基于刚柔耦合的新型航天飞行器舱门锁紧机构捕获域研究

摘要

Considering the failure of one⁃sided deployable mechanism, the capture field of central latch mechanism of new spacecraft door is investigated based on rigid⁃flexible coupling. The main structure of spacecraft door is mod⁃eled. Internal and external skins, internal embedded frames, and internal girders are modeled as flexible, and the influence of number of internal girders and spacing between two internal girders on the capture field of central latch mechanism are studied. In addition, the spacing between two internal girders is optimized under different number of internal girders. Moreover, the influence of thermal deformation on the capture field under the space temperature is also considered and investigated. The results show that there are light effects of spacing between two internal girders and the number of the internal girders on the capture field, and the capture fields decrease as the increase of the number of the internal girders. For the original design with 3 internal girders, the optimal value of the spacing be⁃tween two internal girders is 1.163 m, and the corresponding capture field increases 3.505 mm. When the number of the internal girders is 2, the optimal value of the spacing between two internal girders is 2.326 m, and the cap⁃ture field increases 3.556 mm. For the case of 5 internal girders, the optimal value of the spacing between two inter⁃nal girders is 0.5815m, and the capture field increases 3.394 mm. Therefore, one can choose 2 internal girders if the corresponding capture field is under control. Compared with room temperature, the capture field under high temperature will be enhanced, while low temperature can contribute to reducing the capture field.%针对新型航天飞行器舱门单侧展收机构故障的工况，基于刚柔耦合技术，研究了舱门中心锁紧机构捕获域的变化情况。建立了舱门主体结构模型，将舱门内外蒙皮、内埋框和大梁设置为柔体，研究了大梁间距以及大梁数目对中心锁紧机构捕获域的影响，并针对不同大梁数目情况下的大梁间距进行了优化设计。此外，考虑空间高低温环境，研究了极限温度下热变形对舱门中心锁紧机构捕获域的影响。结果表明：舱门单侧展收机构故障时，大梁间距对舱门中心锁捕获域有一定的影响，捕获域随大梁数目的增大而减小，但其影响有限。原有3根大梁的设计，大梁间距的最优值为1．163 m，对应捕获域增大3．505 mm；大梁数目为2根时，大梁间距最优值为2．326 m，捕获域增大3．556 mm，而大梁数目为5根时，大梁间距最优值为0．5815 m，捕获域增大3．394 mm。因此，在满足捕获域要求的前提下，可采用2根大梁。与常温环境相比，高温环境捕获域增大，不利于舱门闭合，而低温环境更有利于舱门闭合。