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Aircraft wing rib and production process thereof

A production process and rib technology, applied in the directions of wings, aircraft assembly, aircraft parts, etc., can solve the problems of rib fracture, low structural strength, slow flow rate, etc.

Active Publication Date: 2020-04-10
上海蓝享机械制造有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The above-mentioned existing technical solutions have the following defects: However, due to the need to strictly control the weight of the aircraft wing during the manufacturing process of the aircraft wing, the stability of the flight can be maintained while reducing the weight of the aircraft as much as possible.
The light weight of ordinary wing ribs results in low structural strength, although it can withstand the forces from other parts of other wings to a certain extent
However, during the flight of the aircraft, once a strong airflow is encountered, the airflow at the leading edge of the wing is blocked, the flow velocity slows down, and the pressure increases suddenly. It is very easy to break the wing rib or squeeze other parts of the wing, causing damage to the wing
Therefore, the problem of low structural strength of the wing rib needs to be solved urgently

Method used

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  • Aircraft wing rib and production process thereof
  • Aircraft wing rib and production process thereof
  • Aircraft wing rib and production process thereof

Examples

Experimental program
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Effect test

Embodiment 1

[0067] refer to figure 1 , is an aircraft wing rib disclosed by the present invention, comprising a trapezoidal rib 1 and a support plate 2 fixedly connected to the edge of the rib 1, and one side of the rib 1 is fixedly connected with a plurality of criss-cross reinforcements 3 A mounting plate 4 is obliquely and fixedly connected to the edge of the side of the rib plate 1 away from the reinforcing member 3 . In this embodiment, the entire wing rib is preferably made of 7050-T7451 aluminum alloy material, and is cut into a specific shape by a CNC machining center, so all connection methods in this embodiment are integrally formed and fixedly connected.

[0068] The main alloying element of 7075 series aluminum alloy is zinc. Adding magnesium to the alloy containing 3%-75% zinc can form MgZn2 with significant strengthening effect, making the heat treatment effect of the alloy far better than that of aluminum-zinc binary alloy. Increasing the zinc and magnesium content in the ...

Embodiment 2

[0078] refer to image 3 , a production process for aircraft wing ribs, comprising the steps of:

[0079] Step S1: Design the macroscopic shape and microscopic structural parameters of the wing ribs through drawing software, and then transmit the data to the console of the CNC machining center through the computer.

[0080] Step S2: According to the raw materials provided by the warehouse, verify the furnace batch number, sawing material and quality inspection of the raw materials, and mark them on the raw materials.

[0081] In step S2, the raw material is preferably 7050-T7451 aluminum alloy plate, 7050-T7451 aluminum is a high-strength heat-treatable alloy with extremely high strength and resistance to exfoliation corrosion and stress corrosion cracking. The blank size is 650*430*88.9MM, 25.6*17*3.5IN, and the saw size is 590*410*88.9MM, 23.22*16.14*3.5IN. After precise sawing on the blank, the preliminary shape of the product is obtained, which is convenient for subseque...

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Abstract

The invention relates to an aircraft wing rib which comprises a trapezoidal rib plate and supporting plates integrally formed and fixedly connected to the edges of the rib plate, and a plurality of crisscross reinforcing pieces are fixedly connected to one face of the rib plate. A mounting plate is obliquely and fixedly connected to the edge of the face, away from the reinforcing pieces, of the rib plate, and the two ends, in the length direction, of the mounting plate are integrally formed and fixedly connected with the supporting plates. A lightening hole and a positioning hole are formed inthe rib plate, and a plurality of first mounting holes are formed in the mounting plate. Compared with a common wing rib formed through welding, the wing rib cut by a numerical control machining center is integrally formed, and the wing rib has the advantages of being high in structural strength and not prone to stress deformation. No redundant waste is generated after machining, so that good close fit with the internal structure of the aircraft wing can be realized, and the structural rigidity of the wing is effectively improved. The wing rib can bear and transmit large concentrated loads inthe plane of the wing rib or additional loads caused by structural discontinuity, and therefore the stability of the wing is improved.

Description

technical field [0001] The invention relates to the technical field of manufacturing aircraft parts, in particular to an aircraft wing rib and a production process thereof. Background technique [0002] The wing rib is one of the important components of the aircraft wing. It is the lateral force skeleton of the wing. It is generally consistent with the shape of the airfoil. It is used to support the skin of the aircraft wing and maintain the cross-sectional shape of the wing. Aircraft skin refers to the three-dimensional component that surrounds the frame structure of the aircraft and is fixed on the frame with adhesives or rivets to form the aerodynamic shape of the aircraft. The skin structure composed of aircraft skin and skeleton has a large bearing capacity and rigidity, but its own weight is very light, and it plays the role of bearing and transmitting aerodynamic loads. [0003] In the prior art, the structural function of common ribs is to maintain the required shap...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64F5/10B64F5/60B64C3/18
CPCB64F5/10B64F5/60B64C3/187
Inventor 张金伍
Owner 上海蓝享机械制造有限公司
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