CN210942304U - Processing tool for lower half frame of rear fuselage of airplane - Google Patents
Processing tool for lower half frame of rear fuselage of airplane Download PDFInfo
- Publication number
- CN210942304U CN210942304U CN201921908799.9U CN201921908799U CN210942304U CN 210942304 U CN210942304 U CN 210942304U CN 201921908799 U CN201921908799 U CN 201921908799U CN 210942304 U CN210942304 U CN 210942304U
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- CN
- China
- Prior art keywords
- support body
- fixed mounting
- half frame
- airplane
- lower half
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- 230000003139 buffering effect Effects 0.000 claims abstract description 19
- 238000013016 damping Methods 0.000 claims description 33
- 238000003754 machining Methods 0.000 claims description 8
- 238000007789 sealing Methods 0.000 claims description 6
- 239000010720 hydraulic oil Substances 0.000 claims description 5
- 230000035939 shock Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000008901 benefit Effects 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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- Vibration Prevention Devices (AREA)
Abstract
The utility model discloses a half frame processing frock under fuselage behind aircraft, including first support body and second support body, the bottom fixed mounting of first support body has the connection base, the bottom movable mounting who connects the base has the truckle, the upper portion fixed mounting of first support body has the spliced pole, the spliced pole is connected with the support column through buffering shock-absorbing structure, the top fixed mounting of support column has the protection cushion, the quantity of support column is two, two be equipped with revolution mechanic between the support column, revolution mechanic is including arc seat, pivot and pulley, you are the opposite side of fixed mounting at two support columns respectively at the both ends of arc seat. A fuselage second frame processing frock behind aircraft, can play excellent buffering shock attenuation efficiency, secondly also can directly rotate fuselage second frame behind the aircraft on first support body and second support body, it is more convenient to use, the practicality is higher.
Description
Technical Field
The utility model relates to a processing frock field, in particular to half frame processing frock under fuselage behind aircraft.
Background
The processing tool for the lower half frame of the rear fuselage of the airplane is used for processing the lower half frame of the rear fuselage of the airplane, and comprises a cutter, a clamp, a die, a measuring tool, a checking tool, an auxiliary tool, a bench tool, a station tool and the like, wherein the station tool is used for storing various devices of production objects or tools in a working place or a warehouse, and the station tool of the lower half frame of the rear fuselage of the airplane is mainly used for storing the lower half frame of the rear fuselage of the airplane; however, the existing station apparatus for the lower half frame of the rear fuselage of the airplane does not have a buffering and damping function, is easy to generate large vibration force during moving or machining, is not beneficial to use, does not have a rotating function, cannot directly rotate the lower half frame of the rear fuselage of the airplane on the station apparatus, and is not convenient enough to use because the station apparatus needs to be removed when the lower half frame of the rear fuselage of the airplane needs to be rotated.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a main aim at provides an aircraft fuselage second frame processing frock, the frock that can effectively solve among the background art does not possess buffering shock-absorbing function and does not possess the problem of rotation function.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides an aircraft rear fuselage half frame processing frock down, includes first support body and second support body, the bottom fixed mounting of first support body has the connection base, the bottom movable mounting who connects the base has the truckle, the upper portion fixed mounting of first support body has the spliced pole, the spliced pole is connected with the support column through buffering shock-absorbing structure, the top fixed mounting of support column has the protection cushion, the quantity of support column is two, two be equipped with revolution mechanic between the support column.
Preferably, revolution mechanic is including arc seat, pivot and pulley, you are fixed mounting respectively at the opposite side of two support columns at the both ends of arc seat, pivot movable mounting is in the inside of arc seat, pulley movable mounting is in the outside of pivot.
Preferably, the number of the pulleys is seven, and the seven pulleys are circularly and equidistantly arranged.
Preferably, buffering shock-absorbing structure is including buffering post, first buffer spring, damping fin, sealing washer and second buffer spring, the one end fixed mounting of buffering post is in the bottom of support column, the other end setting of buffering post is in the inside of spliced pole, damping fin fixed connection is located the inside of spliced pole at the other end of buffering post, sealing washer fixed mounting is in the inside top position of spliced pole, second buffer spring places the below position that is located the damping fin in the inside of spliced pole.
