铰链展开式构型航天器设计及其动力学仿真

Design and Dynamic Simulation of Hinged Deployable Configuration Spacecraft

基于航天器结构的模块化设计概念,设计了一种空间可展开航天器模块化结构构型,即铰链展开式构型。利用虚拟样机技术,建立了模块化本体和太阳翼虚拟样机模型。在空间失重环境下,分析了模块化本体和太阳翼在3种展开顺序下(本体各模块和太阳翼同时展开、太阳翼先展开本体各模块后展开和本体各模块先展开太阳翼后展开)对航天器姿态的影响,同时对比了不同扭簧参数对姿态角和展开时间的影响。仿真结果表明该模型可为未来高机动、多型态、多用途自适应变构型航天器的设计以及空间姿态控制提供技术支持和借鉴。

Based on modular design idea of the spacecraft structure, a hinged deployable configuration for the spacecraft was designed. The virtual prototyping model of modular body and solar panels was established with virtual prototyping technology. And the influence of three deployment sequences of modular body and solar panels on attitude of the spacecraft in the weightless space environment were analyzed, including the modular body and solar panels deployed simultaneously, the modular body deployed after the solar panels, and the solar panels deployed after the modular body. Meanwhile, the influences of different torsion spring parameters on attitude angle and deployment time were compared.