CN219416625U - Rigidity detection equipment of aircraft wing - Google Patents
Rigidity detection equipment of aircraft wing Download PDFInfo
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- CN219416625U CN219416625U CN202320385786.8U CN202320385786U CN219416625U CN 219416625 U CN219416625 U CN 219416625U CN 202320385786 U CN202320385786 U CN 202320385786U CN 219416625 U CN219416625 U CN 219416625U
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- aircraft wing
- movable plate
- tension sensor
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Abstract
The utility model relates to the technical field of wing rigidity detection, in particular to rigidity detection equipment for an aircraft wing, which comprises a placing plate, wherein two fixing frames are symmetrically arranged on the upper surface of the placing plate, mounting plates are respectively fixed on the upper surfaces of the two fixing frames, two hydraulic cylinders are symmetrically arranged at the lower ends of the mounting plates, the output ends of the two hydraulic cylinders are respectively connected with a tension sensor, a clamping piece is arranged on the lower surface of the tension sensor, a double-shaft motor is arranged in the clamping piece, an output shaft of the double-shaft motor is connected with a screw rod, a movable plate is connected on the outer wall of the screw rod, and a guide rod is arranged on one side of the movable plate. According to the utility model, the clamping piece can be driven to move through the hydraulic cylinder arranged on the mounting plate, the tension of the hydraulic cylinder can be detected through the tension sensor arranged at the output end of the hydraulic cylinder, and the rigidity of the wing is obtained after calculation of the computer, so that the detection is finished, and the use of people is facilitated.
Description
Technical Field
The utility model relates to the technical field of wing rigidity detection, in particular to rigidity detection equipment for an aircraft wing.
Background
The unmanned plane is called as unmanned plane for short, and the unmanned plane is controlled by radio remote control equipment and a self-provided program control device, when the wing is in the air, lift force is provided for the plane, and in view of the fact that the wing needs to be bent up and down, the air is tilted up, and the ground is bent down, the overall structural design of the wing must meet the standard and has no abrasion, aging, fatigue and other reasons, one of the contents of structural tests is adopted, and therefore the structural test is an important means for observing and researching the strength, the rigidity, the stress and the deformation distribution condition of the aircraft structure or component under the action of static load, and the structural strength and the static analysis correctness of the aircraft are verified.
The utility model discloses a wing strength detection device for an unmanned aerial vehicle manufacturing machine, which comprises a transverse plate, wherein two supporting plates are symmetrically and fixedly connected to the upper end face of the transverse plate, a top plate is fixedly connected to the upper end faces of the two supporting plates together, two hydraulic telescopic rods are symmetrically and fixedly connected to the lower end face of the top plate, and a connecting plate is fixedly connected to the telescopic ends of each hydraulic telescopic rod. According to the utility model, through the matched arrangement of the gear motor, the worm and the worm wheel, the rotating rod can be driven to rotate, the rotating rod can drive the bidirectional threaded rod to rotate through the matched arrangement of the first gear and the second gear, the bidirectional threaded rod can drive the two clips to move relatively and clamp and limit the unmanned aerial vehicle wing, and fine adjustment can be carried out on the two clips, so that the clamping is more stable, the unmanned aerial vehicle wing is prevented from shaking, and the clamping effect is improved.
In summary, the following technical problems exist in the prior art: the existing detection equipment is inconvenient to adjust the clamping mechanism, the unstable clamping condition can occur, the wing easily shakes in the detection process, and then the clamping effect is reduced.
Disclosure of Invention
The utility model aims to provide a rigidity detection device for an aircraft wing, which is used for solving the problems in the background technology.
In order to solve the technical problems, the utility model adopts the following technical scheme:
the utility model provides a rigidity check out test set of aircraft wing, includes places the board, the upper surface symmetry of placing the board is provided with two mounts, two the upper surface of mount all is fixed with the mounting panel, two pneumatic cylinders are installed to the lower extreme symmetry of mounting panel, two the output of pneumatic cylinder all is connected with tension sensor, tension sensor's lower surface is provided with the holder, the internally mounted of holder has biax motor, the output shaft of biax motor has the lead screw, the outer wall connection of lead screw has the fly leaf, one side of fly leaf is provided with the guide bar.
