CN220626036U - Wing panel modularization strength testing device - Google Patents
Wing panel modularization strength testing device Download PDFInfo
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- CN220626036U CN220626036U CN202321884156.1U CN202321884156U CN220626036U CN 220626036 U CN220626036 U CN 220626036U CN 202321884156 U CN202321884156 U CN 202321884156U CN 220626036 U CN220626036 U CN 220626036U
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- 238000012360 testing method Methods 0.000 title claims abstract description 25
- 230000001105 regulatory effect Effects 0.000 claims abstract description 31
- 238000003825 pressing Methods 0.000 claims description 18
- 229910001369 Brass Inorganic materials 0.000 claims description 3
- 239000010951 brass Substances 0.000 claims description 3
- 208000027418 Wounds and injury Diseases 0.000 abstract description 3
- 230000006378 damage Effects 0.000 abstract description 3
- 208000014674 injury Diseases 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 101001017827 Mus musculus Leucine-rich repeat flightless-interacting protein 1 Proteins 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
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Abstract
The utility model discloses a wing panel modularization strength testing device which comprises a base, a positioning module and a loading module; the positioning module is arranged on the base, and the loading module is arranged on the positioning module; the positioning module is used for clamping the wing panel, and the loading module is used for loading different positions of the wing panel. The utility model has simple structure and low cost; the utility model realizes the accurate control of the output force of the cylinder by utilizing the secondary pressure regulating air path combined by the primary pressure regulating valve and the precise pressure regulating valve, and avoids the personal injury of equipment. The air paths of the cylinders are connected in parallel, can be controlled independently, and can load loads with different sizes to a plurality of loading points of the tested wing panel at the same time.
Description
Technical Field
The utility model relates to a modularized strength testing device for a wing panel.
Background
The main function of the aircraft's wing is to generate aerodynamic forces, to keep the aircraft stable or to generate control moments. In the maneuvering process of the aircraft, the wing panel needs to bear normal load brought by high-speed airflow, and in order to cope with the working condition, a design unit usually puts certain requirements on the strength and rigidity of the wing panel and requires corresponding tests. The test method is typically to fix the airfoil as desired, and apply a load to several points on the airfoil, respectively.
The common wing loading equipment is provided with a universal testing machine, weights and servo push rods. The universal testing machine method can only load the load with fixed size, and is not suitable for the working condition of loading the loads with different sizes at the same time. The gravity method is to directly load weight on wing surface, when the wing surface of the tested wing is small and the relative position of the loading points is close, the design of the weight is limited to avoid interference between the weights, even if the problem of weight interference is solved, the problems of inconvenient operation, high labor intensity and the like still exist for loading large load. The servo push rod is driven by electric power, and closed-loop control is formed by the built-in force sensor and the servo control system, so that the servo push rod can stably output accurate load, but the servo push rod is high in manufacturing cost and high in system complexity, and cannot meet the detection requirement of mass production.
Disclosure of Invention
In order to solve the technical problems, the utility model provides the airfoil modularized strength testing device which can load loads with different magnitudes on a plurality of loading points of the tested airfoil at the same time, and has the advantages of high load control precision, low cost and high testing efficiency.
The technical scheme adopted by the utility model is as follows: a modularized strength testing device for a wing panel comprises a base, a positioning module and a loading module; the positioning module is arranged on the base, and the loading module is arranged on the positioning module;
the positioning module comprises a positioning base and a pressing plate; a step groove is formed in one side surface of the positioning base, a pressing plate is arranged at the upper part of the step groove, and a wing panel is arranged at the lower part of the step groove; the upper side wall of the step groove is provided with a plurality of set screw holes and 2 unthreaded holes, set screws are arranged in the set screw holes, and the screws in the unthreaded holes are connected with the pressing plate;
the loading module comprises a plurality of air cylinders which are fixed on the positioning base through air cylinder seats; the piston rods of the cylinders are oriented uniformly and all face downwards for loading the fins.
Further, the rod cavity and the rodless cavity of each cylinder are respectively connected with two air outlets of the reversing valve through a pipeline, and a precise pressure regulating valve is arranged on the pipeline connected with the rodless cavity; the air inlets of the reversing valves connected with the cylinders are connected with the air outlets of the primary pressure regulating valve through pipelines, and the air inlets of the primary pressure regulating valve are sequentially connected with the slide valve and the air inlet connector through pipelines.
