AbstractAs a kind of deployable aerodynamic deceleration technology, the aerodynamic structure of the semi-rigid mechanical deployable aerodynamic deceleration technology is different from the air-bag structure of the flexible inflatable aerodynamic deceleration technology, and it is a linkage mechanism which is made up of ribs, struts, nose and main body. The linkage mechanism is an important part of the semi-rigid mechanical deployable aerodynamic deceleration technology, the mechanism characteristics research is fundamental to ef-ficiently use rocket fairing space and ensure aerodynamic surface configuration stable. Firstly, the paper estab-lishes a linkage mechanism geometry and mechanics models according to the structural features and loaded state of the semi-rigid mechanical deployable aerodynamic deceleration technology. Secondly, using means of mathematics analytical method semi-quantitative analysis and finite element method verification, it analyzes and compares the mechanism characteristics from four aspects, including geometric parameters, folded envelope, structural deformation and system stiffness. Through research, the paper obtains the minimum folded envelope conditions and minimum deformation conditions, determines the linkage mechanism states of the minimum deformation, best stiffness and smallest folded envelope, and gives advice for the geometric parame-ter selection of linkage mechanism. The procedure and the conclusions of the research provide a theoretical basis for the project implementation and mechanism optimization design of the semi-rigid mechanical deploya-ble aerodynamic deceleration technology.%半刚性机械展开式气动减速技术作为可展开气动减速技术的一种，其气动面结构区别于柔性充气式展开技术的气囊结构，它主要是一个由辐条、连接杆、头锥及主体等部件构成的连杆机构系统。连杆机构系统是半刚性机械展开式气动减速技术重要组成部分，对其开展特征研究是有效利用火箭整流罩空间、保证气动面构型稳定的基础。文章首先根据半刚性机械展开式气动减速技术结构特点及受力情况，建立了连杆机构几何模型和力学模型；然后采用数学解析法半定量分析和有限元法验证的手段，从几何参数、收拢包络、机构变形、系统刚度等方面对机构特征进行了分析与比较。通过研究，得出了最小收拢包络条件及最小变形条件；确定了变形最小、刚度最好、收拢包络最小的连杆机构状态；给出了连杆机构几何参数选择建议。文章研究内容及结论为进行半刚性机械展开式气动减速技术工程实施及机构优化设计提供了参考。
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