METHOD OF FATIGUE TESTING A COMPLEX STRUCTURE
FIG2 is an oblique view of a complex structure of the aircraft of FIG1
Referring to FIG2, an oblique view of a complex structure 200 is shown. Complex structure 200 generally comprises a truss structure that forms the airframe structure of aircraft 100. As such, complex structure 200 may form the airframe structure for fuselage 102, tail boom 104, and/or landing gear 114 of aircraft 100. Complex structure 200 may also provide the airframe structure or support structure for a combustion engine, a transmission, controls for the main rotor system 110, a main rotor gearbox, and/or a tail rotor gearbox of aircraft 100. Still further, complex structure 200 may provide the airframe structure for one or more vertical or horizontal stabilizers, wings, and/or other components of aircraft 100. Complex structure 200 is generally formed from a plurality of welded or otherwise joined components (e.g., members 202, 203, 204) and/or subassemblies. As such, complex structure 200 comprises multiple load paths throughout the complex structure 200.
oblique view
201
joint joints
202
members
203
member
206
displacement instrument displacement instruments
204
member
205
strain gauges strain gauge
200
complex structure
['3. The method (800) of claim 2, wherein:- (i) the flight loads are determined based on at least one of measured displacements and measured strains experienced by the complex airframe structure (200); and/or (ii) wherein the fatigue sensitive points are grouped into families based on at least one of (1) the type of joint and (2) the response to the to the flight loads.']