基于动态重叠网格的折叠翼展开过程非定常气动加热数值模拟

何绍荃; 石友安; 何琨; 李少壮; 姚杰

doi:10.7638/kqdlxxb-2025.0050

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基于动态重叠网格的折叠翼展开过程非定常气动加热数值模拟

研究论文 | 更新时间：2026-05-28

- 基于动态重叠网格的折叠翼展开过程非定常气动加热数值模拟
- Unsteady aerodynamic thermal numerical simulation of folding wing deployment process based on dynamic overset grid
- 空气动力学学报 2025年43卷第8期页码：59-73
- 作者机构：
  
  中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
- 作者简介：
  
  何绍荃（1999—），男，新疆乌鲁木齐人，硕士研究生，研究方向：空气动力学. E-mail：2634571661@qq.com
  石友安*，副研究员，研究方向：飞行器气动热与热防护. E-mail：youanshi11@sian.com
- 基金信息：
  
  国家自然科学基金（52276168）;高层次人才计划项目（2021-93，2021-326，2023-36）
- DOI：10.7638/kqdlxxb-2025.0050
  中图分类号： V211.3
- 纸质出版：2025
- 稿件说明：
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何绍荃, 石友安, 何琨, 等. 基于动态重叠网格的折叠翼展开过程非定常气动加热数值模拟[J]. 空气动力学学报, 2025, 43(8): 59−73.

HE Shaoquan, SHI Youan, HE Kun, et al. Unsteady aerodynamic thermal numerical simulation of folding wing deployment process based on dynamic overset grid[J]. 2025, 43(8): 59-73.
何绍荃, 石友安, 何琨, 等. 基于动态重叠网格的折叠翼展开过程非定常气动加热数值模拟[J]. 空气动力学学报, 2025, 43(8): 59−73. DOI： 10.7638/kqdlxxb-2025.0050

HE Shaoquan, SHI Youan, HE Kun, et al. Unsteady aerodynamic thermal numerical simulation of folding wing deployment process based on dynamic overset grid[J]. 2025, 43(8): 59-73. DOI： 10.7638/kqdlxxb-2025.0050.

摘要

相比于传统高速飞行器，折叠翼飞行器除了面临常规固定翼的气动加热问题外，还面临翼展开过程中带来的局部热扰动问题，对防热设计提出严峻挑战。针对折叠翼飞行器动态展开过程中的气动热环境特性，建立了基于刚体运动理论和动态重叠网格方法的非定常数值模拟方法。通过构建折叠翼简化模型，系统分析了翼面展开过程中的非定常流场演化特征及其气动加热规律。研究结果表明：与准定常仿真计算结果相比，两种方法得到的热流分布总体上基本一致，但是在局部存在由非定常热效应产生的热流差异：随着折叠翼面展开，翼尖和翼中部处非定常热效应凸显，翼尖处热扰动与当地线速度较大有关，翼中部处热扰动与时变的波系干扰和热累积有关；飞行攻角对大折叠角度状态下翼前缘热流影响较为明显，攻角–10°与10°的热流在相同位置的差值可达

2055

kW/m

；飞行马赫数减小，翼前缘受到的激波干扰强度减弱，翼前缘热流分布的起伏程度也相应减弱。本研究揭示了折叠翼动态展开过程中的关键热环境特征，为高速变体飞行器的防热设计提供了理论依据。

Abstract

Folding wings are increasingly being adopted to expand aircraft flight envelopes due to their capability to increase the lift-drag ratio and payload capacity. However

compared with traditional fixed-wing aircraft

this configuration not only inherits the aerodynamic heating problems associated with fixed wings but also introduces extra localized thermal disturbance during the wing deployment

imposing a severe challenge to thermal protection design. In this paper

we propose

a method for simulating the unsteady aerodynamic heating of a simplified folding-wing aircraft model during wing deployment using dynamic overset grids. The unsteady aerodynamic heating environment during the deployment of the folding wing is numerically investigated using the newly developed unsteady method and the conventional quasi-steady method

focusing on the unsteady flow fields around a rotating folding wing and the variation trend of the aerodynamic heating during the deployment process as well as the dependence on the freestream condition. The heat flux distributions obtained by the two methods are generally consistent

but local distributions in heat flux arise from unsteady thermal effects: pronounced unsteady thermal effects manifest at both the wingtip and mid-span regions during the folding process. The thermal disturbances at the wingtip are related to the strong local linear velocity

while that at the mid-span is associated with time-varying wave interference and heat accumulation. The flight angle of attack has a more pronounced effect on the heat flux at the wing leading edge under large folding angle configurations; the difference in heat flux between angle of attack of -10° and 10° at the same location can reach 2055kW/m

. As the flight Mach number decreases

the intensity of shock wave interference acting on the wing leading edge weakens

and the magnitude of fluctuations in the heat flux distribution at the wing leading edge correspondingly diminishes.

