Repair Guide for Large Area Composite Structure Repair.

摘要

This repair guide presents recommended procedures for the repair of large damage areas on graphite/expoxy panels. The procedures were developed during a program in which repairs were analysed, designed and tested to verify their strength and durability. Both engineering design information and specific step-by-step shop procedures are given. The recommended repair configuration uses a scarf joint machined into the parent panel as the damaged material is removed.Repair plies of prepreg are stepped to fit the scarfed surface and made to extend slightly beyond the end of the scarf leaving an esentially flush surface. The repair plies are cocured in place with a layer of film adhesive. An alternate repair is shown using a precured external patch which may be simpler to install in some cases, although at the expense of aerodynamic smoothness and with some loss in strength. The procedures in this repair guide are intended to supplement, but not replace, instructions given for the repair of specific aircraft as given in technical orders or otherwise specified by the manufacturer of the aircraft. (Author)