为实现“翱翔之星”立方星发射力学环境下可靠的锁定以及在轨低冲击快响应的解锁分离, 提出了一种断电时弹簧锁定与加电时电磁铁吸合解锁的非火工解锁机构。首先, 根据系统要求介绍了电磁解锁机构的工作原理, 并建立了机-电-磁耦合动力学模型, 分析解锁机构的动力学响应特性; 其次, 以地面测试试验结果为依据, 进行电磁参数的多约束多目标设计与优化, 并将优化出的参数在SIMULINK环境下进行仿真验证; 再次, 对电磁解锁机构样机进行功能测试, 实测数值与仿真结果基本一致：额定电压28 V下样机的解锁时间为41.2 ms, 解锁电流为2.2 A, 能耗为2.5 J; 最后, 开展了力学环境和热真空环境地面试验以及±5 V电压拉偏测试, 结果表明电磁解锁机构能够可靠锁定与解锁。本文设计的电磁解锁机构经过飞行验证成功应用于“翱翔之星”立方星的在轨解锁与分离, 可为后续立方星星箭分离解锁机构的标准化设计提供参考。

To implement reliable locking under launching mechanical environment and low-impact and fast-response unlocking on-orbit for the CubeSat “Star of Aoxiang”, a non-pyrotechnic door release mechanism was proposed which locked by reset spring at the time of power off and unlocked by electromagnetic force at the time of power on. Firstly, according to the system requirements, the work principle of electromagnet door release mechanism was introduced, and the coupling dynamical models involving mechanical-electrical-magnetic characteristics were established. Secondly, the multi-constrain and multi-objective problems of electromagnet parameters were solved based on the ground tests, after that, the simulation verification of the optimized parameters was implemented. Then, the functional tests for a prototype of the electromagnet door release mechanism were carried out. The measurement values agreed well with the simulations results, which showed that the unlocking time was 41.2 ms and the current was 2.2 A and the energy consumption was only 2.5 J at the typical voltage of 28 V. Finally, on the condition of mechanical and thermal-vacuum ground environment and down-deflection of ±5 V, the electromagnet door release mechanism could lock and unlock reliably. The proposed door release mechanism has successfully applied to unlocking and launching the CubeSat “Star of Aoxiang” on-orbit. It provides reference for further standardization design of door release mechanism for following CubeSats and other micro-satellites.