低轨道下运行的卫星-太阳帆板系统的刚-柔-热耦合动力学建模

摘要

In the conventional dynamic modeling for satellite-solar panels systems,for considering the thermal effect,only the heat flux by direct solar radiation is taken into account,which cannot be extended to satellite-solar panels systems in low earth orbit.In the paper,a general modeling method for analyzing the rigid-flexible-thermal coupling dynamic performance of a satellite-solar panels system in low earth orbits was proposed.The expressions for the heat flux of direct solar radiation,earth infrared radiation and reflected solar radiation by the earth were derived considering the coupling relationship among the thermally induced deformation of panels,attitude motion of satellite and the heat flux caused by different kinds of thermal radiations.Assuming the satellite-solar panels system as a hub-beam multibody system,the heat conductive equation of a cantilevered beam was derived,and then by leading in the thermal stress-strain relationship,dynamic equations of the satellite-solar panels system were obtained based on the principle of virtual work.The heat conductive equation and the dynamic equations were solved simultaneously.A simulation analysis of the satellitesolar panels system was carried out to show the influences of the earth infrared radiation and reflected solar radiation by the earth on the thermally induced vibration.In addition,the influence of considering the rigid-flexible-thermal coupling effect on the dynamic performance of the flexible multibody system was revealed.Finally,the stable regions of some parameters affecting the thermally induced vibration were given.%传统地考虑热效应的卫星-太阳帆板动力学模型只考虑太阳直接辐射热流的影响,仅适用于高轨道运行的航天器.以低轨道下运行的卫星-太阳帆板系统为研究对象,提出了一种通用的分析其在宇宙空间各种热流作用下刚-柔-热耦合动力学特性的建模方法.考虑太阳帆板热变形、卫星的姿态运动和太阳帆板受到的各种辐射的热流密度之间的耦合关系,分别给出了太阳直接辐射热流、地球红外辐射热流以及地球反照辐射热流的计算公式.将系统视为中心刚体-悬臂梁模型,首先建立了悬臂梁的热传导方程,然后通过引入考虑热应变的应力-应变关系,用虚功原理建立了卫星-太阳帆板多体系统的考虑热效应的动力学方程,对热传导方程和动力学方程联立求解.对低轨道下运行的卫星-太阳帆板系统进行了数值仿真分析,分析了考虑地球红外辐射和地球反照辐射热流对热振动的影响,以及考虑刚-柔-热耦合效应对系统动力学特性的影响,并给出了系统热振动稳定时特征参数的范围.