| 大展弦比气弹机翼柔性非线性变形的气动力效应分析与风洞试验 |
| |
| 作者姓名： | 刘燚 许云涛 吕计男 |
| |
| 作者单位： | 北京机电工程研究院, 北京100074;中国航天空气动力技术研究院, 北京100074 |
| |
| 摘 要： | 从飞行器刚弹耦合动力学模型出发，引入柔性机翼准定常假设，建立大柔性飞行器非线性静气动弹性气动力方程，利用非线性迭代求解思路模拟了柔性飞行器的静气动弹性响应行为，开展了大展弦比飞机静气动弹性风洞试验验证，采用气动力有限基本解与机翼的耦合计算，发现了大柔性飞机大变形状态下载荷及结构变形形式随风速的变化规律.传统基于小变形假设的线性分析方法和刚体分析由于无法考虑气动面随结构变形的曲面气动力因素和结构变形后的非线性刚度特性，均与风洞试验存在一定的误差.对于大展弦比柔性飞机的非线性静气动弹性分析十分必要.
|
| 关 键 词： | 几何非线性 静气动弹性 大展弦比机翼 风洞试验 气动力计算 |
| 收稿时间： | 2019-09-18 |
Aerodynamic Analysis Based on Nonlinear Aeroelastic Large Deformation for Large Aspect Ratio Wing |
| |
| Affiliation: | 1.Beijing Electro-Mechanical Engineering Institute, Beijing 100074, China2.China Academy of Aerospace Aerodynamics, Beijing 100074, China |
| |
| Abstract: | The rigid/elastic coupling dynamic equations were utilized based on quasi-steady hypotheses to obtain the nonlinear static aeroelastic equations in this paper. Combined with nonplanar vortex lattice methods and nonlinear FEM, iterative methods were adopted to simulate the nonlinear static aeroelastic response. A wind tunnel test was implemented to reveal the nonlinear trends of loads and structural deformations. The linear static aeroelastic analysis cannot consider the structural geometry and non-planar effect when the deformation is large. Therefore, there are some differences compared with wind tunnel test and nonlinear analysis. For very flexible aircraft, the nonlinear static aeroelastic analysis is significant for accurate aerodynamic evaluation. |
| |
| Keywords: | |
| 本文献已被 万方数据 等数据库收录！ |
| 点击此处可从《》浏览原始摘要信息 |
|
点击此处可从《》下载全文 |
