CN213532569U - Avionics fault diagnosis tool box - Google Patents
Avionics fault diagnosis tool box Download PDFInfo
- Publication number
- CN213532569U CN213532569U CN202022128308.8U CN202022128308U CN213532569U CN 213532569 U CN213532569 U CN 213532569U CN 202022128308 U CN202022128308 U CN 202022128308U CN 213532569 U CN213532569 U CN 213532569U
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- China
- Prior art keywords
- avionics
- wedge
- fault diagnosis
- piston
- handle
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- Expired - Fee Related
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- 238000003745 diagnosis Methods 0.000 title claims abstract description 20
- 238000001514 detection method Methods 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000005299 abrasion Methods 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
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Abstract
The utility model discloses an avionics fault diagnosis tool box, which relates to the technical field of avionics detection tool boxes and mainly solves the problem that the existing avionics tool box is inconvenient to move; the device includes the casing, be provided with the rack in the casing, the bottom of casing is provided with the pull rod, the pull rod links to each other with the link, the symmetry is provided with the second connecting rod on the link, be provided with the second piston on the second connecting rod, the second piston links to each other with the piston pipe, the intraductal first piston that is provided with of piston, first piston links to each other with the head rod, be provided with the pulley on the head rod, the top of casing is provided with the mounting bracket, the intermediate position of mounting bracket has the handle, the handle in-connection has the push rod, the end of push rod is provided with first wedge, first wedge links to each other with the second wedge, the second wedge links to each other with the bracing piece, the bracing piece links to each other with the supporting seat.
Description
Technical Field
The utility model relates to a diagnostic tool case technical field specifically is an avionics fault diagnosis toolbox.
Background
In the technical field of avionics, the avionics equipment is subjected to fault detection and frequent maintenance by being provided with the corresponding fault diagnosis tool box, various corresponding tools and measuring instruments are arranged, and the conventional avionics fault diagnosis tool box has complete functions and richer tools arranged in the avionics fault diagnosis tool box, so that the tool box is increased in size and weight and is inconvenient to move.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an avionics fault diagnosis toolbox 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 avionics fault diagnosis toolbox comprises a shell, wherein a placing frame is arranged in the shell, a pull rod is arranged at the bottom of the shell and is connected with a connecting frame, second connecting rods are symmetrically arranged on the connecting frame, second pistons are arranged on the second connecting rods and are connected with piston tubes, first pistons are arranged in the piston tubes and are connected with the first connecting rods, pulleys are arranged on the first connecting rods, a mounting frame is arranged at the top of the shell, a handle is arranged in the middle of the mounting frame, two push rods are symmetrically connected in the handle, adjusting threads are arranged on the push rods, the push rods are connected with the handle through the adjusting threads, a first wedge block is arranged at the tail end of each push rod and is connected with a second wedge block, and the second wedge block is connected with a support column, the support column is connected with the support seat, a clamping block is arranged on the support column, a baffle is arranged in the shell, the support column is connected with the baffle in a sliding mode, and a spring is arranged between the support column and the baffle.
As a further aspect of the present invention: the rack is provided with two layers.
As a further aspect of the present invention: the piston tube is of a U-shaped design.
As a further aspect of the present invention: the pulley is a universal wheel.
As a further aspect of the present invention: the handle is provided with a rubber ring.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model realizes the movement operation of the shell by arranging the pull rod in the shell and matching the first piston, the second piston and the pulley, thereby being convenient for moving the tool box in a long distance; the mounting frame is arranged on the shell, and the position of the supporting column is adjusted by matching with the mounting frame, the push rod, the adjusting thread, the first wedge-shaped block and the second wedge-shaped block and the clamping block, the spring and the baffle plate, so that the shell is conveniently supported by the supporting seat when the shell is horizontally placed; through above-mentioned structure effectively promote the removal ability to the toolbox.
Drawings
Fig. 1 is a schematic structural diagram of an avionics fault diagnosis kit.
Fig. 2 is a schematic view of the installation of a support column in an avionics fault diagnosis kit.
FIG. 3 is a schematic view of the mounting of the pulleys in an avionics fault diagnosis kit.
Fig. 4 is a schematic structural diagram of a push rod in an avionics fault diagnosis kit.
In the figure: 1-shell, 2-placing rack, 3-pull rod, 4-pulley, 5-first connecting rod, 6-piston tube, 7-first piston, 8-connecting rack, 9-second connecting rod, 10-second piston, 11-handle, 12-push rod, 13-adjusting screw thread, 14-first wedge block, 15-second wedge block, 16-mounting rack, 17-clamping block, 18-spring, 19-baffle, 20-support column and 21-support seat.
Detailed Description
In the description of the present invention, it is to be understood that the terms "upper", "lower", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and "fixed" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those skilled in the art.
The technical solution of the present patent will be described in further detail with reference to the following embodiments.
