气动力热作用下飞行器结构分析的分区耦合CG/DG有限元方法

赵建宁; 魏东; 杜雁霞; 刘冬欢; 桂业伟

doi:10.7638/kqdlxxb-2021.0050

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气动力热作用下飞行器结构分析的分区耦合CG/DG有限元方法

研究论文 | 更新时间：2026-05-28

- 气动力热作用下飞行器结构分析的分区耦合CG/DG有限元方法
- A zonal coupled continuous/discontinuous Galerkin finite element method for vehicle structure analyses under aerodynamic force/heating effects
- 空气动力学学报 2022年40卷第2期页码：67-78
- 作者机构：
  
  1. 北京科技大学数理学院应用力学系,北京,100083
  2. 中国空气动力研究与发展中心,绵阳,621000
- 作者简介：
  
  赵建宁（1994-），男，河北张家口人，研究方向：结构热防护. E-mail：zhaojn_fastbetan@163.com
  刘冬欢*（1982-），男，副教授，研究方向：结构热防护. E-mail：liudh@ustb.edu.cn
- 基金信息：
  
  国家数值风洞工程（ NNW）
- DOI：10.7638/kqdlxxb-2021.0050
  中图分类号： V215.4
- 纸质出版：2022
- 稿件说明：
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赵建宁, 魏东, 杜雁霞, 等. 气动力热作用下飞行器结构分析的分区耦合CG/DG有限元方法[J]. 空气动力学学报, 2022, 40(2): 67−78.

ZHAO Jianning, WEI Dong, DU Yanxia, et al. A zonal coupled continuous/discontinuous Galerkin finite element method for vehicle structure analyses under aerodynamic force/heating effects[J]. 2022, 40(2): 67-78.
赵建宁, 魏东, 杜雁霞, 等. 气动力热作用下飞行器结构分析的分区耦合CG/DG有限元方法[J]. 空气动力学学报, 2022, 40(2): 67−78. DOI： 10.7638/kqdlxxb-2021.0050

ZHAO Jianning, WEI Dong, DU Yanxia, et al. A zonal coupled continuous/discontinuous Galerkin finite element method for vehicle structure analyses under aerodynamic force/heating effects[J]. 2022, 40(2): 67-78. DOI： 10.7638/kqdlxxb-2021.0050.

摘要

高超声速飞行器热防护结构中存在大量不同材料的装配界面，因此在结构热力耦合分析中会产生界面非完好接触、热力耦合等非线性效应。针对传统三维有限元方法在求解此类结构时存在的计算量大、计算效率低的问题，建立了适用于含搭接界面温度场和热力耦合分析的分区连续/间断伽辽金有限元方法，充分考虑材料非线性以及温度和应力相关的接触热阻对结构热力耦合响应的影响，并编制相应的有限元计算软件，形成适应于工程大规模计算的含多材料搭接界面结构的三维传热、热力耦合问题研究的高效高精度计算能力，为我国新型高超声速飞行器热气动弹性特性预测及安全评估等提供研究手段和技术支撑。

Abstract

Assembly interfaces between dissimilar materials widely exist in thermal protection structures of hypersonic aircrafts. The resulting imperfect contact and thermomechanical coupling need to be carefully considered in structural analyses. Since the traditional three-dimensional finite element method is computational expensive and inefficient

a new zonal coupled continuous/discontinuous Galerkin finite element method is established especially for the thermal and thermomechanical analyses of problems with dissimilar-material assembly interfaces. The effects of material nonlinearity

temperature

and stress-dependent thermal contact resistance to the structural thermomechanical coupling response are taken into account. In addition

an efficient and accurate finite element software suitable for large-scale engineering computations and three-dimensional thermal and thermomechanical coupling analyses of problems with dissimilar-material assembly interfaces is developed. This software provides a research tool and technical supports for the aerothermoelasticity prediction and safety evaluation of novel hypersonic aircrafts.

关键词

Keywords

references

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