CN220207457U - Infrared nondestructive testing device for aircraft composite material - Google Patents
Infrared nondestructive testing device for aircraft composite material Download PDFInfo
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- CN220207457U CN220207457U CN202320025151.7U CN202320025151U CN220207457U CN 220207457 U CN220207457 U CN 220207457U CN 202320025151 U CN202320025151 U CN 202320025151U CN 220207457 U CN220207457 U CN 220207457U
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- 239000002131 composite material Substances 0.000 title claims abstract description 26
- 238000009659 non-destructive testing Methods 0.000 title abstract description 20
- 238000012360 testing method Methods 0.000 claims abstract description 11
- 239000000463 material Substances 0.000 claims abstract description 8
- 230000001066 destructive effect Effects 0.000 claims 6
- 238000007689 inspection Methods 0.000 claims 6
- 238000001514 detection method Methods 0.000 abstract description 11
- 238000000034 method Methods 0.000 abstract description 3
- 230000006978 adaptation Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The utility model relates to the technical field of material detection, and discloses an infrared nondestructive testing device for an aircraft composite material. This an infrared nondestructive test device for aircraft combined material will assemble the piece card in the upper end of gear for the gear has protection architecture, and the rotation of gear also can drive the rotation of assembly piece, consequently makes the infrared nondestructive test appearance of installing in assembly piece upper end can do not have the dead angle rotation according to needs, increases the convenience to aircraft combined material detection, in this operational architecture, the setting of limiting plate, makes gear drive pivoted assembly piece and axis of rotation second also have relation of connection, and can not influence the normal operating of gear with the in-process of axis of rotation second connection.
Description
Technical Field
The utility model relates to the technical field of material detection, in particular to an infrared nondestructive detection device for an aircraft composite material.
Background
The use amount of the composite material in the aircraft is gradually increased, so that the demand of production detection of the composite material is gradually increased, particularly, the detection is carried out, the aircraft runs in the air, the requirements on the performances of the composite material are extremely strict, and the detection equipment of the composite material for the aircraft is usually infrared nondestructive detection.
When the infrared nondestructive testing device detects the composite material, the composite material is usually placed on the infrared nondestructive testing device, which causes the problem that the infrared nondestructive testing device cannot move when detecting the composite material with larger size.
In order to solve the problems, the movable component is arranged below the infrared nondestructive testing equipment, so that the moving convenience of the infrared nondestructive testing equipment is improved, and the infrared nondestructive testing equipment can only move and cannot be adjusted in the same practical operation, so that the infrared nondestructive testing equipment is inconvenient to use.
Disclosure of Invention
(one) solving the technical problems
The utility model aims to provide an infrared nondestructive testing device for an aircraft composite material, so as to solve the problems in the background technology.
(II) technical scheme
In order to achieve the above-mentioned object, the utility model provides the following technical scheme: the utility model provides an infrared nondestructive test device for aircraft combined material, includes device body, supporting mechanism, movable mechanism, adjustment mechanism and infrared nondestructive test appearance, supporting mechanism is located the below of device body, movable mechanism is located the inside of supporting mechanism top, adjustment mechanism is located the upper end of movable mechanism, infrared nondestructive test appearance is located the upper end of movable mechanism, adjustment mechanism is including axis of rotation two, limiting plate, gear, assembly piece, spacing groove and rack, the fixed middle part that sets up in the axis of rotation outer end of limiting plate, gear fixed mounting is in the middle part of axis of rotation two upper ends, assembly piece fixed mounting is in the upper end of gear and with two swing joint of axis of rotation, the fixed below that sets up in the assembly piece lower extreme of spacing groove, the fixed top that sets up in the assembly piece lower extreme inside of rack.
Preferably, the supporting mechanism comprises a fixed bottom plate, an extension rod, pulleys, supporting columns, sliding grooves, a first rotating shaft and a rotating screw rod, wherein the extension rod is fixedly arranged below the middle part of the outer end of the fixed bottom plate, the pulleys are fixedly arranged at the lower end of the extension rod, the supporting columns are fixedly arranged at the middle part of the upper end of the fixed bottom plate, the sliding grooves are fixedly arranged at the middle parts of the left end and the right end of the supporting columns, the first rotating shaft is fixedly arranged inside the upper end and the lower end of the sliding grooves, the rotating screw rod is fixedly arranged on the inner side of the first rotating shaft, and the stress area of the fixed bottom plate is enlarged by arranging the extension rod, so that the lower end of the device is more stable.
