CN117451518A - Aircraft panel structural strength verifying attachment - Google Patents
Aircraft panel structural strength verifying attachment Download PDFInfo
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- CN117451518A CN117451518A CN202210841071.9A CN202210841071A CN117451518A CN 117451518 A CN117451518 A CN 117451518A CN 202210841071 A CN202210841071 A CN 202210841071A CN 117451518 A CN117451518 A CN 117451518A
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- panel structural
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- 238000007689 inspection Methods 0.000 claims abstract description 47
- 238000012360 testing method Methods 0.000 claims abstract description 34
- 230000005540 biological transmission Effects 0.000 claims description 12
- 238000000034 method Methods 0.000 abstract description 7
- 230000008569 process Effects 0.000 abstract description 7
- 238000012545 processing Methods 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 11
- 230000000694 effects Effects 0.000 description 8
- 230000007246 mechanism Effects 0.000 description 3
- 239000004576 sand Substances 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/08—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
- G01N3/10—Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces generated by pneumatic or hydraulic pressure
- G01N3/12—Pressure testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N3/00—Investigating strength properties of solid materials by application of mechanical stress
- G01N3/02—Details
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- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses an aircraft panel structural strength inspection device, and relates to the technical field of aircraft panel processing. The invention comprises a test bench, wherein a plurality of first sliding grooves are formed in the upper surface of the test bench, a first screw rod is arranged in the first sliding grooves, two sliding blocks are arranged on the first screw rod, a limiting frame is fixed on the upper surface of the sliding blocks, an air cylinder is arranged on the upper surface of the inside of the limiting frame, a clamping block is connected to the telescopic end of the air cylinder, the two sides of an aircraft wallboard are conveniently limited and fixed, the stability of the aircraft wallboard in the test process is ensured, second sliding grooves are formed in the front side and the rear side of the upper surface of the test bench, a second screw rod is arranged in the second sliding grooves, a U-shaped frame is arranged between the two second screw rods, a third screw rod is arranged in the U-shaped frame, a movable block is arranged on the third screw rod, a hydraulic cylinder is arranged on the lower surface of the movable block, a pressure sensor is connected to the output end of the hydraulic cylinder, and the lower side of the pressure sensor is connected with a pressure head, so that the different positions of the aircraft wallboard are conveniently tested, and the accuracy of test data is ensured.
Description
Technical Field
The invention belongs to the technical field of aircraft panel processing, and particularly relates to an aircraft panel structural strength inspection device.
Background
The aircraft panel is generally a curved thin-walled part, and strength inspection is required after the aircraft panel is processed, so that the later-stage use safety is ensured.
At present, the fixed effect of current aircraft wallboard when carrying out intensity inspection is not good, and the aircraft wallboard is receiving the pressure effect, takes place the slip skew easily, influences the test result, and most verifying attachment are inconvenient for carrying out the inspection to the different positions of aircraft wallboard simultaneously, lead to the inspection data not accurate enough, influence the accuracy of inspection. In this regard, we have devised an aircraft panel structural strength inspection apparatus to address the above-mentioned issues.
Disclosure of Invention
In order to solve the technical problems, the invention is realized by the following technical scheme:
the invention relates to an aircraft panel structural strength inspection device which comprises an inspection table and a conveying frame, wherein a plurality of conveying frames are arranged on the upper surface of the inspection table along the horizontal direction, a plurality of first sliding grooves are formed in the upper surface of the inspection table, first screw rods are arranged in the first sliding grooves, two sliding blocks are in threaded fit on the first screw rods, a limiting frame is fixed on the upper surface of each sliding block, an air cylinder is mounted on the upper surface of the inner part of each limiting frame, a clamping block is connected to the telescopic end of each air cylinder, second sliding grooves are formed in the front side and the rear side of the upper surface of the inspection table, a second screw rod is arranged in each second sliding groove, a U-shaped frame is arranged between the two second screw rods, through grooves are formed in the upper surface of each U-shaped frame, a third screw rod is arranged in each through groove, movable blocks are in threaded fit on the upper surfaces of the third screw rods, a hydraulic cylinder is mounted on the lower surface of each movable block, and the lower side of each hydraulic cylinder is connected to a pressure sensor.
