CN211223930U - Aircraft maintenance anticollision board - Google Patents
Aircraft maintenance anticollision board Download PDFInfo
- Publication number
- CN211223930U CN211223930U CN201922366890.9U CN201922366890U CN211223930U CN 211223930 U CN211223930 U CN 211223930U CN 201922366890 U CN201922366890 U CN 201922366890U CN 211223930 U CN211223930 U CN 211223930U
- Authority
- CN
- China
- Prior art keywords
- plate
- connecting plate
- side wall
- sliding
- shock absorption
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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
Links
- 238000012423 maintenance Methods 0.000 title claims abstract description 13
- 238000013016 damping Methods 0.000 claims abstract description 17
- 230000035939 shock Effects 0.000 claims description 23
- 238000010521 absorption reaction Methods 0.000 claims description 22
- 230000000694 effects Effects 0.000 description 5
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 238000006243 chemical reaction Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
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Abstract
The utility model discloses an aircraft maintenance anticollision plate, which comprises a connecting plate, an anticollision plate, an assembly plate and a limiting rod, wherein the anticollision plate is fixedly connected with the limiting rod, the assembly plate is positioned on the right side of the connecting plate, one end of the limiting rod, which is far away from the anticollision plate, is slidably extended out of the right side wall of the connecting plate, the top and the bottom of the right side wall of the anticollision plate are fixedly connected with a main damping column, two groups of main damping columns are sleeved with a second damping spring, the two ends of the second damping spring are respectively fixedly connected with the side walls, which are close to the anticollision plate and the connecting plate, the top and the bottom of the inner cavity of the connecting plate are symmetrically provided with a sliding groove, the top and the bottom of one end, into which the two groups of main damping columns extend, of the left side wall of the assembly plate are fixedly connected with an auxiliary damping column, the center of the inner cavity of the two groups of auxiliary damping columns is provided with a sliding cavity, the utility model has reasonable design structure, and can, can bear large force impact.
Description
Technical Field
The utility model relates to an anticollision board technical field specifically is an aircraft maintenance anticollision board.
Background
In the prior art, an aircraft (aeroplane) refers to an aircraft that is heavier than air and flies in the atmosphere, and has a power plant with one or more engines to generate forward thrust or pull force, and a fixed wing of a fuselage generates lift force. Aircraft is one of the most common fixed wing aircraft. The conventional aircraft, which may be classified into a jet aircraft and a propeller aircraft according to the type of engine used therein, needs a new structure to solve the above problems because the conventional aircraft has a complicated structure and needs special care during maintenance to prevent a collision, and the prior patent discloses a problem of avoiding the maintenance collision.
However, the applicant believes that the conventional aircraft maintenance anti-collision plate can only use the spring to perform a shock absorption effect once, the anti-collision plate cannot perform multiple or multiple shock absorption, the shock absorption effect is not obvious, aircraft parts are still damaged when the anti-collision plate is impacted by a large force, and the protection performance of the aircraft parts is insufficient.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aircraft maintenance anticollision board to solve the problem that proposes among the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme: an aircraft maintenance anti-collision plate comprises a connecting plate, an anti-collision plate, an assembly plate and a limiting rod, wherein the anti-collision plate is fixedly connected with the limiting rod, the left end of the limiting rod extends out of the left side wall of the anti-collision plate, the assembly plate is positioned on the right side of the connecting plate, one end, far away from the anti-collision plate, of the limiting rod slidably extends out of the right side wall of the connecting plate, the top and the bottom of the right side wall of the anti-collision plate are fixedly connected with main damping columns, two groups of main damping columns are sleeved with second damping springs, two ends of each second damping spring are fixedly connected with the side wall, close to the anti-collision plate and the connecting plate, of the inner cavity of the connecting plate, the top and the bottom of the inner cavity of the connecting plate are symmetrically provided with sliding grooves, the top and the bottom of one end, extending into the left side wall of the connecting plate, of the two groups of main damping columns are fixedly connected with sliding blocks, the top and the, and two sets of vice bradyseism post all with sliding tray looks sliding connection, two sets of the slip chamber has all been seted up to the inner chamber center department of vice bradyseism post, and the inner chamber in slip chamber and the main bradyseism post looks sliding connection who stretches into connecting plate left side wall one end, the rigid coupling has the spring between the main bradyseism post that the chamber end in slip chamber and main bradyseism post stretch into connecting plate left side wall one end, and is two sets of all cup jointed first bradyseism spring on the vice bradyseism post, and the lateral wall looks rigid coupling that the both ends of first bradyseism spring are pressed close to respectively with mounting plate and connecting plate, the spacing hole with gag lever post matched with is all seted up to the left and right sides wall top and the bottom of mounting plate.
