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论文:2016,Vol:34,Issue(1):1-10 |
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引用本文： |
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叶坤, 叶正寅, 屈展. 高超声速热气动弹性中结构热边界影响研究[J]. 西北工业大学学报 |
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Ye Kun, Ye Zhengyin, Qu Zhan. Effect of Structural Thermal Boundary on Areothermoelasticity forHypersonic Vehicles[J]. Northwestern polytechnical university |
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| 高超声速热气动弹性中结构热边界影响研究 |
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| 叶坤, 叶正寅, 屈展 |
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| 西北工业大学 航空学院, 陕西 西安 710072 |
| 摘要: |
| 基于分层求解思路研究结构热边界对高超声速飞行器全动舵面和翼面结构热气动弹性特性的影响。首先,基于CFD求解N-S方程得到热环境,在此基础上进行结构的瞬态热传导分析,进而分析结构由于温度梯度产生的热应力和温度对材料属性的影响下的模态固有特性,然后将结构振型插值到气动网格上,最后,通过求解Euler方程得到流动参数,基于CFD的当地流活塞理论计算气动力,在状态空间中进行了气动弹性分析。通过对4组结构模型进行热气动弹性分析,研究了结构热边界对舵面和翼面热气动弹性的影响,结果表明:对全动舵面而言,结构热边界首先会影响舵轴处结构的热传导过程及温度分布,进而对结构固有频率、频率间距、颤振速度以及颤振频率的变化产生的影响达到了16%。对翼面而言,结构热边界对结构固有频率、频率间距、颤振速度以及颤振频率的变化产生的影响约为1%。因此,工程实际当中,进行热气动弹性分析时应采用合理的结构热边界。 |
| 关键词:
高超声速
热气动弹性
结构热边界
气动加热
当地流活塞理论
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| Effect of Structural Thermal Boundary on Areothermoelasticity forHypersonic Vehicles |
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| Ye Kun, Ye Zhengyin, Qu Zhan |
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| College of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China |
| Abstract: |
| The effect of structural thermal boundary on aerothermoelasticity of hypersonic all-movable control surface/wing is studied on the basis of hierarchical solution process. On the basis of CFD technology, Navier-Stokes equation is solved to get the thermal environment. And then transient thermal conduction of structure is analyzed. Then structural modal is analyzed under the effect of structure's thermal stress caused by temperature gradient and material property decrease caused by high temperature, then structural mode is interpolated to the aerodynamic grid; Finally, Euler equation is solved to get flow parameter, and based on CFD local piston theory, aerothermoelasticity is analyzed in state space. Through analyzing aerothermoelasticity of four different structural models, the effect of the structural thermal boundary on aerothermoelasticity of all-movable control surface/wing is analyzed. The results show that: for the control surface in this paper, the structural thermal boundary would firstly affect the heat transfer process and temperature distribution of shaft structure. The effect on the variation of the natural frequency, frequency spacing, flutter velocity and flutter frequency is about 16%. For the wing in this paper, The effect on the variation of the natural frequency, frequency spacing, flutter velocity and flutter frequency is about 1%. Therefore, in practical engineering, reasonable thermal boundary should be used while analyzing aerothermoelasticity. |
| Key words:
aerodynamic
configurations
aerodynamic heating
aeroelasticity
angle of attack
boundary conditions
calculations
computational fluid dynamics
control surfaces
Euler equations
flow fields
flow velocity
flowcharting
flutter(aerodynamics)
heat transfer
hypersonic vehicles
materials properties
mathematical models
matrix algebra
mesh generation
modal analysis
Navier Stokes equatons
Prandtl number
radial basis function networks
structural dynamics
temperature distribution
turbulence models
vectors
velocity
wings
aerothermoelasticity
flutter frequency
flutter velocity
local flow piston theory
structural thermal boundary
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| 收稿日期: 2015-09-29
修回日期:
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| DOI: |
| 基金项目: 国家自然科学基金(91216202)资助 |
| 通讯作者:
Email： |
| 作者简介: 叶坤(1987-),西北工业大学博士研究生,主要从事高超声速热气动弹性研究。
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| 作者相关文章 |
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| 叶坤 在本刊中的所有文章 |
| 叶正寅 在本刊中的所有文章 |
| 屈展 在本刊中的所有文章 |
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