Through the pneumatic cylinder drives the reciprocates of pressure head, exert pressure to the aircraft wallboard, carry out intensity inspection, combine pressure sensor, be convenient for monitor the condition of exerting pressure, make things convenient for staff's looking into and record, the carriage is convenient for wait to examine the getting of aircraft wallboard and put, first lead screw and the screw-thread fit of slider, be convenient for adjust two sliders each other and be close to or keep away from, and then drive the removal of the spacing of front and back both sides, carry out spacing clamp to aircraft wallboard both sides, combine the cylinder to adjust the fixture block to press in aircraft wallboard border department simultaneously, further compress tightly fixedly to the aircraft wallboard, the steadiness of aircraft wallboard has been guaranteed, prevent that the slip skew from appearing in the inspection process, influence the inspection result, wherein the back-and-forth movement of movable block is convenient for adjusting to the third lead screw, and then drive the back-and-forth movement of pressure head, combine the second lead screw to be convenient for adjust the left-and-right movement of U type frame, and then drive the left-and-right movement of pressure head, adapt to the intensity inspection of aircraft wallboard different positions, be convenient for obtain multiunit data, the accuracy of inspection data has been improved.
Preferably, the movable groove has been seted up to logical groove rear side, the third lead screw rear end extends to inside the movable groove, is connected with driven gear, driven gear right side meshing has the driving gear, the inside gag lever post that is provided with of driving gear, just the gag lever post surface is provided with a plurality of sand grips, mutually support with the driving gear, through gag lever post and sand grip mutually support, be convenient for carry out spacingly to U type frame, ensured the stability that the U type frame moved about along the horizontal direction, gag lever post and sand grip combined action simultaneously is convenient for drive the driving gear and rotates, combines the meshing effect of driving gear and driven gear, and then drives the rotation of third lead screw, realizes adjusting the purpose that the pressure head reciprocated.
Preferably, the conveying frame comprises a conveying roller and fixing plates, wherein a plurality of fixing plates are oppositely arranged on the front side and the rear side of the upper surface of the inspection table, and the front end and the rear end of the conveying roller are respectively in running fit with the front fixing plate and the rear fixing plate.
Preferably, the lower part of the limit frame and the inner side of the clamping block are both of an inclined structure, and the right side of the upper surface of the inspection bench is fixedly provided with a limit baffle plate.
Preferably, the strip groove has been seted up to the checkout stand upper surface, the strip inslot portion is provided with a plurality of dwells, the dwang rear end passes the strip inslot wall, is connected with first lead screw front end, be provided with first belt pulley on the dwang, surface mounting has first motor under the checkout stand, first motor output is connected with the axis of rotation, be provided with a plurality of second belt pulleys in the axis of rotation, first belt pulley and second belt pulley one-to-one, mutually support, and a plurality of the second belt pulley is provided with first belt with the transmission between the first belt pulley of left and right sides respectively, through the transmission cooperation of first belt pulley and second belt pulley, combines first motor, is convenient for drive the rotation of first lead screw, realizes adjusting the relative movement of spacing, makes things convenient for the fixed of aircraft wallboard and gets to put.
Preferably, a fixed block is fixed on the front side of the lower surface of the inspection bench, and the front end of the rotating shaft is connected with the fixed block.
Preferably, the right ends of the second screw rods penetrate through the right surface of the inspection bench, a third belt pulley is connected, a second belt is arranged between the front belt pulley and the rear belt pulley in a transmission mode, the right end of the central shaft of the third belt pulley is connected with a second motor, and the purpose of adjusting left-right movement of the U-shaped frame is achieved by combining the transmission effect of the second belt and the rotation of the second screw rods through the combination of the second motor.
Preferably, two support plates are oppositely arranged on the rear side of the upper surface of the inspection bench, the left end of the limiting rod is in running fit with the left support plate, the right end of the limiting rod penetrates through the right support plate and is connected with a third motor, the limiting rod is conveniently driven to rotate through the third motor, and the purpose of adjusting the pressure head to move back and forth is achieved.
