Studies in the matrix dominated failures of composite joints

摘要

The potential use of composites for weight savings is now widely recognized and they are extensively sued in both aircraft control surfaces and doors. However, if major weight savings are to be realized it is essential that composites be sued in `primary' structural components, i.e. wing and fuselage skins. Before this can be achieved it must be shown that measure of transmitting the load form the composite structure to the underlying, or adjacent structure, are both safe and meet the FAA adage tolerance certification requirements.