跨声速机翼静气动弹性数值分析方法  

A Static Aeroelastic Numerical Analytic Method of Transonic Flow About Wings

作　　者：张建柏[1] 张秀滨[1] 

机构地区：[1]中国空气动力研究与发展中心

出　　处：《空气动力学学报》1995年第1期63-66,共4页Acta Aerodynamica Sinica

摘　　要：本文给出一种以改进的跨声速守恒型全位势有限体积法为基础的机翼静气动弹性数值分析方法。改进发展了气动网格划分技术，使其对大后掠三角形机翼也能顺利适用。采用位移法计算机翼柔度影响矩阵。将非线性气动力与结构线化机翼弹性变形耦合迭代求解。当气动力和结构变形均收敛后，即求出弹性机翼的气动特性。通过算例计算，表明气动方法改进是成功的，弹性结果是合理的。跨声速范围弹性影响大，值得注意。A static aeroelastic numerical analytic method of transon-ic flow about wings is presented.The method based on improved finite volume method for a transonic full potential formulation in conservative form.The grid generation technique is modified and developed to apply high swept and low tapered wings well.The displacement procedure is used to calculate flexible influence coefficient matrices in the method.The method requires the coupling of two iterative processes-a nonlinearaerodynamic analysis and a linear structural deflections analysis.When aerodynamic solution and structural deflections are both converged,the aerodynamic characteristic of the elastic wing is obtained. The rigid and elastic aerodynamic forces for fighter wing are calculated and compared with the experiment data or the computed results of linear theory. The comparisons indicate that the modification of the aerodynamic method is successful and the elastic results is reasonable.Some effects of elastic-ity on the aerodynamic loading for transonic regime are noted.

关 键 词：静气动弹性 跨声速流动 机翼 数值分析 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]