CN221124379U - Aviation material test box - Google Patents
Aviation material test box Download PDFInfo
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- CN221124379U CN221124379U CN202322359442.2U CN202322359442U CN221124379U CN 221124379 U CN221124379 U CN 221124379U CN 202322359442 U CN202322359442 U CN 202322359442U CN 221124379 U CN221124379 U CN 221124379U
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- 238000012360 testing method Methods 0.000 title claims abstract description 136
- 239000000463 material Substances 0.000 title claims abstract description 55
- 238000005192 partition Methods 0.000 claims abstract description 15
- 239000013013 elastic material Substances 0.000 claims description 3
- 238000005057 refrigeration Methods 0.000 claims description 3
- 230000002146 bilateral effect Effects 0.000 claims 1
- 230000010354 integration Effects 0.000 abstract description 2
- 238000002485 combustion reaction Methods 0.000 description 5
- 238000004154 testing of material Methods 0.000 description 5
- 230000007613 environmental effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000000969 carrier Substances 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000004880 explosion Methods 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000779 smoke Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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Abstract
The utility model provides an aviation material test box. The aviation material test box comprises: the box body is provided with a partition board in the middle of the interior of the box body, the partition board divides the interior of the box body into an upper part and a lower part, the upper end is a low-temperature test area, and the lower end is a high-temperature test area; the low-temperature test area is internally provided with a placing plate; the high-temperature test area, install a plurality of heaters on the inner wall of the inside both sides of high-temperature test area, install on the inside bottom surface of high-temperature test area and place the case. According to the utility model, the partition board is arranged in the middle of the box body and is made of high-strength materials, the high temperature resistance and the low temperature resistance are realized, and the partition board divides the interior of the box body into the low temperature test area and the high temperature test area, so that the device can test aviation materials in a high-low temperature environment, the test is comprehensive, and meanwhile, the device is high in integration degree and good in practicality.
Description
Technical Field
The utility model belongs to the technical field of test boxes, and particularly relates to an aviation material test box.
Background
With the continuous development of modern technological industries, aviation materials are also widely used as important carriers for advancing the development of aviation industry, and various environmental tests are required to ensure the quality of the aviation materials, and the environmental tests often require special environmental test boxes so as to test the aviation materials under various different environmental conditions.
The prior authorized public number is CN208026666U, and discloses an aviation material combustion performance testing device, which comprises a test box, wherein a testing cavity is arranged in the test box; the sample device is arranged on the test box; the blast lamp device is arranged in the test chamber; the smoke exhaust system is communicated with the test chamber; the flue gas collection device and the heat testing device are arranged in the testing cavity; the pattern device comprises 4 clamps, wherein two clamps are horizontally arranged; the other two clamps form a certain included angle with the horizontal plane. The device for testing the combustion performance of the aviation material has the advantages that the design of the test box is elegant and attractive, the device can be used for testing the combustion performance of the aviation material, and the test box is detachable. The blast lamp device is positioned through motor control, and is convenient and accurate. When gas leakage occurs, the system can automatically close the gas path so as to avoid explosion risk; the combustion performance of the material at different positions can be measured in one test. However, the above-mentioned device for testing combustion performance of aviation material can only test aviation material at high temperature, and aviation material is often used in very low temperature environment, so that it is required to test aviation material at very low temperature, so as to test its property in very low temperature environment, and therefore, it is required to provide an aviation material testing box to solve the above-mentioned problems.
Disclosure of utility model
The technical content of the utility model is to provide an aviation material test box.
In order to solve the above problems, the present utility model provides an aviation material testing box, comprising: the box body is provided with a partition board in the middle of the interior of the box body, the partition board divides the interior of the box body into an upper part and a lower part, the upper end is a low-temperature test area, and the lower end is a high-temperature test area; the low-temperature test area is internally provided with a placing plate; the high-temperature test area, install a plurality of heaters on the inner wall of the inside both sides of high-temperature test area, install on the inside bottom surface of high-temperature test area and place the case.
