CN217945492U - Aircraft floor stiffening beam - Google Patents
Aircraft floor stiffening beam Download PDFInfo
- Publication number
- CN217945492U CN217945492U CN202222123768.0U CN202222123768U CN217945492U CN 217945492 U CN217945492 U CN 217945492U CN 202222123768 U CN202222123768 U CN 202222123768U CN 217945492 U CN217945492 U CN 217945492U
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- Prior art keywords
- plate
- bottom plate
- reinforcing
- top plate
- mounting hole
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- Expired - Fee Related
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 66
- 230000002787 reinforcement Effects 0.000 claims description 8
- 238000000034 method Methods 0.000 claims description 4
- 230000008093 supporting effect Effects 0.000 abstract description 6
- 230000000694 effects Effects 0.000 abstract description 4
- 230000007547 defect Effects 0.000 description 3
- 238000010030 laminating Methods 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
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Abstract
The utility model provides an airplane bottom plate stiffening beam, which comprises a top plate (1) and a bottom plate (2), wherein a middle vertical plate (3) is connected in the middle between the top plate (1) and the bottom plate (2); reinforcing ribs are arranged between the left reinforcing plate and the middle plate and between the right reinforcing plate and the middle plate, lightening holes are formed between the adjacent reinforcing ribs and the top plate or the bottom plate, the connecting strength and the supporting stability are improved through the reinforcing ribs, and the self lightening effect of the reinforcing beam is realized through the lightening holes; the right end is connected with the external fixing piece through the right mounting hole of the bottom plate and the mounting hole of the right reinforcing plate respectively, and the left end is connected with the external fixing piece through the left mounting hole of the bottom plate and the mounting hole of the left reinforcing plate respectively, so that the connection with the external fixing piece is realized from the two dimensions of the upper direction, the lower direction and the front-back direction respectively, and the connection is stable, safe and reliable.
Description
Technical Field
The utility model relates to an aircraft bearing structure's technical field, concretely relates to aircraft bottom plate stiffening beam.
Background
Aircraft bottom plate supports plays important role to aircraft inner space, thereby satisfy the stable supporting effect in order to guarantee inside passenger and goods safety and stability at the flight in-process on the one hand, thereby on the other hand need go on the aircraft in-process with lower quality and less volume in order to realize less windward area and lighter quality and reduce the windage fuel saving, consequently along with the continuous development of science and technology, current aircraft bottom plate bearing structure can not satisfy current needs far away, current aircraft bottom plate bearing structure needs external fixing pieces such as more bolts to realize location locking function on the one hand, the locking function of on the other hand single dimension is connected and support stability not enough in the proruption situation when facing the flight. Accordingly, it is desirable to provide a bottom plate support structure that is reliable in strength and low in mass.
SUMMERY OF THE UTILITY MODEL
In order to solve the defects and the defects existing in the prior art, the utility model provides an aircraft bottom plate stiffening beam.
For solving the above-mentioned prior art defect and not enough, the utility model provides a scheme as follows:
the aircraft floor stiffening beam comprises a top plate and a bottom plate, wherein a middle vertical plate is connected to the middle part between the top plate and the bottom plate; the method is characterized in that:
a right vertical plate and a right vertical plate are connected to the right side between the top plate and the bottom plate; a right reinforcing plate is arranged in a space enclosed by the right vertical plate, the top plate and the bottom plate;
a left reinforcing plate is arranged on the left side between the top plate and the bottom plate;
reinforcing ribs are arranged between the left reinforcing plate and the middle vertical plate and between the right reinforcing plate and the middle vertical plate, and lightening holes are formed between the adjacent reinforcing ribs and the top plate or the bottom plate.
As a further preferred embodiment of the present invention, the front and rear sides of the top plate are respectively provided with a top plate positioning protrusion and a top plate positioning groove.
As a further preferred embodiment of the present invention, the right end of the bottom plate is provided with a bottom plate positioning portion, the front and rear sides of the bottom plate positioning portion are respectively provided with a bottom plate positioning protrusion and a bottom plate positioning groove, and the bottom plate right mounting hole is provided in the bottom plate positioning protrusion.