Preferably, the left side wall of the anti-collision plate is provided with a flexible convex pad, and the flexible convex pad is composed of a plurality of elastic convex balls, so that the impact force applied to the anti-collision plate can be buffered.
Preferably, the central line of the limiting rod and the central line of the limiting hole are on the same horizontal line, so that the limiting rod can move along a straight line, and the impact force on the whole device is in the same straight line direction.
Preferably, the maximum sliding distance of the connecting plate on the limiting rod is the same as the distance between the sliding block and one end, extending into the right side wall of the connecting plate, of the auxiliary shock absorption column, so that the possibility that the connecting plate slides out of the limiting rod can be reduced.
Preferably, the rod point part of the limiting rod is circular, so that the circular part of the rod point can play a role in guiding, and the limiting rod can conveniently penetrate through the limiting hole in the assembly plate.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model discloses a gag lever post that sets up on aircraft maintenance anticollision board is convenient for fix the position of anticollision board, and anticollision board is fixed mutually with the gag lever post, thereby great improvement the utility model discloses fixed stability when receiving the impact force on the assembly plate, cup joint first spring on main bradyseism post and cup joint the impact force that the outside received and carry out bradyseism many times on second spring and the vice bradyseism post, main bradyseism post also can slide along the slip chamber of vice bradyseism post inner chamber simultaneously, and the spring of being connected between main bradyseism post and the vice bradyseism post plays the effect of bradyseism once more, thereby makes whole device bear great impact force, and is stronger to aircraft part's protectiveness, and the bradyseism effect is obvious.
Drawings
FIG. 1 is a front view of the overall structure of the present invention;
FIG. 2 is an enlarged schematic view of part A of the present invention;
FIG. 3 is an enlarged schematic view of part B of the present invention;
in the figure, 1-connecting plate; 2-a crash-proof plate; 3-assembling a plate; 4-a limiting rod; 5-limiting holes; 6-main shock absorption column; 7-auxiliary shock absorption columns; 8-a sliding cavity; 9-a spring; 10-a sliding groove; 11-a slide block; 12-a second cushioning spring; 13-a flexible convex pad; 14-first cushioning spring.
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.