Preferably, the lower surface of the inspection bench is provided with a supporting chassis, and the lower surface of the first motor is in contact with the supporting chassis.
The invention has the following beneficial effects:
1. according to the invention, the hydraulic cylinder drives the pressure head to move up and down to press the aircraft wall plate, the strength test is carried out, the pressure sensor is combined, the pressure condition is convenient to monitor, the observation and recording of workers are convenient, the conveying frame is convenient for taking and placing the aircraft wall plate to be tested, the first screw rod is matched with the screw threads of the sliding blocks, the two sliding blocks are convenient to adjust to be close to or far away from each other, the limiting frames on the front side and the rear side are driven to move, the two sides of the aircraft wall plate are limited and clamped, meanwhile, the air cylinder is combined to adjust the clamping blocks to press the edge of the aircraft wall plate, the aircraft wall plate is further pressed and fixed, the stability of the aircraft wall plate is ensured, the sliding deviation in the test process is prevented, the test result is influenced, the third screw rod is convenient to adjust the front and rear movement of the movable block, the front and rear movement of the pressure head is driven, the U-shaped frame is convenient to adjust to move left and right by combining the second screw rod, the pressure head is further driven to move left and right, the strength test of different positions of the aircraft wall plate is convenient to obtain multiple groups of data, and the accuracy of test data is improved.
2. According to the invention, the limiting rod and the convex strips are mutually matched, so that the U-shaped frame is conveniently limited, the stability of the U-shaped frame moving left and right along the horizontal direction is ensured, meanwhile, the limiting rod and the convex strips are jointly acted, so that the driving gear is conveniently driven to rotate, the meshing action of the driving gear and the driven gear is combined, the third screw rod is further driven to rotate, and the purpose of adjusting the press head to move forwards and backwards is realized.
3. According to the invention, through the lower part of the limiting frame and the inclined structure at the inner side of the clamping block, the fixing effect of the aircraft wall plate is improved by being conveniently matched with the aircraft wall plate, wherein the limiting baffle limits the right end of the aircraft wall plate, and the stability of the aircraft wall plate is further ensured.
Of course, it is not necessary for any one product to practice the invention to achieve all of the advantages set forth above at the same time.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a front view of the present invention;
FIG. 3 is a schematic view of the structure of section A-A of FIG. 2;
FIG. 4 is an enlarged schematic view of the structure shown at B in FIG. 3;
FIG. 5 is a schematic view of the structure of section C-C in FIG. 2;
FIG. 6 is a top view of the present invention;
FIG. 7 is a schematic view of the structure of section D-D in FIG. 6;
FIG. 8 is a schematic diagram of the structure of the present invention;
fig. 9 is an enlarged schematic view of the structure at E in fig. 8.
In the drawings, the list of components represented by the various numbers is as follows:
1. a test bench; 2. a carriage; 3. a first chute; 4. a first screw rod; 5. a slide block; 6. a limiting frame; 7. a clamping block; 8. a cylinder; 9. a second chute; 10. a second screw rod; 11. a U-shaped frame; 12. a third screw rod; 13. a driven gear; 14. a drive gear; 15. a limit rod; 16. a convex strip; 17. a movable block; 18. a hydraulic cylinder; 19. a pressure sensor; 20. a pressure head; 21. a limit baffle; 22. a first pulley; 23. a second pulley; 24. a first belt; 25. a first motor; 26. a third pulley; 27. a second belt; 28. a second motor; 29. a support plate; 30. a third motor; 31. and a supporting chassis.
Detailed Description
The following description of the embodiments of the present invention 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 invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present invention, it should be understood that the terms "upper," "middle," "outer," "inner," and the like indicate an orientation or a positional relationship, and are merely for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the components or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Referring to fig. 1-9, the invention discloses an aircraft panel structural strength testing device, which comprises a testing table 1 and a conveying frame 2, wherein a plurality of conveying frames 2 are arranged on the upper surface of the testing table 1 along the horizontal direction, a plurality of first sliding grooves 3 are formed in the upper surface of the testing table 1, a first lead screw 4 is arranged in the first sliding groove 3, two sliding blocks 5 are in threaded fit with the first lead screw 4, a limiting frame 6 is fixed on the upper surface of the sliding blocks 5, an air cylinder 8 is arranged on the upper surface of the limiting frame 6, a clamping block 7 is connected to the telescopic end of the air cylinder 8, second sliding grooves 9 are formed in the front side and the rear side of the upper surface of the testing table 1, a second lead screw 10 is arranged in the second sliding groove 9, a U-shaped frame 11 is arranged between the two second lead screws 10, a through groove is formed in the upper surface of the U-shaped frame 11, a third lead screw 12 is arranged in the through groove, a movable block 17 is in threaded fit with the upper surface of the third lead screw 12, a hydraulic cylinder 18 is arranged on the lower surface of the movable block 17, a pressure sensor 19 is connected to the output end of the hydraulic cylinder 18, and a pressure head 20 is connected to the lower side of the pressure sensor 19.
The hydraulic cylinder 18 drives the pressing head 20 to move up and down to press the aircraft wall plate, strength inspection is carried out, the pressure sensor 19 is combined, the pressure condition is monitored conveniently, the observation and recording of staff are facilitated, the conveying frame 2 is convenient for the taking and placing of the aircraft wall plate to be inspected, the first screw rod 4 is matched with the screw threads of the sliding blocks 5, the two sliding blocks 5 are convenient to adjust to be close to or far away from each other, the limiting frames 6 on the front side and the rear side are driven to move, the two sides of the aircraft wall plate are limited and clamped, meanwhile, the clamping blocks 7 are combined with the air cylinder 8 to be adjusted to be pressed at the edge of the aircraft wall plate, the aircraft wall plate is further pressed and fixed, the stability of the aircraft wall plate is guaranteed, the sliding offset in the inspection process is prevented, the inspection result is influenced, the third screw rod 12 is convenient to adjust the front and rear movement of the movable block 17, the front and rear movement of the pressing head 20 is driven, the U-shaped frame 11 is convenient to adjust in combination with the second screw rod 10 to move left and right, the left and right movement of the pressing head 20 is further driven to move left and right, the strength inspection of the aircraft wall plate at different positions is convenient to obtain multiple groups of data, and accuracy of inspection data is improved.
The lower part of the limiting frame 6 and the inner side of the clamping block 7 are of inclined structures, the limiting baffle 21 is fixed on the right side of the upper surface of the inspection bench 1, and the limiting baffle 21 is convenient to be matched with an aircraft wallboard through the inclined structures of the lower part of the limiting frame 6 and the inner side of the clamping block 7, so that the fixing effect of the aircraft wallboard is improved, the limiting baffle 21 limits the right end of the aircraft wallboard, and the stability of the aircraft wallboard is further guaranteed.
The movable groove is formed in the rear side of the through groove, the rear end of the third screw rod 12 extends into the movable groove, the driven gear 13 is connected, the driving gear 14 is meshed on the right side of the driven gear 13, the limiting rod 15 is arranged in the driving gear 14, a plurality of raised strips 16 are arranged on the outer surface of the limiting rod 15 and are matched with the driving gear 14, two supporting plates 29 are oppositely arranged on the rear side of the upper surface of the inspection bench 1, the left end of the limiting rod 15 is in rotary fit with the left supporting plate 29, the right end of the limiting rod 15 penetrates through the right supporting plate 29, a third motor 30 is connected, the U-shaped frame 11 is conveniently limited through the mutual fit of the limiting rod 15 and the raised strips 16, the stability of the U-shaped frame 11 moving left and right along the horizontal direction is ensured, meanwhile, the limiting rod 15 and the raised strips 16 are jointly acted, the driving gear 14 is conveniently driven to rotate, the meshing effect of the driving gear 14 and the driven gear 13 is combined, the rotation of the third screw rod 12 is further driven, the purpose of adjusting the front and back movement of the pressure head 20 is achieved, the third motor 30 is conveniently driving the rotation of the limiting rod 15, the purpose of the front and back movement of the adjusting the pressure head 20 is achieved, and the stability of the limiting rod 15 is guaranteed, and the supporting plate 29 is guaranteed.
