Fatigue and strength loads computed with regression equations empirically derived to convert the load spectra to design values

It is the objective of this paper to present regression equations derived for the F-106, F-111, A-7D and V-22. These equations can be the link between the load environment and aircraft structural design to evaluate the required strength and adequate fatigue life. The location load equation variables must completely define the internal or external loads on the structure at the analysis location. The load environment for this method is a statistical representation of variables with multivariable spectra that will allow conversion to any location on the aircraft with load equations. In detail, these spectra have five variables: lateral load factor, normal load factor, pitch acceleration, yaw acceleration, and roll acceleration.