOO J H. Assessment of a one-dimensional finite element charring ablation material response model for phenolic-impregnated carbon ablator [J]. Aerospace Science and Technology, 2019, 91: 301-309.

LI Weijie, GE Jingran, LIANG Jun. Influence factors on the multi-field coupling performances of charring ablators on the basis of a mesoscopic ablation model [J]. Applied Thermal Engineering, 2019, 161: 114126.

GUO Jin, HUANG Jie, HUANG Haiming, et al. Pyrolysis layer model of polymer matrix composites with heating rate and pressure [J]. Thermal Science and Engineering Progress, 2022, 28: 101068.

张军, 李伟, 方国东, 等. 树脂基防隔热复合材料高温响应分析方法研究进展 [J]. 宇航学报, 2020, 41(6): 739-748.

ZHANG Jun, LI Wei, FANG Guodong, et al. Review of high temperature response analysis of resin matrix thermal protection and insulation composites [J]. Journal of Astronautics, 2020, 41(6): 739-748.

陶文铨. 数值传热学 [M]. 2版. 西安: 西安交通大学出版社, 2001.

时圣波, 梁军, 刘志刚, 等. 高硅氧/酚醛复合材料烧蚀环境下的吸热机理 [J]. 固体火箭技术, 2013, 36(1): 113-118.

SHI Shengbo, LIANG Jun, LIU Zhigang, et al. Endothermic mechanism of silica/phenolic composite under ablative environment [J]. Journal of Solid Rocket Technology, 2013, 36(1): 113-118.

严蛟, 邝旻翾, 胡宏林, 等. 间苯二酚-甲醛基酚醛/碳气凝胶微观结构调控研究进展 [J]. 材料导报, 2022, 36(12): 205-214.

YAN Jiao, KUANG Minxuan, HU Honglin, et al. Research progress in tailoring the microstructure of resorcinol-formaldehyde organic/carbon aerogel [J]. Materials Reports, 2022, 36(12): 205-214.

师建军, 孔磊, 左小彪, 等. 酚醛/SiO2双体系凝胶网络结构杂化气凝胶的制备与性能 [J]. 高分子学报, 2018(10): 1307-1314.

SHI Jianjun, KONG Lei, ZUO Xiaobiao, et al. Preparation of PR/SiO2 hybrid phenolic aerogel with bi-component gel networks [J]. Acta Polymerica Sinica, 2018(10): 1307-1314.[23] BAHRAMIAN A R, KOKABI M, FAMILI M H N, et al. Ablation and thermal degradation behaviour of a composite based on resol type phenolic resin: Process modeling and experimental [J]. Polymer, 2006, 47(10): 3661-3673.

时圣波. 高硅氧/酚醛复合材料的烧蚀机理及热-力学性能研究 [D]. 哈尔滨: 哈尔滨工业大学, 2013.

SHI Shengbo, WANG Yifan, YAN Li, et al. Coupled ablation and thermal behavior of an all-composite structurally integrated thermal protection system: fabrication and modeling [J]. Composite Structures, 2020, 251: 112623.

BESSIRE B K, LAHANKAR S A, MINTON T K. Pyrolysis of phenolic impregnated carbon ablator(PICA)[J]. ACS Applied Materials Interfaces, 2015, 7(3): 1383-1395.

LI Weijie, HUANG Haiming, TIAN Ye, et al. A nonlinear pyrolysis layer model for analyzing thermal behavior of charring ablator [J]. International Journal of Thermal Sciences, 2015, 98: 104-112.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Influence of Structural Parameters on the Summer Operational Characteristics of a Three-Tower-in-One Indirect Air-Cooling System

Numerical Simulation of Heat-Moisture Barrier Performance of a Horizontal Air Curtain in Cold Storage

Study on the Thermodynamic Properties in the Anomalous Region of Supercritical Water

Energy Efficiency Optimization of the Cryogenic Air Separation Process for Electronic-Grade Ultra Pure Nitrogen

Integrated and Joint Design Optimization of Centrifugal Compressor Impeller and Casing Treatment at Multiple Working Points

Related Author

No data

Related Institution

No data

⁰