As a further solution of the utility model, two sliding strips are symmetrically arranged at the bottom of the placing box, two sliding grooves are formed in the inner bottom surface of the high-temperature test area, and the sliding strips are arranged in the sliding grooves, so that the placing box can be arranged in the high-temperature test area.
As a further solution of the utility model, the front surface of the placement box is provided with a first pull ring, the top of the placement box is provided with an opening structure and is provided with a cover plate, the lower end size of the cover plate is the same as the inner diameter of the placement box, the upper end size of the cover plate is larger than the inner diameter of the placement box, the top of the cover plate is provided with a second pull ring, the cover plate is convenient to take off from the top of the placement box, and aviation materials to be tested can be placed in the placement box.
As a further solution of the utility model, two fixing pipes are arranged on the left side of the front surface of the lower end of the box body, a rotating shaft is inserted into the upper fixing pipe and the lower fixing pipe, the rotating shaft is in rotating connection with the two fixing pipes, connecting sleeves are arranged on the outer side of the rotating shaft, the two connecting sleeves are symmetrically arranged on the rotating shaft, a movable door is connected on the right side of the two connecting sleeves, the movable door is arranged on the outer side of the front surface of the high-temperature test area, and a third pull ring is arranged on the right end of the front surface of the movable door, so that the movable door can be pulled conveniently.
As a further solution of the utility model, two placing plates are arranged in the low-temperature test area, and the periphery of each placing plate is provided with a convex structure, so that aviation materials can be placed on the top of each placing plate conveniently.
As a further solution of the utility model, the bottom of the placing plate is symmetrically provided with the fixing box, the two sides of one end of the fixing box, which is arranged in the low-temperature test area, are provided with the fixing plate, the fixing plate is fixedly connected with the inner wall of the box body through the fixing bolt, the ball screw is arranged in the fixing box, the left end of the ball screw is rotatably connected with the inner wall of the fixing box, the right end of the ball screw extends out of the fixing box and is connected to the motor, the ball screw is sleeved with the ball screw sleeve, the top of the ball screw sleeve is fixedly connected with the bottom of the placing plate, the placing plate is not contacted with the inner wall of the box body, and the motor can be used for driving the ball screw to rotate so as to drive the ball screw sleeve to move, thereby driving the placing plate connected with the ball screw sleeve to move.
As a further solution of the utility model, the upper end of the front surface of the box body is provided with two sliding doors, the sliding doors are arranged on the front surface of the low-temperature test area, the bottom of each sliding door is provided with a sliding rod, the area opposite to the sliding rods on the partition plate is provided with sliding grooves, the two ends of each sliding groove are provided with through holes, the diameter of each through hole is matched with the diameter of each sliding rod, the size of the two ends of each sliding rod is larger than the diameter of each through hole, the top of each sliding door is provided with a sliding block, the top of the front surface of the box body is provided with a sliding groove, each sliding block is arranged in each sliding groove, and the sliding blocks are of T-shaped structures, so that the sliding doors cannot be separated from the front surface of the low-temperature test area.
As a further solution of the utility model, two locking blocks are symmetrically arranged on the front side of the sliding door up and down, clamping grooves are formed in the top and the bottom of each locking block, when the two sliding doors are close to each other, the low-temperature test area is in a closed state, the two locking blocks on the two sliding doors in the same horizontal direction are combined together, clamping plates are arranged on the outer sides of the front sides of the two locking blocks, clamping blocks are arranged on the top and the bottom of the inner sides of the clamping plates, the sizes of the clamping blocks are the same as those of the clamping grooves formed in the locking blocks, the clamping plates are made of elastic materials, and grooves are formed in the sliding doors, so that the sliding doors can be pulled leftwards and rightwards conveniently.
Compared with the related art, the aviation material test box provided by the utility model has the following beneficial effects:
1. According to the utility model, the partition board is arranged in the middle of the box body and is made of high-strength materials, the high temperature resistance and the low temperature resistance are realized, and the partition board divides the interior of the box body into the low temperature test area and the high temperature test area, so that the device can test aviation materials in a high-low temperature environment, the test is comprehensive, and meanwhile, the device is high in integration degree and good in practicality.