Example 1:
referring to fig. 1-4, an avionics fault diagnosis tool box comprises a housing 1, a placement frame 2 is arranged in the housing 1, a pull rod 3 is arranged at the bottom of the housing 1, the pull rod 3 is connected with a connecting frame 8, second connecting rods 9 are symmetrically arranged on the connecting frame 8, second pistons 10 are arranged on the second connecting rods 9, the second pistons 10 are connected with a piston tube 6, first pistons 7 are arranged in the piston tube 6, the first pistons 7 are connected with first connecting rods 5, pulleys 4 are arranged on the first connecting rods 5, a mounting frame 16 is arranged at the top of the housing 1, a handle 11 is arranged at the middle position of the mounting frame 16, two push rods 12 are symmetrically connected in the handle 11, adjusting threads 13 are arranged on the push rods 12, the push rods 12 are connected with the handle 11 through the adjusting threads 13, a first wedge block 14 is arranged at the tail ends of the push rods 12, first wedge 14 links to each other with second wedge 15, second wedge 15 links to each other with support column 20, support column 20 links to each other with supporting seat 21, be provided with fixture block 17 on the support column 20, set up baffle 19 in the casing 1, support column 20 and baffle 19 sliding connection, be provided with spring 18 between support column 20 and the baffle 19.
Specifically, the position of the pulley 4 is controlled through the pull rod 3, the piston tube 6, the first piston 7, the second piston 10, the first connecting rod 5 and the second connecting rod 9, when the pull rod 3 is pulled out outwards, the second piston 10 pushes the first piston 7, the first connecting rod 5 moves downwards, the pulley 4 extends outwards, otherwise, the pulley 4 is retracted, and therefore the tool box is convenient to move.
More specifically, in order to support the horizontally placed shell 1, the mounting frame 16 is arranged on the shell 1, the handle 11 is arranged between the mounting frames 16, the push rod 12, the adjusting thread 13, the first wedge-shaped block 14 and the second wedge-shaped block 15 are combined to push the supporting column 20 and the supporting seat 21, so that supporting is achieved, and the supporting seat 21 and the supporting column 20 can return to the shell 1 conveniently through the arrangement of the spring 18, the fixture block 17 and the baffle plate 19.
Further, the placing rack 2 is provided with two layers.
Further, the piston tube 6 is of U-shaped design.
Further, the pulley 4 is a universal wheel.
Further, a rubber ring is arranged on the handle 11.
Specifically, the handle 11 is provided with a rubber ring to improve the grip feeling.
Example 2:
this embodiment is a further improvement and a limitation of embodiment 1 on the basis of embodiment 1.
An avionics fault diagnosis kit, comprising all the components of embodiment 1, with the difference that the material of the support base 21 is limited.
Further, the support seat 21 is made of rubber.
Specifically, the supporting seat 21 made of rubber has the advantages of shock absorption and abrasion reduction.
The utility model discloses a theory of operation is:
as shown in fig. 1-4, when the toolbox needs to be moved, the pull rod 3 is pulled out, under the action of the piston tube 6 and the first and second pistons 7 and 10, the pulley 4 extends out of the housing 1, so as to facilitate dragging the toolbox, and at the same time, under the action of the piston tube 6, the connecting operation is performed by compressed air, so as to achieve a certain damping effect.
When the tool box is horizontally placed, the handle 11 is firstly rotated, so that the push rod 12 drives the first wedge block 14 to move, the support column 20 and the support seat 21 are pushed to extend outwards, and then the shell 1 is flatly placed, so that the tool box is supported.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (5)
1. An avionics fault diagnosis toolbox comprises a shell (1), wherein a placing frame (2) is arranged in the shell (1), and is characterized in that a pull rod (3) is arranged at the bottom of the shell (1), the pull rod (3) is connected with a connecting frame (8), second connecting rods (9) are symmetrically arranged on the connecting frame (8), second pistons (10) are arranged on the second connecting rods (9), the second pistons (10) are connected with a piston tube (6), first pistons (7) are arranged in the piston tube (6), the first pistons (7) are connected with first connecting rods (5), pulleys (4) are arranged on the first connecting rods (5), a mounting frame (16) is arranged at the top of the shell (1), a handle (11) is arranged in the middle of the mounting frame (16), and two push rods (12) are symmetrically connected in the handle (11), be provided with adjustment screw thread (13) on push rod (12), push rod (12) link to each other with handle (11) through adjustment screw thread (13), the end of push rod (12) is provided with first wedge (14), first wedge (14) link to each other with second wedge (15), second wedge (15) link to each other with support column (20), support column (20) link to each other with supporting seat (21), be provided with fixture block (17) on support column (20), set up baffle (19) in casing (1), support column (20) and baffle (19) sliding connection, be provided with spring (18) between support column (20) and baffle (19).
2. An avionics fault diagnosis kit according to claim 1, characterized in that the rack (2) is provided with two layers.
3. Avionics fault diagnosis kit according to claim 1, characterized in that the piston tube (6) is of U-shaped design.
4. An avionics fault diagnosis kit according to claim 2, characterized in that the pulleys (4) are universal wheels.
5. An avionics fault diagnosis kit according to claim 1, characterized in that a rubber ring is provided on the handle (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022128308.8U CN213532569U (en) | 2020-09-24 | 2020-09-24 | Avionics fault diagnosis tool box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022128308.8U CN213532569U (en) | 2020-09-24 | 2020-09-24 | Avionics fault diagnosis tool box |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213532569U true CN213532569U (en) | 2021-06-25 |
Family
ID=76494085
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022128308.8U Expired - Fee Related CN213532569U (en) | 2020-09-24 | 2020-09-24 | Avionics fault diagnosis tool box |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213532569U (en) |
-
2020
- 2020-09-24 CN CN202022128308.8U patent/CN213532569U/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: 20210625 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |