Platform interface system for parallel running double-platform spacecraft

The invention discloses a platform interface system for a parallel running double-platform spacecraft, wherein the demands for combination, malfunction and separation state of the double-platform spacecraft are taken as the basis, the mutual relations and influences of machines, electricity, heat and information interfaces of platforms are taken into overall consideration, and the related design is hereby carried out. The design is simple and is easy to implement, task requirements are met, the combination and the isolation of two platform systems are also flexibly realized, and the reliability and the safety of the spacecraft executing a task are guaranteed. 本发明公开了种并行运行双平台航天器的平台接口系统，以双平台航天器组合、故障和分离状态的需求为基础，综合考虑了平台之间的机、电、热和信息接口之间的相互关系和影响，并以此开展相关设计。该设计简单易于实现，既能够满足任务需求，还能够灵活的实现两个平台系统间的组合与隔离，确保了航天器在执行任务中的可靠性和安全性。