Further, the primary pressure regulating valve is arranged on a valve bracket, and the valve bracket is arranged on the base.
Furthermore, a positioning pin hole is processed on the bottom surface of the cylinder seat, and a positioning pin is arranged in the positioning pin hole; the positioning pin is in interference fit with the positioning pin hole, and the positioning pin is in clearance fit with a corresponding pin hole on the positioning base; the cylinder seat is fixedly arranged on the positioning base through a screw.
Furthermore, the end part of the cylinder piston rod is fixedly provided with a pressure head, and the pressure head is made of brass.
Furthermore, the pressure head is in threaded connection with a piston rod of the air cylinder, and the lower end of the pressure head is a convex spherical surface.
Further, the base comprises a rectangular section frame, a bottom plate and four supporting feet; the bottom plate is matched with the profile frame and fixedly connected with the profile frame; four corners of the bottom plate are respectively provided with a supporting foot.
Further, the device also comprises a calibration device, wherein the calibration device comprises a force sensor and a display; the force sensor is electrically connected with the display and is used for calibrating the output force of the air cylinder.
Compared with the prior art, the utility model has the beneficial effects that:
the utility model has simple structure and low cost; the utility model realizes the accurate control of the output force of the cylinder by utilizing the secondary pressure regulating air passage combined by the primary pressure regulating valve and the precise pressure regulating valve, and the exhaust speed regulating valve is used in the air passage, so that the movement speed of the piston of the cylinder can be accurately regulated, the utility model has the functions of protecting the wing panel and preventing the injury of equipment to the human body. The air paths of the cylinders are connected in parallel, can be controlled independently, and can load loads with different sizes to a plurality of loading points of the tested wing panel at the same time.
Drawings
Fig. 1 is a structural diagram of the present utility model.
Fig. 2 is a schematic diagram of a positioning module according to the present utility model.
Fig. 3 is a sectional view of a positioning die of the present utility model.
Fig. 4 is a schematic view of a step groove of a positioning module according to the present utility model.
FIG. 5 is a schematic diagram of a loading module according to the present utility model.
FIG. 6 is a schematic diagram showing the assembly relationship of the loading module according to the present utility model.
In the figure:
1-wing panel;
2-a base 201-a bottom plate 202-a section frame 203-a support leg 204-a screw hole matrix;
3-positioning module 301-positioning base 302-end positioning plate 303-screw 304-pressing plate 305-screw 306-set screw 307-screw 308-loading module positioning hole;
4-a loading module 401-a cylinder 402-a cylinder seat 403-a pressure head 405-a locating pin 406-an air inlet joint 407-a slide valve 408-a primary pressure regulating valve 409-a reversing valve 410-a precise pressure regulating valve 411-a pipeline 412-a valve group bracket 413-a pipe joint 414-a digital display precise pressure gauge 415-an air exhaust speed regulating valve 416-a check valve;
5-calibration means 501-force sensor 502-display.
Detailed Description
The utility model will be further described with reference to the accompanying drawings.
As shown in fig. 1, the utility model consists of a base 2, a positioning module 3, a loading module 4 and a calibration device 5. The positioning module 3 is arranged on the base 2, and the loading module 4 is arranged on the positioning module 3. The calibration device 5 is used for calibrating the output force of the cylinder of the loading module 4.
The base 2 is a foundation for bearing the whole device and consists of a rectangular section frame 202, a bottom plate 201 and supporting legs 203. The bottom plate 201 is matched with and fixedly connected with the profile frame 202, and four corners of the bottom plate 201 are respectively provided with a supporting foot 203. Screw hole matrixes are processed on the bottom plate 201 according to a fixing rule, the fins 1 of different models are required to be clamped by the positioning modules 3 of different sizes, and the positioning modules 3 of different sizes are fixed by using different screw holes in the matrixes. The fins 1 of various types share the basic loading module 4 and the base 1, so that the manufacturing cost can be saved
The calibrating device 5 comprises a force sensor 501 and a display 502, wherein the force sensor 501 is electrically connected with the display 502 and is used for calibrating the output force of the cylinder.
As shown in fig. 2-4, the positioning module 3 includes a positioning base 301, an end positioning plate 302, and a pressing plate 304; a step groove is formed in one side surface of the positioning base 301, a pressing plate 304 is installed on the upper portion of the step groove, and the lower portion of the step groove is used for installing the wing panel 1. One end of the step groove is provided with an end locating plate 302, and the end locating plate 302 is fixedly arranged on the locating base 301 and used for locating the end part of the wing panel 1. The upper side wall of the step groove is provided with a plurality of set screw holes and 2 unthreaded holes, set screws 306 are arranged in the set screw holes, and screws 305 in the unthreaded holes are connected with the pressing plate 304.
