In order to better control the motion state of the satellite and achieve precise orbit insertion, it is necessary to assess the sensitivity of the satellite to the physical parameters of the system during the satellite rocket separation process. This paper proposes a simplified two-dimensional dynamic model for the complex layout scheme of separation of large angle asymmetric star rocket joint surfaces, which simplifies the complex three-dimensional dynamic problem into a planar dynamic problem, reduces the system’s degrees of freedom, and greatly simplifies the computational difficulty of the model. The simulation results indicate that by appropriately configuring the preload of built-in springs and interface friction properties, the initial attitude of satellite orbit insertion can be effectively controlled. The research results can provide guidance for the parameter design of satellite-rocket separation devices.

为更好地控制卫星运动状态并实现精确入轨, 评估卫星火箭分离过程中卫星对系统物理参数的敏感性, 针对捷龙三号遥二卫星发射任务中的星箭非轴对称构型布局, 建立星箭弹簧分离装置的二维简化动力学模型, 将复杂的三维动力学问题简化为平面动力学问题, 降低系统的自由度, 简化了模型计算难度。仿真结果表明, 通过适当配置内置弹簧的预紧力和界面摩擦性质, 可以有效地控制卫星入轨的初始姿态。研究结果可为星箭弹簧分离装置的优化设计提供理论指导。