The strip-shaped groove is formed in the upper surface of the inspection bench 1, a plurality of rotating rods are arranged in the strip-shaped groove, the rear ends of the rotating rods penetrate through the inner wall of the strip-shaped groove and are connected with the front end of the first screw rod 4, a first belt pulley 22 is arranged on the rotating rods, the lower surface of the inspection bench 1 is provided with a first motor 25, the output end of the first motor 25 is connected with a rotating shaft, a plurality of second belt pulleys 23 are arranged on the rotating shaft, the first belt pulleys 22 and the second belt pulleys 23 are in one-to-one correspondence, the second belt pulleys 23 are mutually matched with each other, a first belt 24 is arranged between the plurality of second belt pulleys 23 and the first belt pulleys 22 on the left side and the right side in a transmission mode, a fixed block is fixed on the front side of the lower surface of the inspection bench 1, the front end of the rotating shaft is connected with the fixed block, a supporting underframe 31 is arranged on the lower surface of the inspection bench 1, the lower surface of the first motor 25 is in contact with the supporting underframe 31, the first belt 24 is matched with the transmission of the first belt pulley 22 and the second belt pulley 23, the first motor 25 is combined with the rotation of the first belt pulley 4, the first belt 23 is convenient to drive the rotation of the first screw rod 4, the relative movement of the adjusting limiting frame 6 is realized, the fixing and the panel is convenient, the fixing and the panel are placed.
The conveying frame 2 comprises a conveying roller and fixing plates, wherein a plurality of fixing plates are oppositely arranged on the front side and the rear side of the upper surface of the inspection bench 1, the front end and the rear end of the conveying roller are respectively in running fit with the front fixing plate and the rear fixing plate, and the plane wallboard is convenient to push left and right through the running fit of the conveying roller and the fixing plates.
The right ends of the two second screw rods 10 penetrate through the right surface of the inspection bench 1 and are connected with a third belt pulley 26, a second belt 27 is arranged between the front third belt pulley 26 and the rear third belt pulley 26 in a transmission mode, the right end of the central shaft of the rear third belt pulley 26 is connected with a second motor 28, and the purpose of adjusting the left-right movement of the U-shaped frame 11 is achieved by combining the transmission effect of the second belt 27 and the rotation of the second screw rods 10 through the combination of the second motor 28.
Embodiment one: when the invention is used, firstly, the air cylinder 8, the hydraulic cylinder 18, the pressure sensor 19, the first motor 25, the second motor 28 and the third motor 30 are all connected with an external control mechanism and a display, and meanwhile, the aircraft panel to be inspected is placed on the conveying frame 2, and under the action of the conveying frame 2, the aircraft panel is pushed to the right side until the right end of the aircraft panel is propped against the limit baffle 21;
at this time, the first motor 25 is driven to operate by the external control mechanism, the second belt pulley 23 is driven to rotate under the action of the rotating shaft, the first belt pulley 22 is driven to rotate under the transmission action of the first belt 24, the first screw rod 4 is driven to rotate by the rotating rod in the first belt pulley 22, the two sliding blocks 5 are adjusted to be close to each other under the threaded fit of the first screw rod 4 and the sliding blocks 5, and then the limiting frames 6 on two sides are driven to move towards the direction close to the aircraft wallboard until the inclined surfaces on the lower part of the limiting frames 6 are contacted with the lower surface of the aircraft wallboard, limiting clamping is carried out on two sides of the aircraft wallboard, meanwhile, the air cylinder 8 is started, the clamping block 7 is driven to move downwards under the action of the air cylinder 8 to clamp and fix the aircraft wallboard, the stability of the aircraft wallboard is guaranteed, the aircraft wallboard is effectively prevented from sliding and shifting during the pressing process, and the accuracy of inspection data is affected;
when the strength test is carried out, the second motor 28 is started, and under the transmission action of the second belt 27 and the third belt pulley 26, the front and rear second screw rods 10 are driven to rotate simultaneously, so that the U-shaped frame 11 is driven to move leftwards, and the pressure head 20 is driven to move to the position right above the aircraft wall plate;