关键词

Keywords

references

WILLIANS C. The first five flights entry heating data series volume 1: An overview: NASA-CR-171820[R]. California, USA: National aeronautics and space administration, 1984. https://ntrs.nasa.gov/citations/19850007468

JHA A K, KUDVA J N. Morphing aircraft concepts, classifications, and challenges[C]//Proc of the Smart Structures and Materials 2004: Industrial and Commercial Applications of Smart Structures Technologies, San Diego, CA: SPIE, 2004: 544212. doi: 10.1117/12.544212

WEISSAAR T A. Morphing aircraft technology—new shapes for aircraft design[R]. Meeting Proceedings RTO-MP-AVT-141, Neuilly-sur-Seine, France: RTO, 2006. http://www.rto.nato.int/abstracts.asp.

BARBARINO S, BILGEN O, AJAJ R M, et al. A review of morphing aircraft[J]. Journal of Intelligent Material Systems and Structures, 2011, 22(9): 823−877. doi: 10.1177/1045389x11414084

MCGOWAN A-M R, VICROY D D, BUSAN R C, et al. Perspectives on highly adaptive or morphing aircraft[C]//Proc of the RTO MP-AVT-168: NASA Langley Research Center, Hampton, VA. USA, 2009. https:///ntrs.nasa.gov/citations/20090017845

FANO D, POGGIE J, BLAISDELL G A. Aerodynamic heating in missile-fin interaction region[C]//Proc of the AIAA Scitech 2020 Forum, Orlando, FL. Reston, Virginia: AIAA, 2020: 0583. doi: 10.2514/6.2020-0583

ZHANG W, GUO X G, CAO D X. Investigation of a folding wing aircraft using dynamic analysis simulation and experimental method[J]. Science Technology Review, 2011, 29(20): 18−22(in Chinese). doi: 10.3981/j.issn.1000-7857.2011.20.001

LOOMIS M, VENKATAPATHY E, PAPADOPOULOS P, et al. Aeroheating and aerodynamic CFD validation and prediction for the X-38 program[C]//Proc of the 32nd Thermophysics Conference, Atlanta, GA. Reston, Virginia: AIAA, 1997: 2478. doi: 10.2514/6.1997-2478

HOLLIS B R, HORVATH T J, BERRY S A, et al. X-33 computational aeroheating predictions and comparisons with experimental data[J]. Journal of Spacecraft and Rockets, 2001, 38(5): 658−669. doi: 10.2514/2.3751

HOLLIS B, BERRY S, HORVATH T. X-33 turbulent aeroheating measurements and predictions[C]//Proc of the AIAA Atmospheric Flight Mechanics Conference and Exhibit, Monterey, California. Reston, Virginia: AIAA, 2002: 4700. doi: 10.2514/6.2002-4700

YANG Z B, JIANG J L. Temperature field numerical simulation of multi-wing missiles of aeroheating[J]. Aeronautical Computing Technique, 2014, 44(1): 48−51(in Chinese). doi: 10.3969/j.issn.1671-654X.2014.01.013

FAN G F, LI Q, CAO X L, et al. Numerical study on aerodynamic loads of a high-speed aircraft folding wing in its deploying procedure[J]. Physics of Gases, 2017, 2(6): 48−53(in Chinese). doi: 10.19527/j.cnki.2096-1642.2017.06.006

GUO Q T, ZHANG L P, CHANG X H, et al. Numerical simulation of dynamic aerodynamic characteristics of a morphing aircraft[J]. Acta Aerodynamica Sinica, 2011, 29(6): 744−750(in Chinese). doi: 10.3969/j.issn.0258-1825.2011.06.010

LI T L, LIN S, XIONG X W, et al. Summary and enlightenment of Russian hypersonic weapons and equipment development[J]. Aerodynamic Missile Journal, 2021(12): 51−56(in Chinese). doi: 10.16338/j.issn.1009-1319.20210134

WANG F J. Computational fluid dynamics analysis: Principle and application of CFD software[M]. Beijing: Tsinghua University Press, 2004: 144−145(in Chinese).

MA W P, LU Z H, YUAN W, et al. Parallel algorithm for multi-block overset grid assembly and applications[J]. Application Research of Computers, 2016, 33(3): 788−793,809(in Chinese). doi: 10.3969/j.issn.1001-3695.2016.03.033

CHANG X H, MA R, ZHANG L P. Parallel implicit hole-cutting method for unstructured overset grid[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(6): 121780(in Chinese). doi: 10.7527/S1000-6893.2017.21780

BONET J, PERAIRE J. An alternating digital tree (ADT) algorithm for 3D geometric searching and intersection problems[J]. International Journal for Numerical Methods in Engineering, 1991, 31(1): 1−17. doi: 10.1002/nme.1620310102

LI P, CHEN J Q, DING M S, et al. Framework design of NNW-HyFLOW hypersonic flow simulation software[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 625718(in Chinese). doi: 10.7527/S1000-6893.2021.25718

CHEN Q. Numerical simulation of aircraft pneumatic/control integrated maneuvering flight[D]. Mianyang: China Aerodnamics Research and Development Center, 2016(in Chinese).

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