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Method and device for calculating effective width of skin under fuselage wall plate axial compression load

A technology of effective width and fuselage panels, applied in the direction of instruments, geometric CAD, electrical digital data processing, etc., can solve the problems of unfavorable aircraft weight reduction and economy, and achieve the effect of accurate calculation, simple calculation and

Active Publication Date: 2021-04-23
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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Problems solved by technology

At present, the effective width of the lower skin of the long truss in engineering design is often taken as 30*skin thickness t, which is relatively conservative and is not conducive to aircraft weight reduction and economy. Therefore, a new calculation method for the effective skin width needs to be proposed

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  • Method and device for calculating effective width of skin under fuselage wall plate axial compression load
  • Method and device for calculating effective width of skin under fuselage wall plate axial compression load
  • Method and device for calculating effective width of skin under fuselage wall plate axial compression load

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Embodiment Construction

[0037] When the fuselage panel unit bears compressive loads, the girder bears most of the loads. In addition, the skin also bears a non-negligible load. The effective width of the skin (such as figure 1 Be) load capacity shown is an important part of the load capacity of the siding. At present, there are two methods for calculating the load-carrying capacity of the slab in engineering. The most convenient calculation method is that the effective width of the skin under the girder is 30*skin thickness t, but this method is relatively conservative, which is not conducive to aircraft weight reduction and economy; In addition, there is also a relatively mature empirical method for the calculation of the strength of the wall panel, but the calculation process of the empirical method is complicated and has many steps, and the effective width of the skin needs multiple iterations, and because of copyright issues, only a small number of aircraft design institutions hold it. Applicabil...

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Abstract

The invention belongs to the field of fuselage wall plate axial compression load calculation methods, and relates to a method and device for calculating the effective width of a skin under a fuselage wall plate axial compression load. The method comprises the steps of: determining the average thickness t of wallboard unit skin; determining an influence coefficient c of a fastener on the effective width, wherein the fastener is used for connecting the skin and the stringer; determining the rigidity A of the stringer and the rigidity B of the skin; and according to the average thickness t of the skin, the influence coefficient c of the fastener on the effective width, the rigidity A of the stringer and the rigidity B of the skin, determining the effective width be of the skin under the axial compression load of the fuselage wall plate. Effective skin width calculation is simple and accurate, the problem that an original calculation method is conservative is solved, engineering personnel can conveniently apply the method to aircraft design, great value is brought to weight reduction of aircraft structures and creation of economic value, and the method is suitable for structural strength calculation of various fuselage wall plates.

Description

technical field [0001] The invention belongs to the field of calculation methods for the axial compression load of fuselage wall panels, and relates to a method and a device for calculating the effective width of a skin under the axial compression load of fuselage wall panels. Background technique [0002] The panel is the main load-carrying structure of the transport aircraft fuselage, and its bearing capacity under tension, compression, shear, bending and torsional loads is the focus of aircraft design research. [0003] Since the skins are all thin plates, buckling will occur when the load is much lower than the design load of the aircraft. After the skin buckles under compression, the stress of the part of the skin under the stringer will continue to increase with the increase of the load. This part of the skin is called Effective skin for axial load bearing. At present, the effective width of the lower skin of the girder in engineering design is usually taken as 30*ski...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F119/14
CPCG06F30/15G06F2119/14
Inventor 杜鹏良张新全刘彦杰李明强李禹冯军
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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