the limiting rod 15 effectively limits the movement of the U-shaped frame 11, so that the stability of the U-shaped frame 11 in the moving process is ensured, and the limiting rod 15, the raised strips 16 and the U-shaped frame 11 are in rotary fit through bearings;
simultaneously, the third motor 30 is driven, the limiting rod 15 and the raised strips 16 are driven to rotate relative to the U-shaped frame 11 under the action of the bearing, the driving gear 14 is driven to rotate, the meshing action of the driving gear 14 and the driven gear 13 is combined, the third screw rod 12 is driven to rotate, the movable block 17 is driven to move to a proper position forwards and backwards through the third screw rod 12, the hydraulic cylinder 18 is started to drive the pressure head 20 to move downwards to be in contact with the aircraft wall plate, the hydraulic cylinder 18 continuously applies pressure, the pressure sensor 19 monitors the pressure in real time, and pressure data are transmitted to an external display, so that the observation and recording of workers are facilitated;
after the inspection is finished, the driving cylinder 8 is contracted to drive the clamping block 7 to separate from the edge of the aircraft panel, meanwhile, the first motor 25 is reversed to drive the limiting frame 6 to move in the direction away from the aircraft panel, and finally the aircraft panel is pulled to the left side and moved out of the inspection bench 1.
According to the invention, the left-right movement of the U-shaped frame 11 is regulated through the second screw rod 10, meanwhile, the limit rod 15 is matched with the raised strips 16 to drive the driving gear 14 to rotate, and the left-right and front-back movement of the pressure head 20 is regulated through the meshing action of the driving gear 14 and the driven gear 13 and the action of the third screw rod 12, so that the strength test of different aircraft panel positions is adapted, a plurality of groups of test data are conveniently obtained, and the accuracy of the test data is improved;
the first sliding groove 3 and the inner walls of the two sides of the through groove are provided with limiting grooves, and the two sides of the sliding block 5 and the movable block 17 are connected with limiting blocks which are matched with the limiting grooves, so that the stability of the sliding block 5 and the movable block 17 in the front-back sliding process is ensured.
It should be further noted that, in the present invention, the cylinder 8, the hydraulic cylinder 18, the pressure sensor 19, the first motor 25, the second motor 28 and the third motor 30 are all connected with an external control mechanism and a display, so as to facilitate the operation and use of a worker, wherein the display is convenient for displaying the monitoring data of the pressure sensor 19, so as to facilitate the viewing and recording of the worker, and the above components are purchased in the market, and can be installed and used by a person skilled in the art according to the requirements.
In the description of the present specification, the descriptions of the terms "one embodiment," "example," "specific example," and the like, mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
The preferred embodiments of the invention disclosed above are intended only to assist in the explanation of the invention. The preferred embodiments are not exhaustive or to limit the invention to the precise form disclosed. Obviously, many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention. The invention is limited only by the claims and the full scope and equivalents thereof.
Claims (9)
1. The utility model provides an aircraft wallboard structural strength verifying attachment, includes inspection bench (1) and carriage (2), a plurality of carriage (2) set up at inspection bench (1) upper surface along the horizontal direction, a serial communication port, a plurality of first spouts (3) have been seted up to inspection bench (1) upper surface, first spout (3) inside are provided with first lead screw (4), screw thread fit has two slider (5) on first lead screw (4), fixed surface has spacing frame (6) on slider (5), surface mounting has cylinder (8) on spacing frame (6) inside, cylinder (8) flexible end is connected with fixture block (7), second spout (9) have all been seted up on inspection bench (1) upper surface front and back both sides, second spout (9) inside are provided with second lead screw (10), two be provided with U type frame (11) between second lead screw (10), U type frame (11) upper surface sets up logical groove, logical inslot portion is provided with third (12), third lead screw (12) upper surface fit has hydraulic pressure sensor (17) on the upper surface of third lead screw (12) flexible end is connected with hydraulic pressure sensor (17), the lower side of the pressure sensor (19) is connected with a pressure head (20).
