迈向智能驱动的高超声速飞行器边界层主动质量引射减阻降热研究新范式

  • 刘延芳 ,
  • 王洪悦 ,
  • 鄂羽佳 ,
  • 齐乃明
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  • 哈尔滨工业大学

收稿日期: 2025-04-28

  修回日期: 2025-08-21

  网络出版日期: 2025-08-28

基金资助

大型在轨可组装平台机热控制等多功能动态重构及验证技术

Towards a new paradigm of intelligence-driven active mass ejection drag and heat reduction research for hypersonic vehicle boundary layer

  • LIU Yan-Fang ,
  • WANG Hong-Yue ,
  • E Yu-Jia ,
  • QI Nai-Ming
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Received date: 2025-04-28

  Revised date: 2025-08-21

  Online published: 2025-08-28

摘要

新一代高超声速飞行器因高马赫数、长时间飞行、过载大的特性,导致其面临着极端气动加热与复杂力学环境,对减阻与降热性能提出了严峻挑战。本文聚焦高超声速飞行器边界层主动质量引射减阻降热研究方法,系统评述该领域的研究进展及其范式转型路径。首先,全面梳理了传统研究范式——实验、理论与数值方法的发展现状,并揭示核心挑战:实验数据稀疏性与多场耦合测量瓶颈、数值模拟的“精度-效率”权衡困境以及多尺度耦合建模理论与方法缺失。基于这些挑战,提出了以数据驱动、物理信息融合和多尺度耦合为核心的智能化科研新范式,并归纳了其技术分类与前沿进展。通过流体力学场景中的应用案例,深入分析了该新范式的创新机制及其在解决传统研究范式挑战中的优势和潜在应用思路。本文旨在通过对智能化科研新范式的深入洞察,激发研究人员的兴趣,推动高超声速飞行器减阻降热研究的持续发展与范式跃迁,为后续探索新一代高超声速飞行器的减阻降热性能提升提供重要的参考与启示。

本文引用格式

刘延芳 , 王洪悦 , 鄂羽佳 , 齐乃明 . 迈向智能驱动的高超声速飞行器边界层主动质量引射减阻降热研究新范式[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32171

Abstract

Due to the characteristics of high Mach number, long flight time and large overload, the new generation of hypersonic vehi-cle is facing extreme aerodynamic heating and complex mechanical environment, which poses a serious challenge to drag reduction and heat reduction performance. This paper focuses on the research methods of active mass ejection drag and heat reduction in the boundary layer of hypersonic vehicles, and systematically reviews the research progress and paradigm trans-formation path in this field. Firstly, the development status of traditional research paradigm-experiment, theory and numerical method is comprehensively reviewed, and the core challenges are revealed : the bottleneck of experimental data sparsity and multi-field coupling measurement, the ' precision-efficiency ' trade-off dilemma of numerical simulation, and the lack of mul-ti-scale coupling modeling theory and method. Based on these challenges, a new paradigm of intelligent scientific research with data-driven, physical information fusion and multi-scale coupling as the core is proposed, and its technical classification and frontier progress are summarized. Through the application cases in the fluid mechanics scenario, the innovation mecha-nism of the new paradigm and its advantages and potential application ideas in solving the challenges of traditional research paradigms are deeply analyzed. The purpose of this paper is to stimulate the interest of researchers through in-depth insight into the new paradigm of intelligent scientific research, promote the sustainable development and paradigm transition of drag reduction and heat reduction research of hypersonic vehicles, and provide important reference and inspiration for the subse-quent exploration of the improvement of drag reduction and heat reduction performance of the new generation of hypersonic vehicles.

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