摘要
以 N- S方程为控制方程计算机翼气动力 ,考虑机翼的结构弹性的影响 ,采用结构影响系数法建立结构平衡方程计算弹性变形 ,两个方程相互迭代耦合求解 ,计算弹性飞机飞行中的真实载荷 ,并在已知弹性机翼飞行时总载荷的情况下 。
Modern large aircraft have become increasingly flexible, causing its deformation to become increasingly large. We contracted to develop an analysis method for calculating loads acting on flexible aircraft wing with its real deformation considered. In this paper, we explain in much detail the analysis method we developed under contract. Here we give only a briefing of our method. It involves the calculation of aerodynamic loads followed by calculation of deformation; this cycle is repeated again and again until the actual aerodynamic loads and the actual deformation of wing are both obtained. The aerodynamic loads are calculated by solving Navier-Stokes equations with the second order implicit LU-NND algorithm; the structure deformation is calculated by structure influence coefficient method. In this paper, we take a swept-back wing as numerical example and the numerical simulation results obtained with our method show preliminarily that our method is feasible. The numerical example also contains a number of interesting results that correspond to the discussion of the detailed explanation of our method given in this paper.
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
2004年第6期786-789,共4页
Journal of Northwestern Polytechnical University
关键词
N-S方程
结构弹性
弹性机翼
载荷
Navier-Stokes equations, elastic wing, structure deformation, aerodynamic load