Referring to fig. 1-3, an embodiment of an aircraft maintenance anti-collision plate provided by the present invention comprises a connecting plate 1, an anti-collision plate 2, an assembling plate 3 and a limiting rod 4, wherein the anti-collision plate 2 is fixedly connected to the limiting rod 4, the central line of the limiting rod 4 and the central line of the limiting hole 5 are on the same horizontal line, so as to ensure that the limiting rod 4 moves along a straight line, the impact force applied to the entire apparatus is in the same straight line direction, the left end of the limiting rod 4 extends out of the left side wall of the anti-collision plate 2, the left side wall of the anti-collision plate 2 is provided with a flexible convex pad 13, and the flexible convex pad 13 is composed of a plurality of elastic convex balls, so as to buffer the impact force applied to the anti-collision plate 2, the assembling plate 3 is located on the right side of the connecting plate 1, one end of the limiting rod 4 far away from the anti-collision plate 2 slidably extends out of the right side wall of the connecting plate 1, the top and the bottom of the, the two groups of main shock absorption columns 6 are respectively sleeved with a second shock absorption spring 12, two ends of each second shock absorption spring 12 are respectively and fixedly connected with the side wall, close to the anti-collision plate 2 and the connecting plate 1, of each second shock absorption spring 12, the maximum sliding distance of the connecting plate 1 on the limiting rod 4 is the same as the distance between the sliding block 11 and one end, extending into the right side wall of the connecting plate 1, of the auxiliary shock absorption column 7, so that the possibility that the connecting plate 1 slides out of the limiting rod 4 can be reduced, the rod tip part of the limiting rod 4 is circular, the circular part of the rod tip can play a guiding role, the limiting rod 4 can conveniently penetrate through the limiting hole 5 in the assembling plate 3, the sliding grooves 10 are symmetrically formed in the top and the bottom of the inner cavity of the connecting plate 1, the sliding blocks 11 are fixedly connected to the top and the bottom of one end, extending into the left side wall of the connecting plate 1, of the sliding blocks 11 are slidably connected with the sliding grooves 10, the auxiliary shock, and two sets of vice bradyseism post 7 all with sliding tray 10 looks sliding connection, sliding cavity 8 has all been seted up to the inner chamber center department of two sets of vice bradyseism post 7, and sliding cavity 8's inner chamber and the main bradyseism post 6 looks sliding connection who stretches into 1 left side wall one end of connecting plate, the rigid coupling has spring 9 between the main bradyseism post 6 that stretches into 1 left side wall one end of connecting plate at the bottom of sliding cavity 8's the chamber and main bradyseism post 6, first bradyseism spring 14 has all been cup jointed on two sets of vice bradyseism posts 7, and the lateral wall looks rigid coupling that the both ends of first bradyseism spring 14 pressed close to respectively with mounting plate 3 and connecting plate 1, spacing hole 5 with gag lever post 4 matched with is all seted up with the left and right sides wall top and the bottom of.
The working principle is as follows: firstly, the utility model is checked by the staff to check whether the utility model has defects, if the utility model has defects, the utility model can not be used, at the moment, the maintenance staff is required to be informed to maintain, if no problem exists, the utility model can be used, when in use, the utility model is fixed at the position where the installation is required through the fixing hole on the limiting rod 4, the anti-collision plate 2 is fixed with the limiting rod 4, the connecting plate 1 and the assembling plate 3 can slide on the limiting rod 4, the fixed anti-collision plate 2 can also play the role of supporting and bearing the connecting plate 1 and the assembling plate 3 at the same time, thereby greatly improving the fixing stability of the utility model, when one side of the assembling plate 3 receives impact force, the auxiliary shock-absorbing column 7 slides along the sliding groove 10, the first shock-absorbing spring 14 sleeved on the auxiliary shock-absorbing column 7 is extruded, thereby generating a reaction force to the assembling plate 3, the auxiliary cushioning column 7 slides leftwards at the moment, the first cushioning spring 14 extrudes the connecting plate 1 to slide leftwards along the limiting rod 4, when one end of the auxiliary cushioning column 7 is contacted with the sliding block 11, the auxiliary cushioning column 7 stops the trend of sliding leftwards, the sliding block 11 plays a certain limiting role, the connecting plate 1 sliding leftwards extrudes the second cushioning spring 12, the second cushioning spring 12 generates a reaction force on the connecting plate 1, the connecting plate 1 is bounced off according to the force conductivity, the first cushioning spring 14 is stressed by a force in the same direction to play a role of secondary cushioning, the distance between the auxiliary cushioning column 7 sliding leftwards and the main cushioning column 6 is reduced, the spring 9 in the sliding cavity 8 is continuously extruded, the spring 9 generates a reaction force on the auxiliary cushioning column 7 to play a role of tertiary cushioning, and the role of multiple times or multiple cushioning of the whole device is realized, the bradyseism effect is obvious, and the central line of gag lever post 4 and the central line of spacing hole 5 are on same water flat line, can guarantee like this that gag lever post 4 is along linear motion, and the impact force that makes whole device receive is on same straight line direction, and flexible protruding pad 13 has then played the purpose of buffering, plays the purpose of protection maintained object through the deformation that has elastic protruding ball on the flexible protruding pad 13.