CN217945494U - Aircraft fuselage stay tube - Google Patents
Aircraft fuselage stay tube Download PDFInfo
- Publication number
- CN217945494U CN217945494U CN202222089341.3U CN202222089341U CN217945494U CN 217945494 U CN217945494 U CN 217945494U CN 202222089341 U CN202222089341 U CN 202222089341U CN 217945494 U CN217945494 U CN 217945494U
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- Prior art keywords
- groove
- aircraft fuselage
- positioning groove
- wing
- pipe body
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- 238000009434 installation Methods 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims abstract description 5
- 239000000446 fuel Substances 0.000 abstract description 5
- 230000000694 effects Effects 0.000 description 4
- 230000007547 defect Effects 0.000 description 3
- 238000004891 communication Methods 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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Abstract
The utility model provides an aircraft fuselage supporting tube, the fuselage shell comprises a tube body (1), a first wing piece (2) and a second wing piece (3) are fixedly stretched out of the top of the tube body (1), and a supporting piece (4) is fixedly stretched out of the bottom of the tube body (1); the method is characterized in that: the side wall of the pipe body (1) is respectively provided with a first positioning groove (1-5) and a second positioning groove (1-7), and the first positioning groove (1-5) and the second positioning groove (1-7) are centrosymmetric relative to the axial lead of the pipe body (1); the positioning and the fixed installation of the shell in the axial direction and the circumferential direction are realized simultaneously through one-time rotation, the assembly and the disassembly are convenient, and the support is stable; and meanwhile, the outer wall of the pipe body is only provided with the first wing piece, the second wing piece and the supporting piece, so that the wind resistance of the airplane is further reduced, and the fuel is saved.
Description
Technical Field
The utility model relates to a technical field of aircraft fuselage, concretely relates to aircraft fuselage stay tube.
Background
The aircraft fuselage plays important support and guard action to the aircraft inner space, both satisfy and connect and support stable requirement, need again go the in-process on the aircraft with the less windward area of lower quality reduce the windage fuel of saving, still guarantee great inner space as far as possible simultaneously and in order to increase bearing space, consequently along with the continuous development of science and technology, also more and more high to each item requirement of aircraft fuselage stay tube, current aircraft fuselage spare part can not satisfy the requirement far away.
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 fuselage supporting tube.
For solving the above-mentioned prior art defect and not enough, the utility model provides a scheme as follows:
the supporting tube for the aircraft body comprises a tube body, wherein a first wing and a second wing fixedly extend out of the top of the tube body, and a supporting sheet fixedly extends out of the bottom of the tube body; the method is characterized in that: the side wall of the pipe body is respectively provided with a first positioning groove and a second positioning groove, and the first positioning groove and the second positioning groove are in central symmetry relative to the axial lead of the pipe body.
As a further preferred embodiment of the present invention, the outer wall of the pipe body extends out of the positions corresponding to the first wing and the second wing respectively and is provided with a first extending section and a second extending section, the first extending section of the first wing fixed connection, and the second extending section of the second wing fixed connection.
As a further preferred embodiment of the present invention, the outer wall of the pipe body is formed with a mounting groove corresponding to a connection position of the first extension section and the second extension section.
As a further preferred embodiment of the present invention, the radial extension line of the supporting plate is located between the first wing and the second wing, and the installation positions of the first wing and the second wing are in a non-axisymmetric relationship with respect to the supporting plate.
As a further preferred embodiment of the present invention, the first positioning groove is an L-shaped groove, including an edge of a first sliding groove extending in the axial direction of the pipe body and an edge of a first locking groove extending in the circumferential direction of the pipe body, the first sliding groove and the first locking groove communicate with each other.
As a further preferred embodiment of the present invention, the second positioning groove is an L-shaped groove, including an edge the second sliding groove extending in the axial direction of the pipe body and an edge the second locking groove extending in the circumferential direction of the pipe body, the second sliding groove is in communication with the second locking groove, and the extending direction of the second locking groove is opposite to the extending direction of the first locking groove.