Preferably, the movable mechanism comprises a movable rod, a limiting rod and a thread groove, wherein the limiting rod is fixedly arranged on the left side and the right side of the lower end of the movable rod, the thread groove is fixedly arranged in the side of the limiting rod, and the stability of the movable rod in up-down movement can be increased by arranging the limiting rod.
Preferably, the second fixed mounting of axis of rotation is in the upper end of movable rod, the limiting plate is ring gear, limiting plate and spacing groove looks adaptation, rack and gear looks adaptation, infrared nondestructive test appearance fixed mounting is in the upper end of assembly piece, and during the use, assembly piece card for the gear has protection architecture, and the rotation of gear also can drive the rotation of assembly piece, consequently makes the infrared nondestructive test appearance of installing at assembly piece upper end can carry out no dead angle rotation according to needs, increases the convenience to aircraft combined material detection.
Preferably, the number of the extension bars is four, the sliding grooves are symmetrically distributed in the middle of the left end and the right end of the supporting column, the first rotating shafts are symmetrically distributed in the inner portions of the upper end and the lower end of the sliding grooves, and when the device is used, the first rotating shafts are arranged, the rotation of the first rotating shafts can drive the rotation of the rotating screw rods, so that the convenience of the device in height adjustment is improved.
Preferably, the movable rod movable mounting is in the inside of support column, the gag lever post is the symmetric distribution in the left and right sides of movable rod lower extreme, the gag lever post is cross structure, screw thread groove and rotation lead screw looks adaptation are through with screw thread groove and rotation lead screw looks adaptation, increase the stability that the movable rod used after adjusting on the one hand, make the movable rod pass through the gag lever post and rotate the connection of lead screw on the one hand, make the movable rod can reciprocate by oneself.
Compared with the prior art, the utility model has the beneficial effects that:
1. according to the infrared nondestructive testing device for the aircraft composite material, the assembly block is clamped at the upper end of the gear, so that the gear is provided with the protection structure, and the rotation of the gear can drive the assembly block to rotate, so that the infrared nondestructive testing device arranged at the upper end of the assembly block can rotate at a dead angle according to the required degree, the convenience of detecting the aircraft composite material is improved, in the operation structure, the limiting plate is arranged, so that the gear drives the rotating assembly block and the rotating shaft II to have a connection relationship, and the normal operation of the gear cannot be influenced in the process of being connected with the rotating shaft II;
2. according to the infrared nondestructive testing device for the aircraft composite material, the thread groove is matched with the rotating screw rod, so that the stability of the movable rod after adjustment is improved, the movable rod can move up and down by itself through the connection of the limiting rod and the rotating screw rod, and meanwhile, the limiting rod of the cross-shaped structure is used for improving the stability of the movable rod when moving up and down and being connected with the support column;
3. this an infrared nondestructive test device for aircraft combined material enlarges the area of being stressed of fixed bottom plate through setting up the extension rod, makes the lower extreme of device more firm to install the pulley at the lower extreme of extension rod, increase the convenience that the device removed.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a schematic cross-sectional view of the present utility model;
FIG. 3 is a split structure schematic diagram of the movable mechanism of the utility model;
fig. 4 is an enlarged schematic view of fig. 1 a according to the present utility model.
