CN211543854U - Integral machining groove type beam for airplane structure - Google Patents
Integral machining groove type beam for airplane structure Download PDFInfo
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- CN211543854U CN211543854U CN201922395031.2U CN201922395031U CN211543854U CN 211543854 U CN211543854 U CN 211543854U CN 201922395031 U CN201922395031 U CN 201922395031U CN 211543854 U CN211543854 U CN 211543854U
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- web
- rib
- horizontal edge
- channel beam
- ribs
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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 adds channel beam, this channel beam contains web and upper and lower horizontal edge strip, its characterized in that, has a plurality of strengthening rib strips along length direction vertical distribution on the channel beam, and each strengthening rib strip contains a trapezoidal rib that is located the web outside and two be located the horizontal edge strip, the horizontal edge strip in the lower level and the inboard oblique rib of web. According to the groove-shaped beam, the web plate, the upper horizontal edge strips, the lower horizontal edge strips and the reinforcing rib strips are integrally machined, so that 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 beam web plate, so that the layout space of the inner side of the channel beam is large, and the usable space of the airplane structure is increased.
Description
Technical Field
The application belongs to the field of aviation structural design, and particularly relates to an integrated machining groove beam for an airplane structure.
Background
Channel beams are typical structures found in modern aircraft construction and include a web and horizontal flanges located above and below the web. Typically, channel beams bear in-plane shear loads in the vertical webs; the horizontal flanges carry the tensile and compressive loads while carrying the loads transmitted by the connected structure. In actual design, the horizontal edge strip of the channel beam has certain requirements on supporting rigidity, and under some conditions (for example, structural space is limited due to the reason of arrangement systems), a conventional strut cannot be arranged.
Disclosure of Invention
The application aims to overcome the defects that the service life of a traditional mechanically-connected or welded channel beam is not long, the structural efficiency is not high, and the space between a web and an upper horizontal edge strip and a lower horizontal edge strip is limited, and provides an integrated machining channel beam for an aircraft structure.
The utility model provides an aircraft structure is with whole machine adds channel beam, this channel beam contains web and upper horizontal flange strip, lower horizontal flange strip, its characterized in that has a plurality of strengthening rib along length direction vertical distribution on the channel beam, and each strengthening rib contains a trapezoidal rib that is located the web outside and two diagonal rib that are located upper horizontal flange strip, lower horizontal flange strip and web inboard.
The trapezoidal ribs and the inclined ribs of each reinforcing rib are positioned on the same plane, and the plane is perpendicular to the beam web.
The inclined edge of the trapezoidal rib is parallel to the edge of the inclined rib.
The connecting line of the inflection point of the short edge of the trapezoidal rib and the end point of the adjacent oblique rib is vertical to the web plate.
And a distance is reserved between the two inclined ribs which are positioned at the upper horizontal edge strip and the lower horizontal edge strip and at the inner side of the web plate.
The beneficial effect of this application lies in: 1) according to the groove-shaped beam, the web plate, the upper horizontal edge strips, the lower horizontal edge strips and the reinforcing rib strips are integrally machined, so that 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 beam web plate, so that the layout space of the inner side of the channel 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 integral machined channel beam for an aircraft structure.
Fig. 2 is a schematic diagram of the position relationship between the diagonal ribs and the channel beam.
Fig. 3 is a schematic diagram of the position relationship between the trapezoidal ribs and the channel beams.
The numbering in the figures illustrates: 1 web, 2 upper horizontal marginal strips, 3 lower horizontal marginal strips, 4 trapezoidal ribs and 5 oblique ribs.
Detailed Description
Referring to the drawings, the integral machined channel 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 channel beam along the length direction, and each reinforcing rib comprises a trapezoidal rib 4 positioned on the outer side of the web plate and two inclined ribs 5 positioned on the upper horizontal edge strip 2, the lower horizontal edge strip 3 and the inner side of the web plate.
The trapezoidal 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.
The inclined edge of the trapezoidal rib 4 is parallel to the edge of the inclined rib 5.
The connecting line of the inflection point of the short edge of the trapezoidal rib 4 and the end point of the adjacent oblique rib 5 is vertical to the beam web 1.
And a distance is reserved between the two oblique ribs 5 positioned on the inner sides of the upper horizontal edge strip 2, the lower horizontal edge strip 3 and the web plate in the height direction of the web plate.
Claims (5)
1. The utility model provides an aircraft structure is with whole machine adds channel beam, this channel beam contains web and upper and lower horizontal edge strip, its characterized in that, has a plurality of strengthening rib strips along length direction vertical distribution on the channel beam, and each strengthening rib strip contains a trapezoidal rib that is located the web outside and two be located the horizontal edge strip, the horizontal edge strip in the lower level and the inboard oblique rib of web.
2. An integral machined channel beam for an aircraft structure as defined in claim 1, wherein said trapezoidal ribs and said tilted ribs of each of said reinforcing ribs are located in a common plane which is perpendicular to said web.
3. An integral machined channel beam for an aircraft structure as defined in claim 1 or claim 2 wherein said tapered edges of said trapezoidal ribs are parallel to the edges of said tapered ribs.
4. An integral machined channel beam for an aircraft structure as defined in claim 3, wherein a line connecting an inflection point of a short side of said trapezoidal rib with an end point of said adjacent diagonal rib is perpendicular to said web.
5. An integral machined channel beam for an aircraft structure as defined in claim 3 wherein there is a spacing in the direction of web height between the upper and lower horizontal flanges and the diagonal ribs inboard of the web.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922395031.2U CN211543854U (en) | 2019-12-26 | 2019-12-26 | Integral machining groove type beam for airplane structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922395031.2U CN211543854U (en) | 2019-12-26 | 2019-12-26 | Integral machining groove type beam for airplane structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211543854U true CN211543854U (en) | 2020-09-22 |
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ID=72510291
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922395031.2U Active CN211543854U (en) | 2019-12-26 | 2019-12-26 | Integral machining groove type beam for airplane structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211543854U (en) |
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2019
- 2019-12-26 CN CN201922395031.2U patent/CN211543854U/en active Active
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