柔性飞机大变形曲面气动力计算及配平分析  

NONPLANAR AERODYNAMIC COMPUTATION AND TRIM ANALYSIS UNDER LARGE DEFLECTION OF FLEXIBLE AIRCRAFT

作　　者：刘燚[1] 谢长川[1] 王立波[2] 胡锐[1] 杨超[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中航工业第一飞机设计研究院,西安710089

出　　处：《工程力学》2015年第10期239-249,共11页Engineering Mechanics

摘　　要：柔性飞机在载荷作用下产生较大的弹性变形并呈现出几何非线性特性,机翼升力面呈现出大变形空间曲面的特征,传统平面气动力的工程分析方法无法给出空间变形下的真实载荷状态进而影响柔性飞机气动弹性分析的准确性。该文基于柔性飞机几何非线性气动弹性分析的需求,建立了曲面三维升力线和曲面涡格两种不同的曲面定常气动力方法,并结合曲面样条插值完成了大变形下结构运动信息与气动载荷信息之间的相互作用和交换,实现气动面随结构变形的自适应更新。进行了柔性飞机的全机非线性配平分析,并对两种不同的气动力方法的分析结果进行对比,归纳出柔性飞机几何非线性气动弹性配平分析的特点。升力线方法分析快速简单,涡格法可以考虑机翼弯度影响,便于复杂模型的多轮次反复计算。两种方法的分析结果具有较好的一致性,当飞机变形较小时都与传统的线性分析方法吻合较好;当结构变形较大时,非线性配平结果随风速和结构质量呈非线性变化,与传统线性分析结果产生明显差别需在设计初期引起重视。Due to large structural elastic deflection and the accompanying geometrically nonlinear aeroelasticity, flexible aircraft make the traditional planar aerodynamic computation inaccurate and obsolete. Spatial curved lifting surfaces call for nonplanar aerodynamic computation to describe their real load conditions and structural aeroelastic response. In this paper, two effective nonplanar （spatial curved） aerodynamic computation methods （3-D lifting-line method and nonplanar vortex lattice method） were established and combined with surface spline interpolation to accomplish geometrically nonlinear aeroelastic trim analysis. The 3-D lifting-line method is simple and effective, as is the nonplanar vortex lattice method, which can consider the warp effect and is capable of complicated model and repetitious computations. Rigid and linear trim results were compared with nonlinear analysis results. The nonlinear trim analysis results from those two aerodynamic methods are consistent with one another and both are quite different from the linear importance of nonplanar aerodynamic computation analysis results when deformation is large, which indicates the and nonlinear aeroelastic analysis.

关 键 词：大展弦比柔性飞机 几何非线性 非线性配平:三维升力线 曲面涡格法 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程]