Abstract: Based on the numerical method, the work of optimizing composite crossed beam structures in spacecraft was conducted in this paper. The load-transferred path was optimized depending upon the load-bearing structure components. Furthermore, the enhanced region and lay-up of T700 unidirectional carbon/epoxy prepregs were reasonably presented, while the specimen was fabricated integrally by manual molding technology. The experimental results demonstrate that the weight of this crossed beam is reduced from 966 g to 436 g, up to 37.5%; the maximum deformation is reduced from 0.33 mm to 0.19 mm under the 6000 N compressive load, which satisfied the stiffness demand.

Key words: crossed beam, composite, weight, stiffness