Preferably, the upper surface of the damping fin is provided with a damping hole, and the connecting column is filled with hydraulic oil.
Preferably, the shapes of the first frame body and the second frame body are both V-shaped, and a connecting rod is connected between the first frame body and the second frame body.
Compared with the prior art, the utility model discloses following beneficial effect has: the utility model discloses in, through the buffering damping device who sets up, can play excellent shock attenuation effect through first buffer spring and second buffer spring, also can form damping effect through damping hole and hydraulic oil simultaneously, can further improve buffering shock attenuation efficiency, more do benefit to the use, revolution mechanic through the setting, can make things convenient for the direct fuselage second frame after rotatory aircraft on first support body and second support body, it changes the position to need not to remove it, it is more convenient to use, be favorable to processing, the result of use of the fuselage second frame processing frock behind whole aircraft has been improved.
Drawings
Fig. 1 is a schematic view of the overall structure of the processing tool for the lower half frame of the rear fuselage of the airplane;
FIG. 2 is a cross-sectional view of an arc seat of the machining tool for the lower half frame of the rear fuselage of the aircraft according to the present invention;
fig. 3 is a schematic view of the internal structure of the connecting column of the processing tool for the lower half frame of the rear fuselage of the airplane of the present invention;
fig. 4 is the utility model relates to a first support body and second support body side view of fuselage second frame processing frock behind aircraft.
In the figure: 1. a first frame body; 2. connecting a base; 3. a caster wheel; 4. connecting columns; 5. a buffer shock-absorbing structure; 6. a support pillar; 7. a protective cushion; 8. a rotating structure; 9. an arc-shaped seat; 10. a rotating shaft; 11. a pulley; 12. a buffer column; 13. a first buffer spring; 14. a damping fin; 15. a damping hole; 16. a seal ring; 17. a second buffer spring; 18. a second frame body; 19. a connecting rod.
Detailed Description
In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.
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.
As shown in fig. 1-4, the processing tool for the lower half frame of the rear fuselage of the airplane comprises a first frame body 1 and a second frame body 18, wherein a connecting base 2 is fixedly installed at the bottom of the first frame body 1, casters 3 are movably installed at the bottom of the connecting base 2, a connecting column 4 is fixedly installed at the upper part of the first frame body 1, the connecting column 4 is connected with a supporting column 6 through a buffering and damping structure 5, a protective cushion 7 is fixedly installed at the top of the supporting column 6, the number of the supporting columns 6 is two, and a rotating structure 8 is arranged between the two supporting columns 6;
the rotating structure 8 comprises an arc-shaped seat 9, a rotating shaft 10 and a pulley 11, two ends of the arc-shaped seat 9 are respectively and fixedly arranged on opposite sides of the two supporting columns 6, the rotating shaft 10 is movably arranged inside the arc-shaped seat 9, and the pulley 11 is movably arranged outside the rotating shaft 10; the number of the pulleys 11 is seven, and the seven pulleys 11 are circularly arranged at equal intervals; the damping structure 5 comprises a damping column 12, a first damping spring 13, a damping fin 14, a sealing ring 16 and a second damping spring 17, one end of the damping column 12 is fixedly installed at the bottom of the supporting column 6, the other end of the damping column 12 is arranged inside the connecting column 4, the damping fin 14 is fixedly connected to the other end of the damping column 12 and located inside the connecting column 4, the sealing ring 16 is fixedly installed at the top end position inside the connecting column 4, and the second damping spring 17 is placed inside the connecting column 4 and located below the damping fin 14; the upper surface of the damping fin 14 is provided with a damping hole 15, and the connecting column 4 is filled with hydraulic oil; the shape of first support body 1 and second support body 18 is V style of calligraphy, be connected with connecting rod 19 between first support body 1 and the second support body 18.