As a further preferred embodiment of the present invention, the side wall of the pipe body is located at one axial side of the first positioning groove and the second positioning groove and is correspondingly provided with a first mounting hole and a second mounting hole.
As a further preferred embodiment of the present invention, the supporting sheet has a supporting sheet mounting hole formed therein.
As a further preferred embodiment of the present invention, the radially outer ends of the first fin, the second fin, and the supporting plate are set to be rounded.
Compared with the prior art, the utility model discloses the technological effect that can realize includes:
1) The utility model provides an aircraft fuselage stay tube, first constant head tank and second constant head tank have been seted up respectively at the lateral wall of body, only need during fixed mounting to slide the body axial earlier so that the body internal positioning epaxial radially stretched out setting element slide to the tip that corresponds the groove along the axial of first constant head tank and second constant head tank earlier, then rotate the body in the tip position of first constant head tank and second constant head tank and make the setting element be located the first locking groove of first constant head tank and the second locking inslot of second constant head tank, rethread first and second mounting hole realize the fixed of body position, thereby realize simultaneously location and fixed mounting of this stay tube in axial and circumferencial direction through once rotating, and the loading and unloading is convenient, and the support is stable;
2) The utility model provides an aircraft fuselage stay tube for the inside front side below of aircraft fuselage supports, only is provided with first, second fin and support piece at the outer wall of body simultaneously, effectively reduces rather than matching installation and expose the windward area and the size of aircraft fuselage part outside, thereby further reduces the aircraft windage, practices thrift fuel.
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 left side view of the structure of the present invention.
Fig. 4 is a right side view of the structure 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 efforts all 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," "second," and the like 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 should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "provided," "connected," and the like are to be construed broadly, such as "connected," which may be fixedly connected, 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 ]
As shown in fig. 1 to 4, a first embodiment of the present invention provides an aircraft fuselage support tube, in which the aircraft fuselage support tube includes a tube body 1, an inner hole 1-1 for accommodating a positioning shaft (not shown) is formed inside the tube body 1, a first wing piece 2 and a second wing piece 3 are fixed to the top of the tube body 1, and a supporting piece 4 is fixed to the bottom of the tube body 1; the outer wall of the pipe body 1 is only provided with the first fin, the second fin and the supporting sheet, so that the wind resistance of the airplane can be further reduced in the operation process of the airplane, and the fuel is saved.
As shown in fig. 2, in this embodiment, a first extending section 1-2 and a second extending section 1-3 are respectively disposed on the outer wall of the tube body 1 at positions corresponding to the first wing 2 and the second wing 3, the first wing 2 is fixedly connected to the first extending section 1-2, and the second wing 3 is fixedly connected to the second extending section 1-3. The first extending section 1-2 and the second extending section 1-3 are used for enhancing the connection strength and stability of the first wing piece 2 and the second wing piece 3 with the pipe body 1, preferably, in the embodiment, the first wing piece 2, the first extending section 1-2 and the pipe body 1 are formed into an integral structure, and the second wing piece 3, the second extending section 1-3 and the pipe body 1 are also formed into an integral structure, so that the manufacturing and forming are facilitated, the assembly applicability is further increased while the appearance is attractive, and meanwhile, the influence of overlarge wind resistance and the like possibly caused by the unsmooth shape of the non-integral structure in the operation of the airplane is reduced.
As shown in fig. 2, preferably, the outer wall of the pipe body 1 is formed with a mounting groove 1-4 corresponding to the connection position of the first extending section 1-2 and the second extending section 1-3, the mounting groove 1-4 can be positioned and mounted with an external fixing member while achieving the overall positioning effect of the support pipe of the aircraft body, the external fixing member (not shown) is located in the mounting groove 1-4 and achieves the overall primary positioning effect of the support pipe of the aircraft body due to the blocking of the first and second fins on both sides, and the external fixing member (not shown) located in the mounting groove 1-4 cannot achieve 360-degree rotation of the support pipe but can allow the support pipe to rotate with a small-amplitude rotation angle, thereby providing a rotation space for the subsequent installation locking of the first positioning groove 1-5 and the second positioning groove 1-7.