Preferably, the hydraulic cylinder is connected with the mounting plate through bolts, a telescopic structure is formed between the tension sensor and the hydraulic cylinder, and the clamping piece is fixedly connected with the tension sensor.
Preferably, a rotating structure is formed between the screw rod and the double-shaft motor, the screw rod penetrates into the movable plate, and a sliding structure is formed between the movable plate and the clamping piece through the guide rod.
Preferably, the movable plate is further provided with:
the connecting block is symmetrically arranged at two ends of the movable plate, and one side of the connecting block is provided with a clamping plate.
Preferably, the connecting block is fixedly connected with the movable plate, and the clamping plate is integrally fixed with the connecting block.
Preferably, the fixing frame is further provided with:
the fixed plate, it sets up respectively two the inner wall of mount, the internally mounted of fixed plate has adjusting screw, adjusting screw's end-to-end connection has the connecting rod, the below of connecting rod is provided with the bearing, the lower extreme of bearing is connected with the limiting plate.
Preferably, the adjusting screw penetrates into the fixing plate, and the limiting plate and the adjusting screw form a rotating structure through the bearing.
The above description shows that, by the above technical solution of the present application, the technical problem to be solved by the present application can be necessarily solved.
Meanwhile, through the technical scheme, the utility model has at least the following beneficial effects:
according to the utility model, the clamping piece can be driven to move through the hydraulic cylinder arranged on the mounting plate, the tension of the hydraulic cylinder can be detected through the tension sensor arranged at the output end of the hydraulic cylinder, and the rigidity of the wing is obtained after calculation of the computer, so that the detection is finished, and the use of people is facilitated; the screw rod can be driven to rotate through the arranged double-shaft motor, and the movable plate moves under the cooperation of the guide rod, so that the clamping mechanism is adjusted, the wings with different sizes are clamped and limited conveniently, the unstable clamping condition is reduced, and the detection effect is improved;
according to the wing clamping device, the movable plate is driven to move when moving through the connecting blocks, so that the wing is clamped and limited, and subsequent detection operation is facilitated; through twisting the adjusting screw on the fixed plate, can drive limiting plate motion, limiting plate lower surface and wing upper surface contact, and under the cooperation of bearing for the connecting rod can normally carry out vertical motion, thereby promote limiting plate removal, carry out spacingly to the wing.
Drawings
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a schematic cross-sectional view of a clamping member according to the present utility model;
FIG. 3 is an enlarged schematic view of a portion of FIG. 2A in accordance with the present utility model;
fig. 4 is a schematic perspective view of a fixing plate according to the present utility model.
In the figure: 1. placing a plate; 2. a fixing frame; 3. a mounting plate; 4. a hydraulic cylinder; 5. a tension sensor; 6. a clamping member; 7. a biaxial motor; 8. a screw rod; 9. a movable plate; 10. a guide rod; 11. a connecting block; 12. a clamping plate; 13. a fixing plate; 14. adjusting a screw; 15. a connecting rod; 16. a bearing; 17. and a limiting plate.
Detailed Description
The present utility model will be described in further detail with reference to the drawings and examples, in order to make the objects, technical solutions and advantages of the present utility model more apparent. It should be understood that the specific embodiments described herein are for purposes of illustration only and are not intended to limit the scope of the utility model.
Description of the preferred embodiments
As shown in fig. 1-3, the present utility model provides a technical solution: the utility model provides a rigidity check out test set of aircraft wing, including placing board 1, the upper surface symmetry of placing board 1 is provided with two mounts 2, the upper surface of two mounts 2 all is fixed with mounting panel 3, two pneumatic cylinders 4 are installed to the lower extreme symmetry of mounting panel 3, the output of two pneumatic cylinders 4 all is connected with tension sensor 5, tension sensor 5's lower surface is provided with clamping piece 6, clamping piece 6's internally mounted has biax motor 7, biax motor 7's output shaft has lead screw 8, lead screw 8's outer wall connection has fly leaf 9, one side of fly leaf 9 is provided with guide bar 10.
