形状记忆复合材料可展桁架在轨热分析

Thermal analysis of deployable shape memory composites truss structure in orbit

传统星载桁架结构需通过驱动器实现展开/收拢动作,应用形状记忆复合材料可突破该限制。对新型可展桁架各组件进行热控方案设计,基于I-DEAS/TMG软件建立热分析数值模型,对桁架各组件在轨外热流以及温度场变化进行计算分析。结果表明:最外端桁架在轨运行4个周期后其温度场呈周期性变化特征;不同多层隔热材料(multi-layer insulation material,MLI)表面辐射特性对内/外端纵杆温度影响明显;热控方案能实现有效的在轨温度控制。

The traditional spaceborne truss structure needs a driver to implement the action of deploying and folding. However, it can be improved by using shape memory composites. The thermal characteristic of a deployable shape memory composites truss was numerically studied and different thermal control measures were designed for different truss parts in this work. Heat flux and transient temperature distribution of truss structure in orbit were calculated using a thermal analysis model established with software I-DEAS/TMG. The numerical results indicate that the temperature of outer truss structure varies periodically after four circles. The radiation characteristic of multi-layer insulation material has influence on temperature distributions of composite tube. It can be found that the thermal control measures proposed is capable of realizing the effective temperature control for deployable shape memory composites truss in orbit.