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为实现“翱翔之星”立方星在轨可靠分离,达到初始分离速度和姿态的要求,设计了立方星星箭分离机构运动系统并进行了实验验证。提出了一种利用分离弹簧推动立方星打开舱门,并采用弹簧销轴完成舱门锁定的运动系统结构方案。首先,基于能量守恒定理确定了分离弹簧的结构参数;其次,建立了星箭分离过程中立方星与舱门的运动耦合系统动力学模型,并利用MATLAB软件进行了数值仿真;最后,对星箭分离机构样机进行了地面分离试验。实验结果显示,实际分离过程与数值仿真结果基本一致,实现了立方星无干涉分离及舱门的可靠锁定。该星箭分离机构成功实现了“翱翔之星”立方星的在轨分离,卫星下传数据表明其初始分离速度为1.08m/s,三轴角速度均小于2(°)/s,完全满足立方星初始分离速度和姿态的要求,可为后续立方星星箭分离机构的标准化设计提供参考。
In order to realize the reliable separation of the star of “Soaring Star” in orbit and to meet the initial separation speed and attitude requirements, the motion system of the cubic star and arrow separation mechanism was designed and verified by experiments. Proposed a separation spring to promote the cubic star to open the door, and the use of spring pin to complete the door locking system structure movement scheme. First, the structural parameters of the separation spring were determined based on the energy conservation theorem. Secondly, the kinematic model of the kinematic coupling between the cubic star and the hatch was established and the numerical simulation was carried out by MATLAB software. Finally, Detachment prototype for ground separation test. Experimental results show that the actual separation process and numerical simulation results are basically the same, to achieve a non-interference separation of the cubic star and reliable locking of the door. The satellite separation mechanism successfully achieved in-orbit separation of the “soaring star” cubic satellite. The satellite downlink data showed that the initial separation speed was 1.08 m / s and the angular velocities of the three axes were less than 2 (°) / s Meet the requirements of initial separation speed and attitude of cubic star, which can provide references for the standard design of subsequent cubic star and arrow separation mechanism.