It should be noted that, the utility model relates to a processing tool for the lower half frame of the rear fuselage of an airplane, when in use, the lower half frame of the rear fuselage of the airplane is directly placed on the upper parts of a first frame body 1 and a second frame body 18 and is positioned on the upper part of an arc seat 9, at the moment, the lower half frame of the rear fuselage of the airplane is contacted with a pulley 11, when in use, people can directly rotate the lower half frame of the rear fuselage of the airplane through the sliding force of the pulley 11, the use is more convenient and the practicability is higher, then a protective cushion 7 and the pulley 11 both belong to soft rubber materials, the surface of the lower half frame of the rear fuselage of the airplane can be protected, the scratch phenomenon is avoided, after the lower half frame of the rear fuselage of the airplane is placed, people can use a caster 3 to move the first frame body 1 and the second frame body 18, when in moving or processing, a vibration force can be generated, the buffer column 12 can be driven to move up and down when the vibration force is generated, at the moment, secondly, when the buffer column 12 moves, the damping sheet 14 moves along with the buffer column, and at the moment, the damping holes 15 and the hydraulic oil inside the connecting column 4 form a damping effect, so that the buffer and shock absorption effects can be further improved.
The basic principles and the main features of the invention and the advantages of the invention have been shown and described above. It will be understood by those skilled in the art that the present invention is not limited to the above embodiments, and that the foregoing embodiments and descriptions are provided only to illustrate the principles of the present invention without departing from the spirit and scope of the present invention. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (6)
1. The utility model provides a fuselage processing frock of half frame under behind aircraft which characterized in that: including first support body (1) and second support body (18), the bottom fixed mounting of first support body (1) has connection base (2), the bottom movable mounting who connects base (2) has truckle (3), the upper portion fixed mounting of first support body (1) has spliced pole (4), spliced pole (4) are connected with support column (6) through buffering shock-absorbing structure (5), the top fixed mounting of support column (6) has protection cushion (7), the quantity of support column (6) is two, two be equipped with revolution mechanic (8) between support column (6).
2. The machining tool for the lower half frame of the rear fuselage of the airplane as claimed in claim 1, wherein: revolution mechanic (8) are including arc seat (9), pivot (10) and pulley (11), you are fixed mounting respectively at the opposite side of two support columns (6) at the both ends of arc seat (9), pivot (10) movable mounting is in the inside of arc seat (9), pulley (11) movable mounting is in the outside of pivot (10).
3. The machining tool for the lower half frame of the rear fuselage of the airplane as claimed in claim 2, wherein: the number of the pulleys (11) is seven, and the seven pulleys (11) are circularly arranged at equal intervals.
4. The machining tool for the lower half frame of the rear fuselage of the airplane as claimed in claim 1, wherein: buffering shock-absorbing structure (5) is including buffering post (12), first buffer spring (13), damping fin (14), sealing washer (16) and second buffer spring (17), the one end fixed mounting of buffering post (12) is in the bottom of support column (6), the other end setting of buffering post (12) is in the inside of spliced pole (4), damping fin (14) fixed connection is in the inside that the other end of buffering post (12) is located spliced pole (4), sealing washer (16) fixed mounting is in the inside top position of spliced pole (4), second buffer spring (17) are placed in the below position that the inside of spliced pole (4) is located damping fin (14).
5. The machining tool for the lower half frame of the rear fuselage of the airplane as claimed in claim 4, wherein the machining tool comprises: damping holes (15) are formed in the upper surface of the damping fin (14), and hydraulic oil is filled in the connecting column (4).
6. The machining tool for the lower half frame of the rear fuselage of the airplane as claimed in claim 1, wherein: the shape of first support body (1) and second support body (18) is V style of calligraphy, be connected with connecting rod (19) between first support body (1) and second support body (18).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921908799.9U CN210942304U (en) | 2019-11-07 | 2019-11-07 | Processing tool for lower half frame of rear fuselage of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921908799.9U CN210942304U (en) | 2019-11-07 | 2019-11-07 | Processing tool for lower half frame of rear fuselage of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210942304U true CN210942304U (en) | 2020-07-07 |
Family
ID=71372506
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921908799.9U Expired - Fee Related CN210942304U (en) | 2019-11-07 | 2019-11-07 | Processing tool for lower half frame of rear fuselage of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210942304U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111941313A (en) * | 2020-08-03 | 2020-11-17 | 河北天启通宇航空器材科技发展有限公司 | Organism assembly fixture |
-
2019
- 2019-11-07 CN CN201921908799.9U patent/CN210942304U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111941313A (en) * | 2020-08-03 | 2020-11-17 | 河北天启通宇航空器材科技发展有限公司 | Organism assembly fixture |
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| 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: 20200707 |
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| CF01 | Termination of patent right due to non-payment of annual fee |