耦合六自由度运动弹性飞机阵风响应数值模拟  

Numerical Simulation of Elastic Aircraft Gust Response Coupled with 6 DOF Motion

作　　者：颜洪[1] 黄江涛[2] 麻蓉[1] 梁益华[1] 

机构地区：[1]中航工业西安航空计算技术研究所,陕西西安710068 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《航空计算技术》2013年第6期91-94,共4页Aeronautical Computing Technique

基　　金：国家863计划项目资助(2012AA01A304)

摘　　要：耦合飞机刚体六自由度运动,考虑飞机结构气动弹性变形,基于全湍流Navier-Stokes方程流场数值模拟方法,建立了离散阵风作用下弹性飞行器气动载荷与飞行姿态响应的数值模拟技术。其中模态空间中结构动力学方程以及六自由度运动方程分别采用四阶R-K进行时间推进求解,采用Radial Basic Function(RBF)技术进行气动/结构数据耦合,对应飞机姿态以及弹性变形采用RBF与TFI组合模式的动网格方法进行网格更新;以飞翼布局弹性飞机为数值研究对象,研究了离散阵风作用下飞行器的气动载荷响应以及飞行姿态的变化,对比分析了刚性飞行器与弹性飞行器对离散阵风响应的区别,为进一步系统地分析真实飞机飞行品质提供数值平台。The numerical simulation technology of aerodynamic load of aircraft and flight attitude response under discrete gust, considering the elastic deformation of aircraft structure, has been established in the premise of coupling 6 degrees of freedom modal of aircraft rigid body. Both he： structural dynamics equa- tions and six degrees of freedom equations of motion in modal space are solved by using the fourth- order R- K time advanced method. The RBF technology is chosen to couple aerodynamic and structural data. The dynamic grid method combining RBF and TFI is selected to corresponding to update grid correspond- ing to the aircraft attitude and elastic deformation. The full turbulent Navier- Stokes equations are used for numerical simulation of flow field. In this paper, taking the elastic aircraft of flying wing as subject of nu- merical research,the changes of the response of aircraft aerodynamic loads and flight attitude under the discrete gust was investigated. The difference of discrete gust response between rigid aircraft and elastic aircraft was compared and analyzed. The numerical platform for further analysis of the real aircraft flying qualities is established.

关 键 词：阵风响应 六自由度运动 模态叠加 弹性飞机 动网格技术 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]