As a further preferred embodiment of the present invention, the left end of the bottom plate extends to the rear side and is provided with a bottom plate extension portion, and a bottom plate left mounting hole is provided inside the bottom plate extension portion.
As a further preferred embodiment of the present invention, a single right reinforcing plate mounting hole is provided inside the right reinforcing plate.
As a further preferred embodiment of the present invention, a plurality of left reinforcing plate mounting holes are provided in the inside of the left reinforcing plate, and the aperture of each left reinforcing plate mounting hole is smaller than the aperture of the right reinforcing plate mounting hole.
As a further preferred embodiment of the present invention, the right two vertical plates and the bottom plate further have end reinforcing plates disposed therebetween.
As a further preferred embodiment of the present invention, the top plate includes a right top plate and a left top plate, the right top plate and the left top plate are connected to the top of the middle standing plate, and the middle standing plate is located at the highest point position of the right top plate and the left top plate in the left-right direction.
As a further preferred embodiment of the present invention, the bottom plate includes a right bottom plate and a left bottom plate, the right bottom plate and the left bottom plate are connected to the bottom of the middle standing plate, and the middle standing plate is located at the lowest point position of the right bottom plate and the left bottom plate in the left-right direction.
Compared with the prior art, the utility model discloses the technological effect that can realize includes:
1) The utility model provides an aircraft bottom plate supporting beam is provided with the stiffening rib between left reinforcing plate and the well neutral plate and between right reinforcing plate and the well neutral plate, has seted up the lightening hole between adjacent stiffening rib and roof or the bottom plate, increases joint strength and support stability through the stiffening rib, realizes the self of stiffening beam through the lightening hole and subtracts heavy effect.
2) The utility model provides an aircraft bottom plate supporting beam realizes being connected with external fixing spare through bottom plate right side mounting hole and right reinforcing plate mounting hole respectively at the right-hand member, realizes being connected with external fixing spare through bottom plate left side mounting hole and left reinforcing plate mounting hole respectively at the left end to realize being connected with external fixing spare from two dimensions of upper and lower direction and fore-and-aft direction respectively, connect stable safe and reliable.
3) The utility model provides an aircraft bottom plate supporting beam is located left roof and right roof hookup location peak through the center pillar top, and center pillar bottom is located left bottom plate and right bottom plate hookup location minimum to it changes into the polygon to become roof and bottom plate by single straight line shape, thereby when being convenient for fix a position with the better shape laminating of external fixing such as aircraft bottom plate, reduces the use of extra setting element, for the single straight line shape panel of whole strip, the possibility of unexpected damage reduces, intensity is more stable.
Drawings
Fig. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a front view of the structure of the present invention.
Fig. 3 is a bottom view of the structure of the present invention.
Fig. 4 is a top view of the present invention.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "upper", "lower", "inner", "outer", "front end", "rear end", "both ends", "one end", "the other end" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of description, but do not indicate or imply that the device or element to which the reference is made must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "connected," and the like are to be construed broadly, and for example, "connected" may be either fixedly connected or detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
[ first embodiment ]
A first embodiment of the present invention is provided as shown in fig. 1-4, in which an aircraft floor reinforcement beam is provided.
As shown in fig. 1, the airplane floor reinforcement beam includes a top plate 1 and a bottom plate 2, and a middle standing plate 3 is connected to a middle portion between the top plate 1 and the bottom plate 2.
As shown in fig. 1-2, in the present embodiment, the top plate 1 includes a right top plate 1-1 and a left top plate 1-2, the right top plate 1-1 and the left top plate 1-2 are connected to the top of the middle standing plate 3, and in the left-right direction, the middle standing plate 3 is located at the highest position of the right top plate 1-1 and the left top plate 1-2; the bottom plate 2 comprises a right bottom plate 2-1 and a left bottom plate 2-2, the right bottom plate 2-1 and the left bottom plate 2-2 are connected with the bottom of the middle vertical plate 3, and the middle vertical plate 3 is positioned at the lowest point position of the right bottom plate 2-1 and the left bottom plate 2-2 in the left-right direction; thereby change roof and bottom plate into polygon by single straight line shape to when being convenient for the location with the better shape laminating of external fixation such as aircraft bottom plate, reduce the use of extra setting element, for whole single straight line shape panel, the possibility of unexpected damage reduces, and intensity is more stable.
