柔性翼飞行器动力学建模与循环求解仿真方法  

Modelling and Simulation Method for Flexible Wing Aircraft

作　　者：于扬 王正杰[1] 

机构地区：[1]北京理工大学机电学院,北京100081

出　　处：《北京理工大学学报》2017年第12期1224-1228,共5页Transactions of Beijing Institute of Technology

基　　金：国家自然科学基金资助项目(11102019);国家部委预研项目(622****0103)

摘　　要：针对刚体飞行动力学难以描述柔性翼飞行器刚柔耦合动力学特性的问题,提出了一种在时域内对刚体运动和弹性体运动交替进行数值计算的建模与循环求解仿真方法.该方法分别为飞行器刚体与弹性体运动建立了独立坐标系,根据坐标系之间的惯性牵连关系,通过气动力与惯性力完成了刚柔耦合动力学关系在刚体与弹性体运动之间的传递.与此对应的仿真算法是在1个积分步长内顺序计算飞行器受力情况、弹性变形状态与刚体运动状态,在仿真步长之间以循环求解的方式进行仿真计算.以飞行器对姿态扰动的动态响应为例进行仿真分析,结果表明本文的动力学建模与仿真方法能正确反映柔性翼飞行器的飞行特性.A new modelling and simulation method for flexible wing aircraft was presented to describe coupling effects between rigid-body movement and structure deflection.Rigid-body movements and structural deflections were calculated under independent inertial and non-inertial systems respectively.Aerodynamic forces and inertial forces were used to describe the rigid flexible coupling dynamic properties.The mathematical solution was to calculate forces,rigidbody movements and elastic deflections in a specific order inside a time-step,and a cyclic solving method was used between time-steps.Simulation results of aircraft＇s attitude dynamic response were used to check the reliability of this method.The results confirm that this modelling and simulation method is able to represent dynamic characters of flexible wing aircraft.

关 键 词：飞行力学 结构动力学 气动弹性力学 柔性翼飞行器 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]