Technical Paper
Flight Test Identification Methods for Loads Models and Applications
2011-10-18
2011-01-2763
The Loads discipline contributes to the aircraft structural design by delivering shear, moment and torque (SMT, loads) all across the airframe resulting from application of aircraft airworthiness requirements as laid down in the CS 25/FAR 25 regulations and in some domestic ones. Loads computation considers the maneuver and gust conditions prescribed therein as well as other special design conditions. It is based on very detailed modeling, accounting for aerodynamics in all configurations, mass properties, flexibility of the airframe, flight control laws and retarded laws, hydraulic actuation, and specification of flight control system failure conditions. The resulting shear loads are processed and refined (e.g. nodal loads) and taken into account by the stress department for structural design.
