利用碳纤维复合材料具有比强度及比模量高等优点, 针对中心承力筒式卫星主承力结构设计了一种主承力架和若干独立模块层单元组合的结构方案。通过复合材料层压板理论和截面设计理论, 对主承力架进行了结构设计。该主承力架由碳纤维复合材料铺层成型, 消除了层间耦合刚度; 采用薄蒙皮+“几”字型筋+T型环筋的桁架结构和合理的工艺设计提高了主承力架的承载能力。对所设计的主承力架结构进行了数值仿真分析, 结果表明主承力架强度和刚度均满足设计要求。最后, 对主承力架进行了实验验证, 结果显示, 实验结果与仿真计算结果基本一致。与铝合金材料结构设计相比, 采用碳纤维复合材料的主承力架结构的重量减少了30%以上, 实现了飞行器主承力结构的轻量化。

On the basis of carbon fiber composites with advantages of high specific strength and high modulus, a structural design scheme of the carbon fiber composite primary force-taking structure combined with several layer element modules was proposed for a principle bearing cylinder in satellite and rocket structures. A primary force-taking structure was designed based on composite laminate structure theories and section beam theories. The designed primary force-taking structure was molded in layering by carbon fiber composite material piles to remove the couple stiffness between the layers and was formed with a thin skin+“几”stringers +”T”-shaped cross-rib truss structure to improve its loading abilities. The primary force-taking structure was simulated numerically. The results indicate that the strength and stiffness of the designed structure meet design requirements. Finally, the primary force-taking structure was assessed by experiments. The verified results show that both the experimental results and simulation results are consistent. As compared to the same type of aluminum structure, the deadweight of the designed structure has reduced by 30%, which means that the proposed lightweight design method is effective.