As shown in fig. 1-2, a right vertical plate 4 and a right vertical plate 5 are connected to the right side between the top plate 1 and the bottom plate 2; a right reinforcing plate 6 is arranged in a space enclosed by the right vertical plate 4, the right vertical plate 5, the top plate 1 and the bottom plate 2; the right reinforcing plate 6 is used for fixedly mounting the reinforcing beam on the right end of the airplane bottom plate;
a left reinforcing plate 7 is arranged on the left side between the top plate 1 and the bottom plate 2, and the reinforcing beam is fixedly arranged at the left end and the bottom plate of the airplane through the left reinforcing plate 7;
reinforcing ribs 8 are arranged between the left reinforcing plate 7 and the middle plate 3 and between the right reinforcing plate 6 and the middle plate 3, lightening holes 9 are formed between adjacent reinforcing ribs 8 and the top plate 1 or the bottom plate 2, the connecting strength and the supporting stability are improved through the reinforcing ribs, and the self lightening effect of the reinforcing beam is realized through the lightening holes.
As shown in FIG. 4, the front side and the rear side of the top plate 1 are respectively provided with a top plate positioning bulge 1-a and a top plate positioning groove 1-b, and the top plate is positioned and matched with the bottom plate of the top airplane through the top plate positioning bulge 1-a and the top plate positioning groove 1-b.
As shown in figure 3, the right end of the bottom plate 2 is provided with a bottom plate positioning part 2-3, the front side and the rear side of the bottom plate positioning part 2-3 are respectively provided with a bottom plate positioning bulge 2-a and a bottom plate positioning groove 2-b, and the bottom plate positioning bulge 2-a and the bottom plate positioning groove 2-b are used for realizing positioning matching with the airplane fixing piece at the bottom of the bottom plate.
As shown in fig. 3, a bottom plate right mounting hole 2-31 is formed inside the bottom plate positioning bulge 2-a; the left end of the bottom plate 2 extends towards the rear side and is provided with a bottom plate extending part 2-4, a bottom plate left mounting hole 2-41 is formed in the bottom plate extending part 2-4, and the connection between the airplane bottom plate reinforcing beam and an external fixing part is realized in the vertical direction through a bottom plate right mounting hole 2-31 and the bottom plate left mounting hole 2-41.
As shown in fig. 2, a single right reinforcing plate mounting hole 6-1 is formed in the right reinforcing plate 6; a plurality of left reinforcing plate mounting holes 7-1 are formed in the left reinforcing plate 7; the connection between the airplane bottom plate reinforcing beam and the external fixing piece is realized in the front and rear direction through the right reinforcing plate mounting hole 6-1 and the left reinforcing plate mounting hole 7-1.
In the present embodiment, it is preferable that the diameter of each of the left reinforcing plate mounting holes 7-1 is smaller than the diameter of the right reinforcing plate mounting hole 6-1 as required in accordance with the fixing mounting strength and the number of fixing members such as bolts.
As a further preferable mode of the present embodiment, as shown in fig. 2, an end reinforcing plate 10 is further provided between the right second vertical plate 5 and the bottom plate 2 to further enhance the connection strength of the end portion of the right end of the reinforcing beam.
When the reinforced beam is installed, the reinforced beam is arranged below an airplane bottom plate, the top plate is positioned and matched with the top airplane bottom plate through the top plate positioning bulge 1-a and the top plate positioning groove 1-b, and the bottom plate positioning bulge 2-a and the bottom plate positioning groove 2-b are positioned and matched with an airplane fixing piece at the bottom of the bottom plate; the connection between the airplane bottom plate reinforcing beam and the external fixing piece is realized in the up-down direction through the bottom plate right mounting hole 2-31 and the bottom plate left mounting hole 2-41, and the connection between the airplane bottom plate reinforcing beam and the external fixing piece is realized in the front-back direction through the right reinforcing plate mounting hole 6-1 and the left reinforcing plate mounting hole 7-1.
