某航天器压紧释放装置结构设计与分析

为了给某微小型航天器设计一种新型的非火工压紧释放装置，采用了弹簧连杆式分离机构，对其可行性进行了分析。介绍了该压紧释放装置的工作原理，并通过理论计算求出该装置燃断器的燃断时间，然后进行试验验证，基于 ANSYS Workbench 软件进行了压紧状态下的随机振动仿真分析。结果表明，该燃断器的燃断时间可靠，理论值与试验值误差在15％以内，如果添加10 N 预拉力，燃断时间可减少约10％。在压紧状态下该装置振动环境适应性好，并且能够及时释放转子。

The Structural Design and Analysis of the Hold-Down and Release Mechanism for the Miniature Spacecraft

In order to design one kind of mew non-pyrotechnic hold-down and release mechanism for a miniature spacecraft,we used the spring-link separation device and analyzed the feasibility.Firstly,we described the working principle of the hold-down and release mechanism,calculated the burn-off time with the First Law of Thermodynamics.Secondly,we carried out the burn-off experiment,and got the actual burn-off time.We did a simulation analysis of random vibration under the compaction status based on the ANSYS Workbench.The experiments show that the burn-off module is reliable and the differences between the theoretical and experimental values are within an error of 15%.The burn-off time has a 10% reduction with the addition of 10 N pre-tension.The simulation analysis suggests that the device has a good vibration adaptability and can release the rotor in time.