某航天器压紧释放装置结构设计与分析

摘要

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，通过理论计算求出该装置燃断器的燃断时间，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。该压紧释放装置可满足微小型航天器精密机构的要求。%For a miniature spacecraft,and in order to design one kind of new non-pyrotechnic hold-down and release mechanism for a miniature spacecraft,we used the spring-link separation device and analyzed the feasibility. We described the working principle of the hold-down and release mechanism, and calculated the burn-off time.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 good vibration adaptability and can release the rotor in time.The hold-down and release system can meet the required standards of the miniature spacecraft.