As shown in fig. 2, in the present embodiment, the radial extension line of the blade 4 is located between the first wing 2 and the second wing 3, and in the present embodiment, to meet the requirements of the product installation structure, the installation positions of the first wing 2 and the second wing 3 are in a non-axisymmetrical relationship with respect to the blade 4; according to the installation needs of the actual service environment, the installation positions of the first fin 2 and the second fin 3 can also be set to be in an axisymmetric relationship relative to the supporting sheet 4, and whether the installation positions of the first fin 2 and the second fin 3 are in the axisymmetric relationship relative to the supporting sheet 4 needs to be determined according to the corresponding fixed installation needs.
As shown in fig. 3 to 4, in this embodiment, the sidewall of the tube body 1 is respectively provided with a first positioning groove 1-5 and a second positioning groove 1-7, and the first positioning groove 1-5 and the second positioning groove 1-7 are centrosymmetric with respect to the axial line of the tube body 1, so that the purpose of the arrangement is to achieve the position locking effect between the two sides of the support tube and the internal positioning element by only one rotation.
As shown in fig. 3, the first positioning groove 1-5 is an L-shaped groove, and includes a first sliding groove 1-51 extending in an axial direction of the pipe body 1 and a first locking groove 1-52 extending in a circumferential direction of the pipe body 1, and the first sliding groove 1-51 and the first locking groove 1-52 are in communication with each other.
As shown in fig. 4, the second positioning groove 1-7 is an L-shaped groove, and includes a second sliding groove 1-71 extending along the axial direction of the pipe body 1 and a second locking groove 1-72 extending along the circumferential direction of the pipe body 1, the second sliding groove 1-71 and the second locking groove 1-72 are communicated with each other, and the extending direction of the second locking groove 1-72 is opposite to the extending direction of the first locking groove 1-52.
Only need slide the body axial earlier so that the body internal positioning axle (not shown) goes up the setting element that radially stretches out and slide groove axial sliding to the tip that corresponds the groove along the first groove that slides of first constant head tank and the second of second constant head tank earlier when fixed mounting, again make the setting element get into and lock in the second locking inslot of the first locking groove of first constant head tank and second constant head tank in the tip position rotation body of first constant head tank and second constant head tank, thereby realize this stay tube simultaneously through a rotation and fixed mounting in axial and ascending location of circumferencial direction, the loading and unloading are convenient, support stably.
As shown in fig. 3-4, a first mounting hole 1-6 and a second mounting hole 1-8 are correspondingly formed on one axial side of the sidewall of the pipe body 1, which is located at the first positioning groove 1-5 and the second positioning groove 1-7, and after the pipe body 1 is rotated to achieve locking, the further fixed mounting of the support pipe is achieved through the first mounting hole 1-6 and the second mounting hole 1-8, so that the fixed mounting stability is further improved.
As shown in fig. 1 and 3-4, as a preferred embodiment of the present invention, a supporting sheet installation hole 4-1 is formed in the supporting sheet 4, and the supporting sheet at the bottom of the supporting tube is installed at a preset position through the supporting sheet installation hole 4-1.
As a further preference of this embodiment, as shown in fig. 1, the radially outer ends of the first fin 2, the second fin 3, and the supporting fin 4 are set to be rounded corners, so as to further reduce wind resistance during the operation of the aircraft and reduce fuel consumption while ensuring an attractive appearance.