It will be evident to those skilled in the art that the invention is not limited to the details of the foregoing illustrative embodiments, and that the present invention may be embodied in other specific forms without departing from the spirit or essential attributes thereof. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Claims (9)
1. The aircraft floor stiffening beam comprises a top plate (1) and a bottom plate (2), wherein a middle vertical plate (3) is connected in the middle between the top plate (1) and the bottom plate (2); the method is characterized in that:
a right vertical plate (4) and a right vertical plate (5) are connected to the right side between the top plate (1) and the bottom plate (2); a right reinforcing plate (6) is arranged in a space enclosed by the right vertical plate (4), the right vertical plate (5), the top plate (1) and the bottom plate (2);
a left reinforcing plate (7) is arranged on the left side between the top plate (1) and the bottom plate (2);
reinforcing ribs (8) are arranged between the left reinforcing plate (7) and the middle plate (3) and between the right reinforcing plate (6) and the middle plate (3), and lightening holes (9) are formed between adjacent reinforcing ribs (8) and the top plate (1) or the bottom plate (2).
2. An aircraft floor stiffening beam according to claim 1, wherein: the front side and the rear side of the top plate (1) are respectively provided with a top plate positioning bulge (1-a) and a top plate positioning groove (1-b).
3. An aircraft floor reinforcement beam according to claim 1, wherein: the bottom plate positioning device is characterized in that a bottom plate positioning part (2-3) is arranged at the right end of the bottom plate (2), a bottom plate positioning bulge (2-a) and a bottom plate positioning groove (2-b) are respectively arranged on the front side and the rear side of the bottom plate positioning part (2-3), and a bottom plate right mounting hole (2-31) is formed in the bottom plate positioning bulge (2-a).
4. An aircraft floor reinforcement beam according to claim 1, wherein: the left end of the bottom plate (2) extends towards the rear side and is provided with a bottom plate extension part (2-4), and a bottom plate left mounting hole (2-41) is formed in the bottom plate extension part (2-4).
5. An aircraft floor reinforcement beam according to claim 1, wherein: a single right reinforcing plate mounting hole (6-1) is formed in the right reinforcing plate (6).
6. An aircraft floor reinforcement beam according to claim 1, wherein: a plurality of left reinforcing plate mounting holes (7-1) are formed in the left reinforcing plate (7), and the aperture of each left reinforcing plate mounting hole (7-1) is smaller than that of the right reinforcing plate mounting hole (6-1).
7. An aircraft floor reinforcement beam according to claim 1, wherein: an end reinforcing plate (10) is further arranged between the right two vertical plates (5) and the bottom plate (2).
8. An aircraft floor reinforcement beam according to claim 1, wherein: the top plate (1) comprises a right top plate (1-1) and a left top plate (1-2), the right top plate (1-1) and the left top plate (1-2) are connected with the top of the middle plate (3), and in the left-right direction, the middle plate (3) is located at the highest point position of the right top plate (1-1) and the left top plate (1-2).
9. An aircraft floor stiffening beam according to claim 1, wherein: the bottom plate (2) comprises a right bottom plate (2-1) and a left bottom plate (2-2), the right bottom plate (2-1) and the left bottom plate (2-2) are connected with the bottom of the middle vertical plate (3), and the middle vertical plate (3) is positioned at the lowest point position of the right bottom plate (2-1) and the left bottom plate (2-2) in the left-right direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222123768.0U CN217945492U (en) | 2022-08-12 | 2022-08-12 | Aircraft floor stiffening beam |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222123768.0U CN217945492U (en) | 2022-08-12 | 2022-08-12 | Aircraft floor stiffening beam |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217945492U true CN217945492U (en) | 2022-12-02 |
Family
ID=84231224
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222123768.0U Expired - Fee Related CN217945492U (en) | 2022-08-12 | 2022-08-12 | Aircraft floor stiffening beam |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217945492U (en) |
-
2022
- 2022-08-12 CN CN202222123768.0U patent/CN217945492U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20221202 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |