CORE STABILIZATION TECHNIQUE WITH THE HELP OF SIMULATOR TOOL FOR MANUFACTURING OF SANDWICH STRUCTURE COMPOSITE COMPONENTS FOR AIRCRAFT AND HELICOPTER

摘要

Sandwich composite parts like doors / covers are used in the fighter aircrafts because of excellent bending stiffness to weight ratio. These door/cover opened & closed in replacement of the LRUs and other systems, either periodically or daily inspection as part of the maintenance procedure. Majority of them are interchangeable parts, therefore dimensional accuracy is more important. As the design point of view, aerodynamic loads are distributed through these structures to the airframe at joints, fasteners point and hinges. The distance between fastener point to core ramp staring point is of importance while transferring bending load from sandwich composite structure to airframe. This critical distance needs to be maintained with tight tolerance. By core stabilization process core movement or core crushing can be prevented there by the critical distance between fastener point to core start point can be achieved, this is also helpful in achieving the interchangeability of these parts.