Composite material beam joint

Abstract

The invention discloses a composite material beam joint. The composite material beam joint comprises a beam flange (2) and a beam web (3), wherein the beam web (3) comprising a sandwich (4) and a loadtransmission link (1) together as an intermediate sandwich of the beam web (3), the load transmission link (1) being arranged in the longitudinal direction of the beam, the load transmission link (1)comprising a link (5), an intermediate piece (6) and a bushing (7), and the chain link (5) being sheathed on the bushing (7), the middle piece (6) fills the remaining space in the chain ring (5), andthe lining (7) and a connecting hole in a panel of the beam web (3) are equal in size and coaxial. According to the composite material beam joint, the load transmission chain ring is added in the composite material beam to reduce the edge distance and the end distance of the connecting lugs of the beam joint, so the connecting height is increased, connecting efficiency is improved, the weight isreduced, and the application mode of the composite material beam is increased.

Description

technical field [0001] The invention belongs to the technical field of composite material structure design, and in particular relates to a composite material beam joint. Background technique [0002] Although composite materials are widely used in aircraft structures, the aircraft wing structure with a beam layout needs to be connected to the fuselage through the joint lugs on the beams, which limits the application of all-composite materials on the load-carrying beams. An important The reason is that the joints on composite beams are not easy to design. From the perspective of connection efficiency, it is better to set the connecting lugs of the wing body on the beam flange or to increase the distance between the connecting bolts of the wing body as much as possible. It is easy to deal with metal beams, but it is very difficult for composite materials, so the connecting holes are generally set There are no special connection lugs on the beam web. Because the mechanical co...

AI Technical Summary

Problems solved by technology

[0002] Although composite materials are widely used in aircraft structures, the aircraft wing structure with a beam layout needs to be connected to the fuselage through the joint lugs on the beams, which limits the application of all-composite materials on the load-carrying beams. An important The reason is that the joints on composite beams are not easy to design

From the perspective of connection efficiency, it is better to set the connecting lugs of the wing body on the beam flange or to increase the distance between the connecting bolts of the wing body as much as possible. It is easy to deal with metal beams, but it is very difficult for composite materials, so the connecting holes are generally set On beam webs without dedicated connection lugs

Because the mechanical connection holes of composite materials require larger side distances, the connection height is greatly reduced, the nail load is increased, and the connection efficiency is greatly reduced. Larger bolt diameters and thicker connection lugs are required, which seriously restricts the use of composite materials Application on main load-carrying beams

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