CN211543856U - Whole machine adds I-beam for aircraft structure - Google Patents
Whole machine adds I-beam for aircraft structure Download PDFInfo
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- CN211543856U CN211543856U CN201922427949.0U CN201922427949U CN211543856U CN 211543856 U CN211543856 U CN 211543856U CN 201922427949 U CN201922427949 U CN 201922427949U CN 211543856 U CN211543856 U CN 211543856U
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- web
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- web plate
- horizontal edge
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The utility model provides an aircraft structure is with whole machine and is with I-beam, this I-beam contains web and upper and lower horizontal edge strip, and it has a plurality of strengthening ribs to distribute along length direction vertical distribution on the I-beam, and each strengthening rib contains a rectangle rib that is located web one side and two oblique ribs that are located upper and lower horizontal edge strip and web opposite side. According to the I-beam, the web plate, the upper horizontal edge strips, the lower horizontal edge strips and the reinforcing rib strips are integrally machined, so that the connection is reduced, the integral weight of the beam is reduced, and the service life of the beam is prolonged; the reinforcing ribs are uniformly distributed on the beam web plate in sections, and meanwhile, the plane of each reinforcing rib is perpendicular to the beam web plate, so that the stability of the beam web plate is improved, and the structural efficiency is high; the reinforcing ribs are distributed on the two sides and the upper end and the lower end of the web plate, so that the layout space of the inner side of the I-beam is large, and the usable space of the airplane structure is increased.
Description
Technical Field
The application belongs to aviation structural design field, concretely relates to aircraft structure adds I-beam with whole machine.
Background
An i-beam is a typical structure commonly found in modern aircraft structures and comprises a web and horizontal flanges located above and below the web. Typically, i-beam vertical webs carry in-plane shear loads; the horizontal flanges carry the tensile and compressive loads while carrying the loads transmitted by the connected structure. During actual design, the horizontal flange of the I-beam has certain requirements on supporting rigidity, and under some conditions (for example, structural space is limited due to the reason of arrangement systems), conventional pillars cannot be arranged.
Disclosure of Invention
The utility model provides an aim at, in order to change traditional mechanical connection or weld the shortcoming that I-beam life is not long, structural efficiency is not high, the web and the space between the upper and lower horizontal flange are limited, provide an aircraft structure and add I-beam with whole machine.
The utility model provides an aircraft structure is with whole machine with I-beam, this I-beam contains web and upper and lower horizontal edge strip, its characterized in that, has a plurality of strengthening ribs along length direction vertical distribution on the I-beam, and each strengthening rib contains a rectangle rib that is located the web outside and two diagonal ribs that are located upper and lower horizontal edge strip and web inboard.
The rectangular ribs and the inclined ribs of each reinforcing rib are positioned on the same plane, and the plane is perpendicular to the beam web.
One side edge of each rectangular rib is connected with the web plate, the upper edge of each rectangular rib is connected with the upper edge strip of the I-beam, and the lower edge of each rectangular rib is connected with the lower edge strip of the I-beam.
And a space is arranged between the upper horizontal edge strip and the lower horizontal edge strip and between the two oblique ribs on the other side of the web plate in the height direction of the web plate.
The beneficial effect of this application lies in: 1) according to the I-beam, the web plate, the upper horizontal edge strips, the lower horizontal edge strips and the reinforcing rib strips are integrally machined, so that the connection is reduced, the integral weight of the beam is reduced, and the service life of the beam is prolonged; 2) the reinforcing ribs are uniformly distributed on the beam web plate in sections, and meanwhile, the plane of each reinforcing rib is perpendicular to the beam web plate, so that the stability of the beam web plate is improved, and the structural efficiency is high; 3) the reinforcing ribs are distributed on the two sides and the upper end and the lower end of the web plate, so that the layout space of the inner side of the I-beam is large, and the usable space of the airplane structure is increased.
The present application is described in further detail below with reference to examples.
Drawings
FIG. 1 is a schematic view of an integrally machined spar for an aircraft structure.
Fig. 2 is a schematic diagram of the position relationship between the diagonal rib and the i-beam.
Fig. 3 is a schematic diagram of the position relationship between the rectangular ribs and the i-beam.
The numbering in the figures illustrates: 1 web, 2 upper horizontal edge strips, 3 lower horizontal edge strips, 4 rectangular ribs and 5 inclined ribs.
Detailed Description
Referring to the attached drawings, the integral machined I-beam for the airplane structure comprises a web plate 1, an upper horizontal edge strip 2 and a lower horizontal edge strip 3, and is characterized in that a plurality of reinforcing ribs are vertically distributed on the I-beam along the length direction, and each reinforcing rib comprises a rectangular rib 4 positioned on one side of the web plate 1 and two inclined ribs 5 positioned on the upper horizontal edge strip, the lower horizontal edge strip and the other side of the web plate.
The rectangular ribs 4 and the inclined ribs 5 of each reinforcing rib are positioned on the same plane, and the plane is perpendicular to the beam web plate 1.
One side edge of the rectangular rib 4 is connected with the beam web plate 1, the upper edge of the rectangular rib 4 is connected with the upper horizontal edge strip 2 of the I-shaped beam, and the lower edge of the rectangular rib 4 is connected with the lower horizontal edge strip 3 of the I-shaped beam.
And a space is arranged between the upper horizontal edge strip 2, the lower horizontal edge strip 3 and the two oblique ribs 5 on the other side of the web plate 1 in the height direction of the web plate.
Claims (4)
1. The utility model provides an aircraft structure is with whole machine and is with I-beam, this I-beam contains web and upper and lower horizontal edge strip, its characterized in that, has a plurality of strengthening ribs along length direction vertical distribution on the I-beam, and each strengthening rib contains a rectangle rib that is located web one side and two diagonal ribs that are located upper and lower horizontal edge strip and web opposite side.
2. An integral machined i-beam for an aircraft structure as defined in claim 1 wherein said rectangular ribs and said angled ribs of each of said reinforcing ribs lie in a common plane which is perpendicular to said web.
3. An integral machined I-beam for an aircraft structure as defined in claim 1 or 2 wherein one side of said rectangular rib is connected to the web, the upper edge of said rectangular rib is connected to the upper edge of the I-beam, and the lower edge of said rectangular rib is connected to the lower edge of the I-beam.
4. An integral machined i-beam for an aircraft structure as in claim 3 wherein said upper and lower horizontal flanges are spaced from said two diagonal ribs on the opposite side of said web in the direction of the height of said web.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922427949.0U CN211543856U (en) | 2019-12-27 | 2019-12-27 | Whole machine adds I-beam for aircraft structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922427949.0U CN211543856U (en) | 2019-12-27 | 2019-12-27 | Whole machine adds I-beam for aircraft structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211543856U true CN211543856U (en) | 2020-09-22 |
Family
ID=72511170
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922427949.0U Active CN211543856U (en) | 2019-12-27 | 2019-12-27 | Whole machine adds I-beam for aircraft structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211543856U (en) |
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2019
- 2019-12-27 CN CN201922427949.0U patent/CN211543856U/en active Active
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