In the figure: 1. a device body; 2. a support mechanism; 201. a fixed bottom plate; 202. an extension rod; 203. a pulley; 204. a support column; 205. a chute; 206. a first rotating shaft; 207. rotating the screw rod; 3. a movable mechanism; 301. a movable rod; 302. a limit rod; 303. a thread groove; 4. an adjusting mechanism; 401. a second rotating shaft; 402. a limiting plate; 403. a gear; 404. a mounting block; 405. a limit groove; 406. a rack; 5. an infrared nondestructive detector.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present utility model, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
Referring to fig. 1-4, the present utility model provides a technical solution: the infrared nondestructive testing device for the aircraft composite material comprises a device body 1, a supporting mechanism 2, a movable mechanism 3, an adjusting mechanism 4 and an infrared nondestructive testing instrument 5, wherein the supporting mechanism 2 is positioned below the device body 1, the movable mechanism 3 is positioned in the upper part of the supporting mechanism 2, the adjusting mechanism 4 is positioned at the upper end of the movable mechanism 3, the infrared nondestructive testing instrument 5 is positioned at the upper end of the movable mechanism 3, the adjusting mechanism 4 comprises a second rotating shaft 401, a limiting plate 402, a gear 403, an assembling block 404, a limiting groove 405 and a rack 406, the limiting plate 402 is fixedly arranged in the middle of the outer end of the second rotating shaft 401, the gear 403 is fixedly arranged in the middle of the upper end of the second rotating shaft 401, the assembling block 404 is fixedly arranged at the upper end of the gear 403 and movably connected with the second rotating shaft 401, the limiting groove 405 is fixedly arranged below the lower end of the assembling block 404, and the rack 406 is fixedly arranged above the lower end of the assembling block 404;
the supporting mechanism 2 comprises a fixed bottom plate 201, an extension rod 202, pulleys 203, a support column 204, a sliding groove 205, a first rotating shaft 206 and a rotating screw rod 207, wherein the extension rod 202 is fixedly arranged below the middle part of the outer end of the fixed bottom plate 201, the pulleys 203 are fixedly arranged at the lower end of the extension rod 202, the support column 204 is fixedly arranged in the middle part of the upper end of the fixed bottom plate 201, the sliding groove 205 is fixedly arranged in the middle parts of the left end and the right end of the support column 204, the first rotating shaft 206 is fixedly arranged in the upper end and the lower end of the sliding groove 205, the rotating screw rod 207 is fixedly arranged on the inner side of the first rotating shaft 206, and the stress area of the fixed bottom plate 201 is enlarged by arranging the extension rod 202, so that the lower end of the device is more stable; the movable mechanism 3 comprises a movable rod 301, a limiting rod 302 and a thread groove 303, wherein the limiting rod 302 is fixedly arranged on the left side and the right side of the lower end of the movable rod 301, the thread groove 303 is fixedly arranged in the side of the limiting rod 302, and the stability of the movable rod 301 in up-and-down movement can be improved by arranging the limiting rod 302;
the second rotating shaft 401 is fixedly arranged at the upper end of the movable rod 301, the limiting plate 402 is an annular mechanism, the limiting plate 402 is matched with the limiting groove 405, the rack 406 is matched with the gear 403, the infrared nondestructive detector 5 is fixedly arranged at the upper end of the assembling block 404, when in use, the assembling block 404 is clamped at the upper end of the gear 403, so that the gear 403 has a protection structure, and the rotation of the gear 403 can also drive the rotation of the assembling block 404, therefore, the infrared nondestructive detector 5 arranged at the upper end of the assembly block 404 can rotate 360 degrees without dead angles according to the requirement, and the convenience of detecting the aircraft composite material is improved; the number of the extension rods 202 is four, the sliding grooves 205 are symmetrically distributed at the middle parts of the left end and the right end of the supporting column 204, the first rotating shafts 206 are symmetrically distributed in the upper end and the lower end of the sliding grooves 205, through the arrangement of the first rotating shaft 206, when the device is used, the rotation of the first rotating shaft 206 can drive the rotating screw rod 207 to rotate, so that the convenience of the device in height adjustment is improved; the movable rod 301 is movably arranged in the support column 204, the limiting rods 302 are symmetrically distributed on the left side and the right side of the lower end of the movable rod 301, the limiting rods 302 are of a cross structure, the threaded grooves 303 are matched with the rotating screw rods 207, on one hand, the stability of the movable rod 301 after being adjusted is improved by matching the threaded grooves 303 with the rotating screw rods 207, on the other hand, the movable rod 301 can automatically move up and down through the connection of the limiting rods 302 and the rotating screw rods 207, and meanwhile, the limiting rods 302 of the cross structure increase the stability of the movable rod 301 when moving up and down and being connected with the support column 204; the number of the pulleys 203 is four, the limiting rods 302 are matched with the sliding grooves 205, and the device is more convenient and faster to move by arranging the pulleys 203.
Working principle: according to the technical scheme, the infrared nondestructive testing device for the aircraft composite material is characterized in that firstly, the infrared nondestructive testing device 5 is arranged at the upper end of the assembly block 404, the assembly block 404 is clamped at the upper end of the gear 403, so that the gear 403 is provided with a protection structure, and the rotation of the gear 403 can drive the assembly block 404 to rotate, therefore, the infrared nondestructive testing device 5 arranged at the upper end of the assembly block 404 can rotate 360 degrees without dead angle according to the requirement, the convenience of the aircraft composite material detection is improved, in the operation structure, the limiting plate 402 is arranged, the gear 403 drives the rotating assembly block 404 and the rotating shaft 401 to have a connection relationship, the normal operation of the gear 403 is not influenced in the process of being connected with the rotating shaft 401, and when the device is in use, the rotation of the rotating shaft 206 and the rotating screw 207 can be driven by the rotation of the rotating shaft 206 arranged at the inner end of the chute 205, and the movable rod 301 in threaded connection with the rotating screw 207 can move up and down in the support column 204, and the convenience of the aircraft composite material detection is further improved.
