Abstract
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.
| Original language | English |
|---|---|
| Pages (from-to) | 152-156 |
| Number of pages | 5 |
| Journal | Yuhang Xuebao/Journal of Astronautics |
| Volume | 28 |
| Issue number | 1 |
| Publication status | Published - Jan 2007 |
Keywords
- Composite structure
- Finite element
- Intensity
- Optimum design