2. The aircraft panel structural strength testing device according to claim 1, wherein a movable groove is formed in the rear side of the through groove, the rear end of the third screw rod (12) extends into the movable groove and is connected with a driven gear (13), a driving gear (14) is meshed on the right side of the driven gear (13), a limiting rod (15) is arranged in the driving gear (14), and a plurality of raised strips (16) are arranged on the outer surface of the limiting rod (15) and are mutually matched with the driving gear (14).
3. The aircraft panel structural strength testing device according to claim 2, wherein the conveying frame (2) comprises a conveying roller and fixing plates, the fixing plates are oppositely arranged on the front side and the rear side of the upper surface of the testing table (1), and the front end and the rear end of the conveying roller are respectively in running fit with the front fixing plate and the rear fixing plate.
4. An aircraft panel structural strength testing device according to claim 3, wherein the lower part of the limiting frame (6) and the inner side of the clamping block (7) are both of an inclined structure, and a limiting baffle (21) is fixed on the right side of the upper surface of the testing table (1).
5. The aircraft panel structural strength inspection device according to claim 4, wherein a strip-shaped groove is formed in the upper surface of the inspection bench (1), a plurality of rotating rods are arranged in the strip-shaped groove, the rear ends of the rotating rods penetrate through the inner wall of the strip-shaped groove and are connected with the front end of the first screw rod (4), first belt pulleys (22) are arranged on the rotating rods, a first motor (25) is mounted on the lower surface of the inspection bench (1), the output end of the first motor (25) is connected with a rotating shaft, a plurality of second belt pulleys (23) are arranged on the rotating shaft, the first belt pulleys (22) are in one-to-one correspondence with the second belt pulleys (23), and a plurality of second belt pulleys (23) are respectively in transmission with first belt pulleys (22) on the left side and the right side.
6. The aircraft panel structural strength testing device according to claim 5, wherein a fixed block is fixed to the front side of the lower surface of the test bench (1), and the front end of the rotating shaft is connected to the fixed block.
7. The aircraft panel structural strength testing device according to claim 6, wherein the right ends of the two second screw rods (10) penetrate through the right surface of the testing table (1), a third belt pulley (26) is connected, a second belt (27) is arranged between the front belt pulley and the rear belt pulley (26) in a transmission manner, and the right end of the central shaft of the third belt pulley (26) on the rear side is connected with a second motor (28).
8. The aircraft panel structural strength testing device according to claim 7, wherein two supporting plates (29) are oppositely arranged on the rear side of the upper surface of the testing table (1), the left end of the limiting rod (15) is in running fit with the left supporting plate (29), and the right end of the limiting rod (15) penetrates through the right supporting plate (29) and is connected with a third motor (30).
9. An aircraft panel structural strength testing device according to claim 8, wherein the lower surface of the test bench (1) is provided with a support chassis (31), and the lower surface of the first motor (25) is in contact with the support chassis (31).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210841071.9A CN117451518A (en) | 2022-07-18 | 2022-07-18 | Aircraft panel structural strength verifying attachment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210841071.9A CN117451518A (en) | 2022-07-18 | 2022-07-18 | Aircraft panel structural strength verifying attachment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117451518A true CN117451518A (en) | 2024-01-26 |
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ID=89586060
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210841071.9A Pending CN117451518A (en) | 2022-07-18 | 2022-07-18 | Aircraft panel structural strength verifying attachment |
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| Country | Link |
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| CN (1) | CN117451518A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118583672A (en) * | 2024-08-07 | 2024-09-03 | 陕西陕飞锐方航空装饰有限公司 | A strength testing device for manufacturing aircraft aviation accessories |
| CN119290590A (en) * | 2024-12-10 | 2025-01-10 | 西安驰达飞机零部件制造股份有限公司 | An inspection mechanism for wing ribbed wall panels |
-
2022
- 2022-07-18 CN CN202210841071.9A patent/CN117451518A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118583672A (en) * | 2024-08-07 | 2024-09-03 | 陕西陕飞锐方航空装饰有限公司 | A strength testing device for manufacturing aircraft aviation accessories |
| CN119290590A (en) * | 2024-12-10 | 2025-01-10 | 西安驰达飞机零部件制造股份有限公司 | An inspection mechanism for wing ribbed wall panels |
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