摘要
为了更准确地反映航天器挠性附件振动模态,采用非约束模态研究方法,对挠性航天器系统进行分析。先应用拉格朗日法建立挠性航天器系统动力学方程,通过动力学方程求解系统固有频率,再结合有限元软件进行比较验证,结果表明了该方法的可行性。在此基础上,研究分析了中心刚体和挠性帆板惯量对航天器系统频率特性的影响。
In order to more accurately reflect the vibration mode of the flexible accessory of the spacecraft,the unconstrained mode research method is adopted to analyze the flexible spacecraft system.First,the Lagrange method is used to establish the dynamic equation of the flexible spacecraft system,and the natural frequency of the system is solved by the dynamic equation,and then the finite element software is used for comparison and verification.The results confirm the feasibility of the method.On this basis,the influence of the inertia of the central rigid body and the flexible windsurfing board on the frequency characteristics of the spacecraft system is studied and analyzed.
作者
沙建波
戈新生
SHA Jianbo;GE Xinsheng(Mechanical Electrical Engineering School,Beijing Information Science&Technology University,Beijing 100192,China)
出处
《北京信息科技大学学报（自然科学版）》
2020年第5期20-24,共5页
Journal of Beijing Information Science and Technology University
基金
国家自然科学基金项目(11172047)。
关键词
挠性航天器
非约束模态
频率特性
flexible spacecraft
unconstrained mode
frequency characteristics
