A resonance fatigue test was carried out on the rear fuselage and empennage of a CT4 aircraft. The structure was supported in a reaction frame, and was excited at the resonant frequency of the fuselage torsional mode (9 Hz) by electromagnetic shakers connected to the tailplane. The loading spectrum applied was based on strain sequence data obtained from flight trials. Regular inspections of the structure were carried out, and several areas on the rear fuselage and empennage were identified as being prone to fatigue damage.
Resonance Fatigue Test of the Empennage of a CT4 Aircraft
1985
36 pages
Report
Keine Angabe
Englisch
Aircraft , Tail assemblies , Aerodynamic control surfaces , Shaking , Fuselages , Torsion , Spectra , Frames , Response , Fatigue tests(Mechanics) , Resonance , Sequences , Strain(Mechanics) , Flight testing , Inspection , Structural properties , Damage , Fatigue(Mechanics) , Resonant frequency , Training aircraft , Foreign technology , CT-4 aircraft