摘要
基于分枝模态法,用修正活塞与细长体理论计算超声速飞行器升力面和机身的非定常气动力,考虑了翼身干扰和翼面对舵面的下洗与阻滞作用,通过控制系统输入参数与结构模态参数的关系,输出舵偏产生的非定常气动力的激励关系,建立由模态坐标运动微分方程和控制系统传递函数联合表示的飞行器气动伺服弹性模型,在时域内求解。某飞行器颤振和气动伺服弹性的计算证明该法可行、有效。另外,讨论了结构滤波器参数、敏感元件位置和及弹身固有频率对气动伺服弹性稳定性的影响。
The branch mode method was used to reckon an aircraft s structural dynamic characteristic using the piston theory with compressive correction to calculate unsteady aerodynamic force of the wings and the rudders,and the linear perturbation slender body theory to calculate the fuselage s unsteady aerodynamic force in this paper.When the influences of atmosphere interference between the fuselage and the wings or the rudders and atmosphere wash from the wings to the rudders were taken into account,and the stimu...
出处
《上海航天》
北大核心
2008年第4期22-25,30,共5页
Aerospace Shanghai
关键词
超声速
气动伺服弹性
颤振
时域
稳定性
分枝模态法
Supersonic
Aeroservoelastic
Flutter
Time-domain
Stability
Branch mode method
