Volume 4, Issue 4 (July 1976)
Converting Fatigue Loading Spectra for Flight-by-Flight Testing of Aircraft and Helicopter Components
Fatigue tests conducted on structural components of flight vehicles are generally required to demonstrate compliance with contract and military specifications. The results of these tests provide assurance to the customer that the structure will have an acceptably low probability of fatigue crack occurrence during service and that the cracks that do develop in service will propagate slowly enough to allow detection and repair. This overview presentation describes how to convert fatigue service loading spectra into fatigue test spectra to meet the requirements for full-scale fatigue testing of aircraft and helicopter components.