Horizontal tail lateral inertia load bearing hinge joint of civil aircraft

Abstract

The invention relates to a civil airliner horizontal tail lateral inertia load bearing hinge joint. A fuselage frame and a horizontal tail rear beam are coaxially arranged through a hinge joint of which the structure is completely symmetrical; the hinge joint consists of a single-lug pivot joint, a double-lug pivot joint, a horizontal tail lateral load joint, a Y-shaped pivot, a diagonal draw barand a bearing; a bearing is arranged in the through hole of the single-lug pivot joint; wherein an inner ring of the bearing is coaxially matched with the Y-shaped pivot, two ends of the Y-shaped pivot respectively extend out of the double-lug pivot joint, one end of the Y-shaped pivot is connected with the horizontal tail lateral load joint, the horizontal tail lateral load joint is vertically supported on the surface of the horizontal tail rear beam, the other end of the Y-shaped pivot is hinged with one end of the diagonal draw bar, and the other end of the diagonal draw bar is hinged on the fuselage frame. According to the hinge joint, the two sides bear lateral loads, the structure is simple, the number of parts is small, the weight is light, the most important point is that the bearing only bears in-plane loads, standard parts can be selected, the civil aircraft section development efficiency is improved, and the cost is reduced.

Description

technical field [0001] The invention relates to a lateral inertial load bearing hinge joint of a horizontal tail of a civil passenger aircraft, and belongs to the field of interface connection design of a horizontal tail of a civil passenger aircraft and a fuselage. Background technique [0002] At present, the horizontal tail and the rear fuselage of civil airliners are usually connected by two rear hinge joints, and the inertial load parallel to the main hinge axis passes through the single (left) hinge joint of the horizontal tail and the same side ( Left) Transverse struts are transferred to the fuselage frame. The advantage of this structure is that the assembly of the flat tail is simple. It only needs to ensure the part manufacturing and assembly accuracy of the joint on one side (left side), and the joint on the other side (right side) can be assembled with a large gap; the disadvantage is that the joint on one side (left side) ) The key structural bearings in the j...

AI Technical Summary

Problems solved by technology

The advantage of this structure is that the assembly of the flat tail is simple. It only needs to ensure the part manufacturing and assembly accuracy of the joint on one side (left side), and the joint on the other side (right side) can be assembled with a large gap; the disadvantage is that the joint on one side (left side) ) The key structural bearings in the joint bear large out-of-plane loads, and foreign suppliers are required to provide customized parts. At the same time, the timeliness of foreign suppliers' supply cannot be guaranteed, and the risk is high

Images