Aero-engine combined main shaft strength test device

The invention discloses a strength test device for a combined main shaft of an aero-engine. The strength test device comprises a frame body, a main shaft, an axial force loading assembly, a rotating bending moment loading assembly and a torque loading assembly. The main shaft comprises a fan shaft and a low-pressure turbine shaft which are of an integrated combined structure. The axial force loading assembly is arranged on the frame body and is used for loading axial force on a fan shaft and a low-pressure turbine shaft of the main shaft respectively; the rotating bending moment loading assembly is arranged on the frame body and is used for loading bending moments on a fan shaft and a low-pressure turbine shaft of the main shaft respectively; and the torque loading assembly is arranged on the frame body and is used for loading main torque and/or vibration torque on the fan shaft and the low-pressure turbine shaft of the main shaft. Compared with the prior art, the device has the beneficial effects that the de