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基于三维升力线方法的大变形飞机非线性
发表时间：2013-08-15 浏览量：1793 下载量：757
| 全部作者： | 谢长川，刘燚，杨超 |
| 作者单位： | 北京航空航天大学航空科学与工程学院 |
| 摘 要： | 大展弦比飞机由于几何非线性现象显著，基于小变形假设的线性气动弹性分析方法已不再适用。为此将升力线方法推广到三维情况，用于计算空间任意形状气动面的气动力。结合推广的多维曲面插值方法，解决大变形飞机曲面气动力与空间变形结构之间的信息传递问题。针对大变形机翼的几何非线性特点，推导出非线性的静气动弹性全机配平方程，并用简单算例与线性方法进行对比验证，突出非线性计算结果的特点。基于以上理论所建立的针对大变形飞机的静气动弹性载荷及配平分析体系，其方法简单快速，应用对象广泛，在初步设计和快速分析中有很大的应用前景。 |
| 关 键 词： | 流体-固体耦合振动；气动弹性配平；几何非线性；曲面气动力；飞行载荷 |
| Title： | Nonlinearity static aeroelastic trim analysis of flexible aircraft based on 3D lifting-line theory |
| Author： | XIE Changchuan, LIU Yi, YANG Chao |
| Organization： | School of Aeronautics Science and Engineering, Beihang University |
| Abstract： | Since the geometric nonlinearity of the flexible aircraft is significant, the traditional aeroelastic analysis method for linearity aeroelastic trim based on small deformation hypothesis is no longer available. In this paper, a new method based on the 3D lifting-line theory was applied to compute the nonplanar steady aerodynamics. Surface spine interpolation method was responsible for the structure/aerodynamics coupling. Moreover, the nonlinear finite element method gave the final nonlinear deformation. By combing these creative methods and using the iterative computation based on rigid aircraft trim, the results considering the nonlinear effects were obtained and compared with the linear results. The results indicated that the new method was much more effective and reliable for the facts and therefore it was very suitable for the rapid and efficient analysis in the preliminary stage of very flexible aircraft design. |
| Key words： | fluid-soild coupled vibration; static aeroelasticity trim; geometric nonlinearity; nonplanar aerodynamics; flight loads |
| 发表期数： | 2013年8月第15期 |
| 引用格式： | 谢长川，刘燚，杨超. 基于三维升力线方法的大变形飞机非线性[J]. 中国科技论文在线精品论文，2013，6（15）：1464-1472. |
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