2. According to the utility model, the ball screw sleeve is arranged at the bottom of the placing plate, the ball screw is inserted into the ball screw sleeve, and the motor is used for driving the ball screw to rotate so as to drive the ball screw sleeve to move, so that the placing plate connected with the ball screw sleeve is driven to move, the placing plate can move out of the low-temperature test area, and aviation materials can be conveniently placed at the top of the placing plate.
3. According to the utility model, the two sliding strips are symmetrically arranged at the bottom of the placement box, two sliding grooves are formed in the inner bottom surface of the high-temperature test area, and the sliding strips are arranged in the sliding grooves, so that the placement box can be arranged in the high-temperature test area, and meanwhile, the placement box can be conveniently taken out from the high-temperature test area.
Drawings
The present utility model is further described below with reference to the accompanying drawings for the convenience of understanding by those skilled in the art.
FIG. 1 is a schematic diagram of an open front perspective of an aircraft material test box according to the present utility model;
FIG. 2 is a schematic elevational view of an aircraft material test box according to the present utility model;
FIG. 3 is a schematic view of a placement box structure of an aircraft material test box according to the present utility model;
FIG. 4 is a schematic view showing the bottom structure of a placement plate of an aircraft material test box according to the present utility model;
FIG. 5 is a schematic diagram of the structure of a fixed box, a ball screw and a motor of the aviation material testing box;
FIG. 6 is a schematic diagram of the structure of a locking block and a clamping plate of the aviation material testing box;
FIG. 7 is an enlarged schematic view of the structure of the aircraft material test box at A;
fig. 8 is an enlarged schematic view of the structure of the aviation material testing box at the position B.
In the figure: 1. a case; 2. a partition panel; 3. a low temperature test zone; 4. a high temperature test zone; 5. a refrigeration plate; 6. placing a plate; 7. a heater; 8. placing a box; 9. a slide bar; 10. a first pull ring; 11. a cover plate; 12. a second pull ring; 13. a fixed tube; 14. a rotating shaft; 15. connecting sleeves; 16. a movable door; 17. a third pull ring; 18. a fixed box; 19. a fixing plate; 20. a ball screw; 21. a motor; 22. a ball screw sleeve; 23. a moving door; 24. a slide bar; 25. a slide block; 26. a locking piece; 27. and (5) clamping plates.
Detailed Description
Please refer to fig. 1, fig. 2, fig. 3, fig. 4, fig. 5, fig. 6, fig. 7, fig. 8 in combination. An aircraft material test kit, comprising: the device comprises a box body 1, wherein a partition board 2 is arranged in the middle of the interior of the box body 1, the partition board 2 divides the interior of the box body 1 into an upper part and a lower part, the upper end is a low-temperature test area 3, and the lower end is a high-temperature test area 4; the low-temperature test area 3, wherein the inner walls of the two sides of the inside of the low-temperature test area 3 are provided with refrigeration plates 5, and the inside of the low-temperature test area 3 is provided with a placing plate 6; the inner walls of the two sides of the inside of the high temperature test area 4 are provided with a plurality of heaters 7, and the bottom surface of the inside of the high temperature test area 4 is provided with a placing box 8.