Finally, it should be noted that the above description is only for illustrating the technical solution of the present utility model, and not for limiting the scope of the present utility model, and that the simple modification and equivalent substitution of the technical solution of the present utility model can be made by those skilled in the art without departing from the spirit and scope of the technical solution of the present utility model.
Claims (7)
1. The utility model provides an infrared nondestructive test device for aircraft combined material, includes device body (1), supporting mechanism (2), movable mechanism (3), adjustment mechanism (4) and infrared nondestructive test appearance (5), its characterized in that: supporting mechanism (2) are located the below of device body (1), movable mechanism (3) are located the inside of supporting mechanism (2) top, adjustment mechanism (4) are located the upper end of movable mechanism (3), infrared nondestructive test appearance (5) are located the upper end of movable mechanism (3), adjustment mechanism (4) are including axis of rotation two (401), limiting plate (402), gear (403), assembly piece (404), spacing groove (405) and rack (406), limiting plate (402) are fixed to be set up in the middle part of axis of rotation two (401) outer end, and gear (403) fixed mounting is in the middle part of axis of rotation two (401) upper end, assembly piece (404) fixed mounting is in the upper end of gear (403) and with axis of rotation two (401) swing joint, the fixed below that sets up in assembly piece (404) lower extreme inside of rack (406), the fixed top that sets up in assembly piece (404) lower extreme.
2. An infrared non-destructive inspection apparatus for an aircraft composite according to claim 1, wherein: supporting mechanism (2) are including PMKD (201), extension pole (202), pulley (203), support column (204), spout (205), axis of rotation one (206) and rotation lead screw (207), extension pole (202) fixed mounting is in the below at PMKD (201) outer end middle part, pulley (203) fixed mounting is in the lower extreme of extension pole (202), support column (204) fixed setting is in the middle part of PMKD (201) upper end, spout (205) fixed setting is in the middle part at both ends about support column (204), axis of rotation one (206) fixed mounting is in the inside at both ends about spout (205), axis of rotation lead screw (207) fixed mounting is in the inboard of axis of rotation one (206).
3. An infrared non-destructive inspection apparatus for an aircraft composite according to claim 2, wherein: the movable mechanism (3) comprises a movable rod (301), a limiting rod (302) and a thread groove (303), wherein the limiting rod (302) is fixedly arranged on the left side and the right side of the lower end of the movable rod (301), and the thread groove (303) is fixedly arranged in the side of the limiting rod (302).
4. An infrared non-destructive inspection apparatus for aircraft composite according to claim 3, wherein: the second rotating shaft (401) is fixedly arranged at the upper end of the movable rod (301), the limiting plate (402) is an annular mechanism, the limiting plate (402) is matched with the limiting groove (405), the rack (406) is matched with the gear (403), and the infrared nondestructive detector (5) is fixedly arranged at the upper end of the assembly block (404).
5. An infrared non-destructive inspection apparatus for an aircraft composite according to claim 4, wherein: the number of the extension rods (202) is four, the sliding grooves (205) are symmetrically distributed in the middle of the left end and the right end of the supporting column (204), the first rotating shafts (206) are symmetrically distributed in the upper end and the lower end of the sliding groove (205).
6. An infrared non-destructive inspection apparatus for an aircraft composite according to claim 5, wherein: the movable rod (301) is movably mounted in the support column (204), the limiting rods (302) are symmetrically distributed on the left side and the right side of the lower end of the movable rod (301), the limiting rods (302) are of a cross structure, and the threaded grooves (303) are matched with the rotary screw rods (207).
7. An infrared non-destructive inspection apparatus for an aircraft composite according to claim 6, wherein: the number of the pulleys (203) is four, and the limiting rods (302) are matched with the sliding grooves (205).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320025151.7U CN220207457U (en) | 2023-01-05 | 2023-01-05 | Infrared nondestructive testing device for aircraft composite material |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320025151.7U CN220207457U (en) | 2023-01-05 | 2023-01-05 | Infrared nondestructive testing device for aircraft composite material |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220207457U true CN220207457U (en) | 2023-12-19 |
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ID=89151205
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320025151.7U Active CN220207457U (en) | 2023-01-05 | 2023-01-05 | Infrared nondestructive testing device for aircraft composite material |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220207457U (en) |
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2023
- 2023-01-05 CN CN202320025151.7U patent/CN220207457U/en active Active
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