挠性多体航天器姿态动力学建模与分析  

Dynamics Modeling and Analysis for a Flexible Multi-Body Spacecraft

作　　者：刘莹莹[1] 周军[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《飞行力学》2005年第3期60-63,共4页Flight Dynamics

基　　金：霍英东优秀青年教师基金(81056);总装武器装备预研基金资助项目(51420030401HK0335)

摘　　要：针对带有多个挠性附件以及天线转动机构的卫星等多体航天器,利用伪坐标L agrange方程建立了系统的姿态动力学模型。通过仿真计算,分析了星体与天线运动的耦合特性,以及挠性附件干扰对卫星姿态的影响,验证了数学模型的正确性。Lagrange＇s equations in quasi-coordinates are used for dynamics modeling of a multi-body spacecraft consisting of a rigid center body, several flexible appendages and an antenna. The coupling character between the antenna and the center body and the vibration effect of the flexible appendages on the satellite attitudes are analyzed by numerical simulation, which also proves the correctness of the dynamics model.

关 键 词：挠性航天器 多体航天器 卫星 LAGRANGE方程 动力学建模 

分 类 号：V448[航空宇航科学与技术—飞行器设计]