Two sliding strips 9 are symmetrically arranged at the bottom of the placement box 8, two sliding grooves are formed in the inner bottom surface of the high-temperature test area 4, and the sliding strips 9 are arranged in the sliding grooves, so that the placement box 8 can be arranged in the high-temperature test area 4, and meanwhile, the placement box 8 can be conveniently taken out from the high-temperature test area 4;
The front of the placement box 8 is provided with a first pull ring 10, the placement box 8 is conveniently taken out from the high-temperature test area 4, the top of the placement box 8 is provided with an opening structure and is provided with a cover plate 11, the size of the lower end of the cover plate 11 is the same as the inner diameter of the placement box 8, the connection tightness between the cover plate 11 and the placement box 8 is improved, the size of the upper end of the cover plate 11 is larger than the inner diameter of the placement box 8, the top of the cover plate 11 is provided with a second pull ring 12, the cover plate 11 is conveniently taken down from the top of the placement box 8, aviation materials to be tested can be placed in the placement box 8, the placement box 8 filled with the aviation materials is installed in the high-temperature test area 4, and the high-temperature test of the aviation materials can be carried out by utilizing the heater 7;
The fixed pipes 13 are arranged on the left side of the front surface of the lower end of the box body 1, two fixed pipes 13 are arranged, a rotating shaft 14 is inserted into the upper fixed pipe 13 and the lower fixed pipe 13, the rotating shaft 14 and the two fixed pipes 13 are connected in a rotating way, a connecting sleeve 15 is arranged on the outer side of the rotating shaft 14, the connecting sleeves 15 are symmetrically arranged on the rotating shaft 14, the right sides of the two connecting sleeves 15 are connected with a movable door 16, the movable door 16 is arranged on the outer side of the front surface of the high-temperature test area 4, the movable door 16 can rotate around the rotating shaft 14, the high-temperature test area 4 can be in a closed state by utilizing the movable door 16, the high-temperature test of aviation materials placed in the movable door 16 can be conveniently tested at high temperature, and a third pull ring 17 is arranged on the right end of the front surface of the movable door 16, and the movable door 16 is conveniently pulled;
Two placing plates 6 are arranged in the low-temperature test area 3, the periphery of each placing plate 6 is provided with a protruding structure, so that aviation materials can be placed at the top of each placing plate 6 conveniently, the interior of the low-temperature test area 3 can be in a low-temperature state by utilizing the refrigerating plate 5, and then the aviation materials placed at the top of each placing plate 6 are subjected to low-temperature test;
The fixing box 18 is symmetrically arranged at two sides of the bottom of the placement plate 6, the fixing plate 19 is arranged at two sides of one end of the fixing box 18 arranged in the low-temperature test area 3, the fixing plate 19 is fixedly connected with the inner wall of the box 1 through a fixing bolt, the fixing box 18 is firmly arranged in the box 1, the ball screw 20 is arranged in the fixing box 18, the left end of the ball screw 20 is rotationally connected with the inner wall of the fixing box 18, the right end of the ball screw 20 extends out of the fixing box 18 and is connected to the motor 21, the ball screw 20 is sleeved with the ball screw sleeve 22, the top of the ball screw sleeve 22 is fixedly connected with the bottom of the placement plate 6, the placement plate 6 is not contacted with the inner wall of the box 1, the ball screw 20 is driven to rotate by the motor 21, the ball screw sleeve 22 is driven to move, the placement plate 6 connected with the ball screw sleeve 22 is driven to move, the placement plate 6 is conveniently moved out of the low-temperature test area 3 and is placed on the aviation material, and the motor 21 is driven to rotate reversely, the placement plate 6 is enabled to move into the low-temperature test area 3, and the aviation material is placed on the low-temperature test area, and the low-temperature test is carried out;
The upper end of the front surface of the box body 1 is provided with two movable doors 23, the two movable doors 23 are arranged on the front surface of the low-temperature test area 3, sliding rods 24 are arranged at the bottom of the movable doors 23, sliding grooves are formed in opposite areas of the partition plate 2, through holes are formed in two ends of each sliding groove, the diameter of each through hole is matched with that of each sliding rod 24, the size of each sliding rod 24 is larger than that of each through hole, the movable doors 23 can be prevented from being separated from the left side and the right side of the low-temperature test area 3 in the process of moving left and right, sliding blocks 25 are arranged at the tops of the movable doors 23, sliding grooves are formed in the tops of the front surfaces of the box body 1, the sliding blocks 25 are arranged in the sliding grooves, the sliding blocks 25 are of T-shaped structures, the movable doors 23 can be prevented from being separated from the front surface of the low-temperature test area 3, the opening and closing of the low-temperature test area 3 can be controlled by utilizing the movable doors 23, and the convenience in placing, testing and taking out of aviation materials can be guaranteed;
Two locking blocks 26 are symmetrically installed on the front side of the movable door 23 up and down, clamping grooves are formed in the top and the bottom of each locking block 26, when the two movable doors 23 are close to each other, the low-temperature test area 3 is in a closed state, two locking blocks 26 which are located on the same horizontal direction on the two movable doors 23 are combined together, clamping plates 27 are installed on the outer sides of the front sides of the two movable doors, clamping blocks are arranged on the top and the bottom of the inner sides of the clamping plates 27, the sizes of the clamping blocks are the same as those of the clamping grooves formed in the locking blocks 26, the clamping plates 27 are utilized to enable the two locking blocks 26 on the two movable doors 23 to be combined together, the two movable doors 23 are further combined together, the low-temperature test area 3 is in a closed state, the clamping plates 27 are made of elastic materials and are convenient to detach from the locking blocks 26, grooves are formed in the movable doors 23, and the movable doors 23 are convenient to pull left and right.
