CN207191395U - A kind of high-mechanic joint - Google Patents

Abstract

The utility model provides a kind of high-mechanic joint, it is arranged at the edge of aircraft wing Composite Panels, Composite Panels are by setting Composite Panels A (1) jaggy and assembly to be formed in the Composite Panels B (2) of the indentation, there, high-mechanic joint (3) is wherein provided through on Composite Panels B (2), both the high-mechanic joint (3) and Composite Panels B (2) are integrated part, and the erection method between two wallboards is：The sides of Composite Panels B (2) one are bent to form a step (4), Composite Panels B (2) is overlapped on Composite Panels A (1) by the step (4), and between skeleton (5) of the step (4) flush-mounted in Composite Panels A (1) and thereon.High-mechanic joint provided by the utility model, the narrow side configuration of multiple material wallboard can be eliminated, avoid the hidden danger of the narrow side damage of Composite Panels, and posting and the functional requirement of aircraft target ship and joint can be ensured.

Description

A kind of high-mechanic joint

Technical field

The utility model belongs to field of airplane structure, and in particular to a kind of high-mechanic joint.

Background technology

Modern combat aircraft is largely using composite material parts to reduce airframe-to-fuel weight ratio, such as composite machine alar wall Plate, fuselage fuel cell wallboard etc..These parts are mostly important or even crucial load-carrying member.In airplane design, often have in fuel tank The design problem of multiple material wallboard edge installation high-mechanic joint.In order that the top load on joint steadily, efficiently passes through again Material wallboard and then it is transitioned into inner skeleton, it usually needs joint is designed to overall structure, now then needed in multiple material wallboard One big opening of upper setting, the neighbouring multiple narrow side of material wallboard that is open not only influence posting, and are also easy to produce layering, peel off equivalent damage, As shown in Figure 1 to Figure 3.

Utility model content

The purpose of this utility model is to provide a kind of high-mechanic joint, overcome or alleviated by prior art it is at least one on State defect.

The purpose of this utility model is achieved through the following technical solutions：A kind of high-mechanic joint, is arranged at aircraft wing and answers The edge of condensation material wallboard, the Composite Panels are by setting Composite Panels A jaggy and assembly to be lacked in this Composite Panels B at mouthful is formed, and the high-mechanic joint, the high-mechanic are wherein provided through on Composite Panels B Both joint and Composite Panels B are integrated part.

Preferably, the sides of Composite Panels B mono- are bent to form a step, and Composite Panels B passes through this Rank is overlapped on the Composite Panels A, and between skeleton of the step flush-mounted in Composite Panels A and thereon.

Preferably, the Composite Panels B is except at stepped locations thereon, its upper and lower two sides with it is described compound It is concordant that material wallboard A is engaged side.

A kind of beneficial effect of high-mechanic joint provided by the utility model is, avoids the narrow side of Composite Panels Configuration, not only eliminates the damage risk on the narrow side of multiple material, and has recovered the overall posting and function of wallboard, while the structure risk It is minimum, it can be applied to aircraft body structure design and repair field, it is easy to spread, there is larger practical value.

Brief description of the drawings

Fig. 1 is existing joint schematic view of the mounting position；

Fig. 2 is the top view of existing joint installation form；

Fig. 3 is the upward view of existing joint installation form；

Fig. 4 is the utility model high-mechanic joint installation form schematic diagram.

Reference：

1- Composite Panels A, 2- Composite Panels B, 3- high-mechanics joint, 4- steps, 5- skeletons.

Embodiment

To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.In the accompanying drawings, from beginning Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Described reality It is the utility model part of the embodiment to apply example, rather than whole embodiments.Below with reference to the embodiment of accompanying drawing description It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made Example, belong to the scope of the utility model protection.

High-mechanic joint of the present utility model is described in further details below in conjunction with the accompanying drawings.

As shown in figure 4, a kind of high-mechanic joint, the edge of aircraft wing Composite Panels is arranged at.Composite Wallboard is by setting Composite Panels A1 jaggy and assembly to be formed in the Composite Panels B2 of the indentation, there, wherein multiple High-mechanic joint 3 is provided through on condensation material wallboard B2, both the high-mechanic joint 3 and Composite Panels B2 are integrated Part.Erection method between two Composite Panels is selected specifically to：The sides of Composite Panels B2 mono- are bent to form a step 4, Composite Panels B2 are overlapped on Composite Panels A1 by the step 4, and the step 4 is flush-mounted in composite walls Between plate A1 and skeleton 5 thereon, cause Composite Panels B2 except the opening position of step 4 thereon, its upper and lower both sides after assembled It is concordant that face is engaged side with Composite Panels A1.

High-mechanic joint is installed on the design process at Composite Panels edge by brief description.

The position of intersecting point and axis of high-mechanic joint are determined first.Enter then according to function, constraints, load-up condition etc. The preliminary configuration design of row and calculating, primarily determine that the profile, size and parameter of joint.Then calculate joint and pass through composite walls After plate, the opening size of wallboard, and calculate the narrow side size of opening near zone.The narrow side of Composite Panels is removed again, Harden structure is designed on joint, is allowed to overlap with Composite Panels plane, and be connected with Composite Panels.Finally synthesis is examined The configuration of each design constraints such as worry intensity, rigidity, function, butt joint and harden structure optimizes design, determines each size Parameter.

It is described above, only specific embodiment of the present utility model, but the scope of protection of the utility model is not limited to In this, any one skilled in the art is in the technical scope that the utility model discloses, the change that can readily occur in Change or replace, should all cover within the scope of protection of the utility model.Therefore, the scope of protection of the utility model should be with described Scope of the claims is defined.

Claims (3)

1. a kind of high-mechanic joint, it is arranged at the edge of aircraft wing Composite Panels, it is characterised in that the composite wood Material wallboard is made up of setting Composite Panels A (1) jaggy and assembly in the Composite Panels B (2) of the indentation, there, The high-mechanic joint (3) is wherein provided through on Composite Panels B (2), the high-mechanic joint (3) and composite walls Both plate B (2) are integrated part.

2. high-mechanic joint according to claim 1, it is characterised in that the side edge bendings of Composite Panels B (2) one A step (4) is formed, Composite Panels B (2) is overlapped on the Composite Panels A (1) by the step (4), and Between skeleton (5) of the step (4) flush-mounted in Composite Panels A (1) and thereon.

3. high-mechanic joint according to claim 2, it is characterised in that the Composite Panels B (2) is except platform thereon Rank (4) opening position, it is concordant that its upper and lower two sides is engaged side with the Composite Panels A (1).