Example two
The scheme in the first embodiment is further described below in conjunction with a specific working manner, and the details are described below:
as shown in fig. 1, fig. 2 and fig. 3, as a preferred embodiment, further, on the basis of the above manner, the hydraulic cylinder 4 is in bolted connection with the mounting plate 3, a telescopic structure is formed between the tension sensor 5 and the hydraulic cylinder 4, the clamping piece 6 is fixedly connected with the tension sensor 5, the clamping piece 6 can be driven to move by the hydraulic cylinder 4 arranged on the mounting plate 3, the tension of the hydraulic cylinder 4 can be detected by the tension sensor 5 arranged at the output end of the hydraulic cylinder 4, and the rigidity of the wing is obtained after calculation by a computer, so that the detection is completed, and the use of people is facilitated; the screw rod 8 and the double-shaft motor 7 form a rotating structure, the screw rod 8 penetrates into the movable plate 9, the movable plate 9 forms a sliding structure through the guide rod 10 and the clamping piece 6, the screw rod 8 can be driven to rotate through the arranged double-shaft motor 7, the movable plate 9 moves under the cooperation of the guide rod 10, the clamping mechanism is adjusted, the wings with different sizes are clamped and limited conveniently, the unstable clamping condition is reduced, and the detection effect is improved.
As shown in fig. 1, 2 and 4, as a preferred embodiment, based on the above manner, further, the connecting blocks 11 are symmetrically arranged at two ends of the movable plate 9, the connecting blocks 11 are fixedly connected with the movable plate 9, one side of each connecting block 11 is provided with a clamping plate 12, the clamping plates 12 and the connecting blocks 11 are of an integral fixed structure, and when the movable plate 9 moves through the connecting blocks 11, the clamping plates 12 are driven to move, so that the wing is clamped and limited, and subsequent detection operation is facilitated; the fixed plate 13, it sets up the inner wall at two mounts 2 respectively, the internally mounted of fixed plate 13 has adjusting screw 14, adjusting screw 14 runs through to the inside of fixed plate 13, the end-to-end connection of adjusting screw 14 has connecting rod 15, the below of connecting rod 15 is provided with bearing 16, the lower extreme of bearing 16 is connected with limiting plate 17, constitute revolution mechanic between limiting plate 17 and connecting rod 15 and the adjusting screw 14 through bearing 16, through twisting adjusting screw 14 on the fixed plate 13, can drive limiting plate 17 motion, limiting plate 17 lower surface and wing upper surface contact, and under the cooperation of bearing 16, make connecting rod 15 can normally carry out vertical motion, thereby promote limiting plate 17 and remove, carry out the spacing to the wing.
From the above, it can be seen that:
the utility model aims at the technical problems that: the existing detection equipment is inconvenient to adjust the clamping mechanism, the unstable clamping condition can occur, and the wings are easy to shake in the detection process, so that the clamping effect is reduced; the technical scheme of each embodiment is adopted. Meanwhile, the implementation process of the technical scheme is as follows:
before using this rigidity check out test set of aircraft wing, place the board 1 suitable position earlier, through the trompil on two mounts 2, pass the wing that will detect and open the trompil, place on the board 1, then twist the adjusting screw 14 rotation on the fixed plate 13, thereby drive connecting rod 15 and carry out vertical motion, make limiting plate 17 lower surface and wing upper surface contact, through constantly twisting adjusting screw 14, under the cooperation of bearing 16, make connecting rod 15 can normally carry out vertical motion, thereby promote limiting plate 17 removal, carry out spacingly to the wing, the condition that takes place the displacement when the wing detects, then through pneumatic cylinder 4 that sets up on mounting panel 3, drive clamping piece 6 and carry out vertical motion, make two sets of clamping plates 12 remove respectively to the both sides of wing, through the biax motor 7 that sets up in clamping piece 6 drive lead screw 8 rotation, under the cooperation of guide bar 10, thereby drive connecting block 11 and remove, make two sets of clamping plates 12 be close to each other, thereby carry out the centre gripping to the wing and fix, the convenience carries out regulation to this clamping mechanism, the condition that does not appear, the subsequent pneumatic cylinder 4 is gone up to the detection that the subsequent pneumatic cylinder 4 is gone up, the subsequent pneumatic cylinder 4 is passed through, the subsequent pneumatic cylinder is calculated, the completion of the situation is calculated, the subsequent pneumatic cylinder is 4 is convenient to carry out the calculation, the completion of the situation is calculated and is passed through the detection 4, and is convenient, the subsequent hydraulic cylinder is 4 is set up and is easy to be convenient to be used to carry out.
