摘要：Additive Manufacturing(AM) processing has attracted wide attention due to its advantages, e.g., rapid prototyping and free design. In aeronautic and astronautic engineering, it is especially attractive to apply AM processing, especially Selective Laser Melting(SLM), into primary structures that always occupy most of the whole mass of aircraft or spacecraft. In this paper, an innovative lattice sandwich structure that is suitable to be manufactured with SLM is adopted to design the typical cylinder under axial compression. Firstly, the mechanical properties of pyramidal lattice are investigated, and the bearing capacity of the lattice sandwich cylinder is given analytically for each failure mode. Secondly, a composite cylinder is re-designed in the form of lattice sandwich structure, which sizes are ultimately obtained through optimization. Finally, finite element model of the innovative cylinder is established and several kinds of imperfection are introduced to simulate the defects caused by SLM. Numerical result shows that the lattice sandwich design can obviously enhance the bearing capacity of cylindrical shell even though the original one is designed with composite material. In other words, SLM has great potential in improving the primary structure of spacecraft in the future.

摘要：针对某航天器整器与其推进舱纵向基频可能出现的耦合问题,为规避耦合带来结构破坏的风险,开展了航天器整器与推进舱纵向基频错频优化设计方法研究。考虑推进剂携带量处于2.4~3.5t之间某一状态,给出了错频设计的两种可行途径;通过分析选择了增加推进模块与推进舱主结构连接刚度来提高推进舱纵向基频的最优途径,论证了增加连接螺栓数量、优化推进模块与推进舱主结构的连接T框和增加传递路径3个方案的优化效果;实现了将推进舱纵向基频与整器纵向基频完全错开,从而解决了基频耦合的问题。

摘要：针对天宫空间站梦天载荷舱提出了采用一种含大开口的半硬壳铆接结构,实现了结构承载、载荷进出舱及载荷试验平台一体化设计。采用数值仿真的方法,考虑主动段飞行及地面整器起吊载荷等因素的影响,进行了结构强度迭代分析,识别结构的潜在薄弱环节,并开展针对性的局部结构验证试验。最后,设计并建立大开口结构的全工况静力试验平台,开展载荷舱整舱静力试验。数值计算与试验所得结果吻合较好,验证了载荷舱大开口结构设计的正确性。载荷舱结构的设计方法及验证思路可为其他飞行器结构提供参考。

摘要：集中载荷形式下如何简化设计试验件,准确、简便、经济地进行强度考核一直是结构和试验设计的核心问题。依托空间站核心舱资源舱结构设计方案和具体的集中力载荷形式,按照基本变形和应力状态等效的原则,通过有限元仿真方法,给出了核心舱资源舱结构在集中载荷条件下试验件的简化设计具体方案,并顺利通过破坏试验,进行了验证。试验和仿真结果表明:该简化的试验件可以较为准确地反映整舱在集中载荷状态下的应力水平,试验件设计简单、有效,可为类似结构的试验件设计提供重要参考。

摘要：航天器推进平台轻量化设计是提升航天器任务效率和优化系统性能的重要突破口。目前,通用推进平台的贮箱极少参与推进平台承载,推进平台需要通过辅助承力构件将贮箱载荷传递至主结构,降低了推进平台的承载效率。为此提出了一种主结构与贮箱共承力的推进平台构型,新研表面张力贮箱通过嵌入安装的方式安装在承力筒侧壁,并通过对承力筒主结构开展变刚度设计,实现对贮箱承载量级的合理控制。以某卫星型号的研制需求为例,基于Nastran软件对其推进平台的结构设计参数进行了优化设计,并开展仿真分析和试验验证。研究结果表明,主结构与贮箱共承力推进平台力学性能与通用推进平台相当,但推进平台干重占比可降至13.6%,可有效提升推进平台的整体效率。研究结果可作为大型航天器推进平台设计参考。