The working principle of the aviation material test box provided by the utility model is as follows:
A first step of: when the low-temperature test is required to be performed on the aviation material, the clamping plate 27 is taken down from the locking block 26 arranged on the front surface of the movable door 23, the movable door 23 is slid, the low-temperature test area 3 is in an open state, the motor 21 is started, the ball screw 20 is driven to rotate by the motor 21, the ball screw sleeve 22 is driven to move, the placing plate 6 connected with the ball screw sleeve 22 is driven to move, the placing plate 6 moves out of the low-temperature test area 3 and places the aviation material thereon, the motor 21 is driven to reversely rotate, the placing plate 6 moves into the low-temperature test area 3, the movable door 23 is moved to enable the low-temperature test area 3 to be in a closed state, the refrigerating plate 5 is started, and the low-temperature test can be performed on the aviation material placed on the placing plate 6.
And a second step of: when high temperature test is required to be performed on the aviation material, the movable door 16 is pulled by the third pull ring 17, the movable door 16 rotates around the rotating shaft 14, the high temperature test area 4 is in an open state, the placement box 8 is pulled out by the first pull ring 10, the cover plate 11 is taken off from the top of the placement box 8 by the second pull ring 12, the aviation material is placed in the placement box 8, then the cover plate 11 is replaced to the top of the placement box 8, the sliding bar 9 at the bottom of the placement box 8 is aligned with the sliding groove formed at the bottom of the high temperature test area 4, the placement box 8 is installed in the high temperature test area 4, then the movable door 16 is rotated to close the high temperature test area 4, the heater 7 is started, and the high temperature test can be performed on the aviation material in the placement box 8.
The standard parts used in the method can be purchased from the market, and can be customized according to the description of the specification and the drawings, the specific connection modes of the parts are conventional means such as mature bolts, rivets and welding in the prior art, the machines, the parts and the equipment are conventional models in the prior art, and the structures and the principles of the parts are all known by the skilled person through technical manuals or through conventional experimental methods.
Although embodiments of the present utility model have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations may be made therein without departing from the spirit and scope of the utility model as defined by the appended claims and their equivalents, and in other related technical fields, which are equally encompassed by the scope of the present utility model.
Claims (8)
1. An aircraft material test kit, comprising:
The device comprises a box body (1), wherein a partition board (2) is arranged in the middle of the interior of the box body (1), the partition board (2) divides the interior of the box body (1) into an upper part and a lower part, the upper end of the box body is a low-temperature test area (3), and the lower end of the box body is a high-temperature test area (4);
the low-temperature test area (3), wherein the inner walls of the two sides of the inside of the low-temperature test area (3) are provided with refrigeration plates (5), and the inside of the low-temperature test area (3) is provided with a placement plate (6);
the high-temperature test area (4), a plurality of heaters (7) are installed on the inner walls of the two sides of the inside of the high-temperature test area (4), and a placement box (8) is installed on the bottom surface of the inside of the high-temperature test area (4).
