脉冲发动机复合壳体的强度分析及优化设计

Intensity Analysis and Optimum Design of the Composite Shell of Pulse Motor

采用ANSYS有限元软件对脉冲发动机复合壳体进行了结构强度分析和优化设计。用六节点三角形单元对复合壳体模型离散化;给出了复合壳体在临界压力载荷下的失效模式;分别在两种材料层中对最大应力约束下,以减少复合壳体的总质量为目标,对复合壳体的壁厚尺寸和过渡圆半径尺寸等设计变量进行了优化,并对设计变量的敏感度进行了分析。计算结果表明,在工作压力载荷下,安装在轨姿控舱体内的脉冲发动机的强度可以满足设计要求;壁厚尺寸是关键的优化设计变量,优化后脉冲发动机复合壳体的总质量可减轻5.7%。理论分析结果与试验结果相吻合。

The intensity analysis and optimization design of the composite shell of pulse motor has been presented using ANSYS finite element software. Triangle elements with six nodes for axial symmetry structure were selected. The failure model of the composite shell under the critical pressure load was given. Under the maximum stress restrictions for the two different material layers, optimum design of the wall thicknesses and the radii of transit arcs for the composite shell were finished in order to reduce the total mass of the composite shell, and the sensitivities of the design variables were analyzed. The analysis result shows that the pulse motors assembled in the section of missile for divert and attitude control can work reliably; the wall thicknesses are the key design variables, and the total mass can be reduced by 5.7 % . The calculation results accord well with the experimental results.