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基于航天器结构的模块化设计概念,设计了一种新的在轨展开航天器构型,即齿轮齿条式构型。利用虚拟样机技术,在ADAMS软件中建立了这种新型航天器在轨展开的虚拟样机。首先研究了航天器本体以不同的驱动速度展开对航天器姿态角及姿态角速度的影响。其次,对航天器本体和太阳帆板的三种展开顺序进行了仿真,即本体模块和太阳帆板同时展开、太阳帆板先展开本体模块后展开、本体模块先展开太阳帆板后展开,分析了这三种展开顺序对航天器姿态角及姿态角速度的影响。仿真结果可以为未来高机动、多任务多形态的模块化航天器设计、在轨展开技术和空间姿态控制提供启发和借鉴。
Based on the concept of modular design of spacecraft structure, a new in-orbit spacecraft configuration, ie, rack and pinion configuration, is designed. Using virtual prototyping technology, a virtual prototype of the new spacecraft in orbit is established in ADAMS software. Firstly, the influence of spacecraft on-vehicle attitude attitude and attitude angular velocity with different driving speed is studied. Secondly, the three kinds of unfolding sequences of the spacecraft body and the solar panel are simulated, that is, the ontology module and the solar panel are deployed at the same time. The solar panel expands after the ontology module is deployed, the ontology module expands after the solar panel is deployed, The influence of these three kinds of unfolding order on spacecraft attitude angle and attitude angular velocity are discussed. The simulation results can provide inspiration and reference for the future design of high-powered, multi-mission and multi-modal modular spacecraft, in-orbit deployment technology and space attitude control.