The specific installation process of the support tube provided by the embodiment is as follows:
1) The supporting tube of the airplane body is integrally positioned while being installed with an external fixing piece through the installation grooves 1-4;
2) When in fixed installation, the pipe body 1 is axially slid to enable the positioning piece in the pipe body to axially slide to the end part of the corresponding groove along the first sliding groove of the first positioning groove and the second sliding groove of the second positioning groove, and then the pipe body is rotated at the end parts of the first positioning groove and the second positioning groove to enable the positioning piece to enter and be locked in the first locking groove of the first positioning groove and the second locking groove of the second positioning groove;
3) After the pipe body 1 is rotated to realize locking, the supporting pipe is further fixedly installed through the first installation holes 1-6 and the second installation holes 1-8, and therefore the stability of fixed installation is further improved.
4) And finally, mounting the supporting sheet at the bottom of the supporting tube at a preset position through the supporting sheet mounting hole 4-1.
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 supporting tube for the airframe of the airplane comprises a tube body (1), wherein a first wing piece (2) and a second wing piece (3) fixedly extend out of the top of the tube body (1), and a supporting piece (4) fixedly extends out of the bottom of the tube body (1); the method is characterized in that: the side wall of the pipe body (1) is provided with a first positioning groove (1-5) and a second positioning groove (1-7), and the first positioning groove (1-5) and the second positioning groove (1-7) are centrosymmetric relative to the axial lead of the pipe body (1).
2. An aircraft fuselage support tube according to claim 1, wherein: the position that the outer wall of body (1) corresponds first fin (2) and second fin (3) stretches out respectively and is provided with first extension section (1-2) and second extension section (1-3), first fin (2) first extension section of fixed connection (1-2), second fin (3) second extension section of fixed connection (1-3).
3. An aircraft fuselage support tube according to claim 2, wherein: and an installation groove (1-4) is formed in the outer wall of the pipe body (1) corresponding to the connection position of the first extension section (1-2) and the second extension section (1-3).
4. An aircraft fuselage support tube as claimed in claim 1, wherein: the radial extension line of the supporting sheet (4) is positioned between the first wing sheet (2) and the second wing sheet (3), and the installation positions of the first wing sheet (2) and the second wing sheet (3) are in non-axisymmetric relation relative to the supporting sheet (4).
5. An aircraft fuselage support tube as claimed in claim 1, wherein: the first positioning groove (1-5) is an L-shaped groove and comprises a first sliding groove (1-51) extending along the axial direction of the pipe body (1) and a first locking groove (1-52) extending along the circumferential direction of the pipe body (1), and the first sliding groove (1-51) is communicated with the first locking groove (1-52).
6. An aircraft fuselage support tube according to claim 5, wherein: the second constant head tank (1-7) is the L shape groove, includes along the second that the axial direction of body (1) extends slides groove (1-71) and follows the second locking groove (1-72) that the circumferencial direction of body (1) extends, second slide groove (1-71) with second locking groove (1-72) intercommunication each other, just the extending direction of second locking groove (1-72) with the extending direction in first locking groove (1-52) is opposite.
7. An aircraft fuselage support tube as claimed in claim 1, wherein: the side wall of the pipe body (1) is positioned at one axial side of the first positioning groove (1-5) and the second positioning groove (1-7) and is also correspondingly provided with a first mounting hole (1-6) and a second mounting hole (1-8).
8. An aircraft fuselage support tube as claimed in claim 1, wherein: the supporting sheet (4) is internally provided with a supporting sheet mounting hole (4-1).
9. An aircraft fuselage support tube as claimed in claim 1, wherein: the radial outer ends of the first wing piece (2), the second wing piece (3) and the supporting piece (4) are set to be round angles.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222089341.3U CN217945494U (en) | 2022-08-10 | 2022-08-10 | Aircraft fuselage stay tube |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222089341.3U CN217945494U (en) | 2022-08-10 | 2022-08-10 | Aircraft fuselage stay tube |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217945494U true CN217945494U (en) | 2022-12-02 |
Family
ID=84226353
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222089341.3U Expired - Fee Related CN217945494U (en) | 2022-08-10 | 2022-08-10 | Aircraft fuselage stay tube |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217945494U (en) |
-
2022
- 2022-08-10 CN CN202222089341.3U patent/CN217945494U/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 |