弹性飞行器飞行动力学建模与刚柔耦合阶次分析  

Flight Dynamics Modeling and Rigid-flexible Coupling Order Analysis for Flexible Flight Vehicle

作　　者：安阳 王天舒[1] AN Yang;WANG Tianshu(School of Aerospace Engineering,Tsinghua University,Beijing 100084,China)

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《宇航学报》2024年第2期240-249,共10页Journal of Astronautics

基　　金：国家自然科学基金(12172213)。

摘　　要：基于虚功率原理与混合坐标法,建立了弹性飞行器的飞行动力学模型。发现了附加在弹性结构上的部件会对飞行器姿轨运动与结构振动产生影响,从而给出了耦合系数与模态质量的修正项。定义了描述弹性变形项保留程度的刚柔耦合阶次,并以由弹性本体和刚体舵面组成的刚柔耦合多体系统为例,通过对比不同刚柔耦合阶次下动力学模型的时域响应与保守系统的动量计算结果,分析了动力学模型及动量公式中弹性变形项的保留阶次对动力学响应及动量计算精度的影响。揭示了传统模型忽略弹性变形高阶项可能导致的误差水平,为弹性飞行器动力学模型的简化与验证提供了参考。Based on virtual power principle and hybrid coordinate method,the flight dynamic model for flexible flight vehicle is established.It is found that the components attached to the flexible structure will have an effect on the attitude and orbit motion and the structure vibration of the flight vehicle,so the correction terms of the coupling coefficient and modal mass are given.The rigid-flexible coupling order is defined to describe the degree of flexible deformation term retention.Taking a rigid-flexible coupling multibody system consisting of a flexible body and a rigid rudder as an example,by comparing the time-domain response of the dynamic model and the momentum calculation results of the conservative system under different rigid-flexible coupling order,the influence of the retention order of the flexible deformation term in the dynamic model and momentum formula on the dynamic response and momentum calculation accuracy is analyzed.The error level caused by the traditional model ignoring the high-order term of flexible deformation is revealed,which provides a reference for the simplification and verification of the dynamic model for flexible flight vehicle.

关 键 词：弹性飞行器 耦合动力学 刚柔耦合阶次 虚功率原理 混合坐标法 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]