Fuselage load applying device

The invention belongs to the field of strength testing, and particularly relates to a fuselage load applying device. The fuselage load applying device comprises multiple shearing force blocks, which are symmetrically fixed on strong frames on the left and right sides of an aircraft fuselage; a lever located at the bottom of the aircraft fuselage; double lugs of resultant force point, hinged at themidpoint position of the lever; first and second adjustment screws hinged to the end parts of the two ends of the lever, respectively; a first supporting plate, which is fixedly connected with the first adjustment screw and is provided with a neck matching the shearing force block on the side facing to the aircraft fuselage; and a second supporting plate, which is fixedly connected to the secondadjustment screw and is provided with a neck matching the shearing force block on the side facing to the aircraft fuselage. The fuselage load applying device provided by the invention applies a vertical downward load at the re