2. An aircraft material test kit according to claim 1, wherein: two sliding strips (9) are symmetrically arranged at the bottom of the placement box (8), two sliding grooves are formed in the inner bottom surface of the high-temperature test area (4), and the sliding strips (9) are arranged in the sliding grooves.
3. An aircraft material test kit according to claim 1, wherein: the front of placing case (8) is installed first pull ring (10), the top of placing case (8) sets up to open structure and installs apron (11), the lower extreme size of apron (11) is the same with the internal diameter of placing case (8), the upper end size of apron (11) is greater than the internal diameter of placing case (8), the top of apron (11) is provided with second pull ring (12).
4. An aircraft material test kit according to claim 1, wherein: fixed pipe (13) are installed in the positive left side of lower extreme of box (1), fixed pipe (13) set up to two, insert in two upper and lower fixed pipes (13) and be equipped with pivot (14), constitute between pivot (14) and two fixed pipes (13) and rotate and be connected, adapter sleeve (15) are installed in the outside of pivot (14), adapter sleeve (15) set up to two in pivot (14) symmetry, and the right side of two adapter sleeves (15) is connected with dodge gate (16), dodge gate (16) set up in the positive outside of high temperature test area (4), third pull ring (17) are installed to the positive right-hand member of dodge gate (16).
5. An aircraft material test kit according to claim 1, wherein: two placing plates (6) are arranged in the low-temperature test area (3), and the periphery of each placing plate (6) is provided with a protruding structure.
6. An aircraft material test kit according to claim 1, wherein: fixed box (18) are installed to the bottom bilateral symmetry of placing board (6), fixed plate (19) are installed in the both sides of the inside one end of low temperature test area (3) to fixed box (18), fixed plate (19) are through the inside fixed connection of gim peg and box (1), the inside of fixed box (18) is provided with ball screw (20), the rotation is constituteed with the inner wall of fixed box (18) to the left end of ball screw (20), the right-hand member of ball screw (20) extends fixed box (18) and connects on motor (21), the cover is equipped with ball silk cover (22) on ball screw (20), the top of ball silk cover (22) is with the bottom fixed connection of placing board (6), and places board (6) and does not contact with the inner wall of box (1).
7. An aircraft material test kit according to claim 1, wherein: the utility model discloses a low temperature test box, including box (1), including box, slide bar (25), slide bar (24) are installed in the front upper end of box (1), the front upper end of box (1) is provided with dodge gate (23), and spout has been seted up with the region that it is relative to on baffle (2), and the through-hole has been seted up at the both ends of spout, and the diameter of through-hole and the diameter phase-match of slide bar (24), and the size at the both ends of slide bar (24) is greater than the diameter of through-hole, slider (25) are installed at the top of dodge gate (23), the spout has been seted up at the front top of box (1), slider (25) set up in the spout, and slider (25) are T shape structure.
8. An aircraft material test kit according to claim 7, wherein: two locking pieces (26) are installed to the front upper and lower symmetry of dodge gate (23), the draw-in groove has been seted up to the top and the bottom of locking piece (26), and when two dodge gates (23) were close to each other, low temperature test area (3) were in the closed state, and two locking pieces (26) that are in same horizontal direction on two dodge gates (23) are in the same place, and cardboard (27) are installed in the front outside of two, and inboard top and the bottom of cardboard (27) all are provided with the fixture block, and the size of the draw-in groove of seting up on the locking piece (26) is the same, cardboard (27) are made for elastic material, set up flutedly on dodge gate (23).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322359442.2U CN221124379U (en) | 2023-08-30 | 2023-08-30 | Aviation material test box |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322359442.2U CN221124379U (en) | 2023-08-30 | 2023-08-30 | Aviation material test box |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN221124379U true CN221124379U (en) | 2024-06-11 |
Family
ID=91343793
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322359442.2U Active CN221124379U (en) | 2023-08-30 | 2023-08-30 | Aviation material test box |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN221124379U (en) |
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2023
- 2023-08-30 CN CN202322359442.2U patent/CN221124379U/en active Active
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