Through above-mentioned setting, this application must solve above-mentioned technical problem, simultaneously, realizes following technical effect:
according to the utility model, the clamping piece 6 can be driven to move through the hydraulic cylinder 4 arranged on the mounting plate 3, the tension of the hydraulic cylinder 4 can be detected through the tension sensor 5 arranged at the output end of the hydraulic cylinder 4, and the rigidity of the wing is obtained after calculation of the computer, so that the detection is finished, and the use of people is facilitated; the screw rod 8 can be driven to rotate through the arranged double-shaft motor 7, and the movable plate 9 moves under the cooperation of the guide rod 10, so that the clamping mechanism is adjusted, the wings with different sizes are clamped and limited conveniently, the unstable clamping condition is reduced, and the detection effect is improved;
according to the wing clamping device, through the connecting block 11, when the movable plate 9 moves, the clamping plate 12 is driven to move, so that the wing is clamped and limited, and subsequent detection operation is facilitated; through twisting adjusting screw 14 on the fixed plate 13, can drive limiting plate 17 motion, limiting plate 17 lower surface and wing upper surface contact, and under the cooperation of bearing 16 for connecting rod 15 can normally carry out vertical motion, thereby promote limiting plate 17 removal, carry out the spacing to the wing.
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 can be made therein without departing from the principles and spirit of the utility model, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. An aircraft wing stiffness detection apparatus, comprising:
place board (1), the upper surface symmetry of placing board (1) is provided with two mount (2), two the upper surface of mount (2) all is fixed with mounting panel (3), the lower extreme symmetry of mounting panel (3) installs two pneumatic cylinders (4), two the output of pneumatic cylinder (4) all is connected with tension sensor (5), the lower surface of tension sensor (5) is provided with clamping piece (6), the internally mounted of clamping piece (6) has biax motor (7), the output shaft of biax motor (7) has lead screw (8), the outer wall connection of lead screw (8) has fly leaf (9), one side of fly leaf (9) is provided with guide bar (10).
2. The device for detecting the rigidity of an aircraft wing according to claim 1, wherein the hydraulic cylinder (4) is connected with the mounting plate (3) through bolts, a telescopic structure is formed between the tension sensor (5) and the hydraulic cylinder (4), and the clamping piece (6) is fixedly connected with the tension sensor (5).
3. An aircraft wing stiffness testing device according to claim 1, characterized in that a rotating structure is formed between the screw (8) and the double-shaft motor (7), and that the screw (8) extends through the inside of the movable plate (9), and that the movable plate (9) forms a sliding structure with the clamping member (6) via the guide rod (10).
4. An aircraft wing stiffness detection device according to claim 1, characterized in that the movable plate (9) is further provided with:
the connecting blocks (11) are symmetrically arranged at two ends of the movable plate (9), and clamping plates (12) are arranged on one side of each connecting block (11).
5. The device for detecting the rigidity of an aircraft wing according to claim 4, wherein the connecting block (11) is fixedly connected with the movable plate (9), and the clamping plate (12) and the connecting block (11) are integrally fixed.
6. An aircraft wing stiffness detection device according to claim 1, wherein the mount (2) is further provided with:
fixed plate (13), it sets up respectively two the inner wall of mount (2), the internally mounted of fixed plate (13) has adjusting screw (14), the end-to-end connection of adjusting screw (14) has connecting rod (15), the below of connecting rod (15) is provided with bearing (16), the lower extreme of bearing (16) is connected with limiting plate (17).
7. The device for detecting the rigidity of an aircraft wing according to claim 6, characterized in that the adjusting screw (14) penetrates into the inside of the fixed plate (13), and the limiting plate (17) forms a rotating structure with the adjusting screw (14) through the bearing (16) and the connecting rod (15).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320385786.8U CN219416625U (en) | 2023-03-06 | 2023-03-06 | Rigidity detection equipment of aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320385786.8U CN219416625U (en) | 2023-03-06 | 2023-03-06 | Rigidity detection equipment of aircraft wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219416625U true CN219416625U (en) | 2023-07-25 |
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ID=87244116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320385786.8U Active CN219416625U (en) | 2023-03-06 | 2023-03-06 | Rigidity detection equipment of aircraft wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219416625U (en) |
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2023
- 2023-03-06 CN CN202320385786.8U patent/CN219416625U/en active Active
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