Abstract:

Directing to needs about designing UAVs airframe and working out technological process, this article compares the mechanical properties of composite laminates and panels of honeycomb sandwich structure made from different kinds of prepregs at the same cure condition. It comes to the conclusion that cocure technique can be directly used to make honeycomb sandwich structure used for UAVs airframe. The results show that mechanical properties are basically about the same, but the shear strength of the panels is lower than the laminates obviously.