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. 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 (5)
1. The utility model provides an aircraft maintenance anticollision board, includes connecting plate (1), anticollision board (2), assembly plate (3) and gag lever post (4), its characterized in that: the anti-collision plate (2) is fixedly connected with the limiting rod (4), the left end of the limiting rod (4) extends out of the left side wall of the anti-collision plate (2), one end, far away from the anti-collision plate (2), of the limiting rod (4) slidably extends out of the right side wall of the connecting plate (1), the top and the bottom of the right side wall of the anti-collision plate (2) are fixedly connected with main damping columns (6), two groups of main damping columns (6) are sleeved with second damping springs (12), two ends of each second damping spring (12) are fixedly connected with the side walls, close to the anti-collision plate (2) and the connecting plate (1), of the inner cavity of the connecting plate (1), the top and the bottom of the inner cavity of the connecting plate (1) are symmetrically provided with sliding grooves (10), two groups of main damping columns (6) extend into the top and the bottom of one end, far away from the left side wall of the connecting plate (1), of each sliding block (11) are fixedly connected with the sliding grooves (10), the sliding blocks (11) are slidably connected with the sliding grooves (, the top and the bottom of the left side wall of the assembly plate (3) are symmetrically and fixedly connected with auxiliary shock absorption columns (7), two groups of auxiliary shock absorption columns (7) are in sliding connection with a sliding groove (10), the centers of the inner cavities of the two groups of auxiliary shock absorption columns (7) are respectively provided with a sliding cavity (8), a main shock absorption column (6) is in sliding connection with the sliding cavity (8), the inner cavity of the sliding cavity (8) is in sliding connection with the main shock absorption column (6) extending into one end of the left side wall of the connecting plate (1), the cavity bottom of the sliding cavity (8) is fixedly connected with a spring (9) between the main shock absorption column (6) extending into one end of the left side wall of the connecting plate (1) and the main shock absorption column (6), first shock absorption springs (14) are sleeved on the two groups of auxiliary shock absorption columns (7), and the two ends of the first shock absorption springs (14) are respectively and fixedly connected with the side walls of the assembly plate (3) and the connecting plate (1), and the top and the bottom of the left side wall and the right side wall of the assembling plate (3) are provided with limiting holes (5) matched with the limiting rods (4).
2. An aircraft service fender according to claim 1 wherein: the left side wall of the anti-collision plate (2) is provided with a flexible convex pad (13), and the flexible convex pad (13) is composed of a plurality of elastic convex balls.
3. An aircraft service fender according to claim 1 wherein: the central line of the limiting rod (4) and the central line of the limiting hole (5) are on the same horizontal line.
4. An aircraft service fender according to claim 1 wherein: the maximum sliding distance of the connecting plate (1) on the limiting rod (4) is the same as the distance between the sliding block (11) and one end, extending into the right side wall of the connecting plate (1), of the auxiliary shock absorption column (7).
5. An aircraft service fender according to claim 1 wherein: the rod tip part of the limiting rod (4) is circular, and a fixing hole is formed in the surface of the rod tail of the limiting rod (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922366890.9U CN211223930U (en) | 2019-12-25 | 2019-12-25 | Aircraft maintenance anticollision board |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922366890.9U CN211223930U (en) | 2019-12-25 | 2019-12-25 | Aircraft maintenance anticollision board |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211223930U true CN211223930U (en) | 2020-08-11 |
Family
ID=71925776
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922366890.9U Expired - Fee Related CN211223930U (en) | 2019-12-25 | 2019-12-25 | Aircraft maintenance anticollision board |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211223930U (en) |
-
2019
- 2019-12-25 CN CN201922366890.9U patent/CN211223930U/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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200811 |