Abstract: Thin-walled deployable composite structures with high deformability are of considerable interest and increasingly used in aerospace field due to their superior mechanical behaviour and folding function. The stiffness and stability for the space thin-walled deployable composite boom are analysed with different configuration parameters and layup. The numerical model is demonstrated through experimental bending and torsion tests of cantilever boom. The quasi static folding process is numerical simulated used explicit non-linear method. Analysis results show that the boom section radius is smaller and the layup is thicker, the stress level of boom is greater during folding process. The drum diameter is smaller, the stress level of boom is greater during folding process. Analysis results provide a reference basis for thin-walled composite boom and winding institutional design.

Key words: fibre reinforced composite, thin-walled boom, stiffness, folding process, mechanical analysis