The length L and the width W1 of the lower part of the step groove are designed according to the test specification, and the height h1=twing+0.2 (twing is the thickness of the tested wing). Total h2=t wing+t pressure+1mm of step groove (t pressure is the thickness of the platen). The pressing plate is a rectangular steel plate with the length, width and thickness of L, W, t, and 2 threaded blind holes are processed near two ends of the pressing plate.
After the positioning base 301 is assembled with the pressing plate 304, the pressing plate 304 is limited at the upper part of the step groove by 2 screws 305, and the pressing plate 304 has an up-down movement range of 1.2 mm. When the wing panel 1 is installed, the wing root of the wing panel 1 is attached to the lower part of the step groove of the positioning base 301, and the wing panel end face is attached to the end positioning plate 302. The pressure plate 304 is pressed against the tab 1 using a set screw 306.
As shown in fig. 5-6, the loading module 4 includes a cylinder block 402, a cylinder 401, a ram 403, and a locating pin 405. The cylinder 401 is a double-acting cylinder, and the design or the type selection of the cylinder 401 is based on the following: the force of the cylinder 401 at 0.5MPa should be similar to the load value required for the test.
The cylinder 401 is fixed to the positioning base 301 by a cylinder block 402. The bottom surface of the cylinder block 402 is provided with a positioning pin hole, and a positioning pin 405 is arranged in the positioning pin hole. The locating pin 405 is in interference fit with the locating pin hole, and the locating pin 405 is in clearance fit with a corresponding pin hole on the locating base 301. The cylinder block 402 is fixedly mounted on the positioning base by means of screws. The upper part of the cylinder seat 402 is provided with a cylinder positioning hole and a counter bore for connecting with the cylinder 401. The piston rods of the cylinders 401 are oriented uniformly and all downwards for loading the airfoil 1. The end of the piston rod of the air cylinder 401 is in threaded connection with the pressing head 403, the lower end of the pressing head 403 is a convex spherical surface, and the pressing head 403 is made of brass.
The rod cavity and the rodless cavity of each cylinder 401 are respectively connected with two air outlets of a reversing valve 409 through a pipeline 411, and the reversing valve 409 controls the cylinders 401 to descend or reset. A precision pressure regulating valve 410 is arranged on the pipeline connected with the rodless cavity. The air inlets of the reversing valves 409 connected with the cylinders 401 are connected with the air outlets of the primary pressure regulating valve 408 through pipelines, and the air inlets of the primary pressure regulating valve 408 are sequentially connected with the slide valve 407 and the air inlet connector 406 through pipelines. The primary pressure regulating valve 408 is mounted on a valve bracket 412, and the valve bracket 412 is mounted on the base 2. The precise pressure regulating valve 410 is provided with a digital display precise pressure gauge 414.
The slide valve 407 is an air source main valve of the testing device, and can also be used as an emergency stop switch, so that personal injury of equipment is avoided. The precise pressure regulating valve 410 and the digital display precise pressure gauge 414 have a precise pressure regulating function and a precise air pressure display, and can regulate, stabilize and display the air pressure of the cylinder 401 during the descending process, so that the cylinder 401 keeps stable output.
In use, compressed gas enters through the inlet connector 406, then enters the cylinder 401 after being depressurized and regulated through the slide valve 407 and the primary pressure regulating valves 408 and 410, and drives the cylinder piston to downwards apply load to the airfoil surface or drives the cylinder to upwards return to the preparation position. In the utility model, a set of measuring device can prepare a plurality of loading modules 4 and assemble cylinders 401 of different types, and a user can select a proper loading module 4 for testing according to the actual testing requirement of the tested wing panel 1.
The application method of the utility model is as follows:
1. the check device confirms that the spool 407 is in the closed state and that the reversing valve 409 is in the up position.
2. The clean and stable air source is connected into the air inlet joint 406, and the air pressure of the air source is kept to be 1-1.5 MPa; the slide valve 407 is opened, the reversing valve 409 is shifted, the cylinder 401 is kept still in a descending mode, the primary pressure regulating valve 408 is regulated to a set pressure, and meanwhile, the gas path is checked to confirm that no obvious gas leakage exists.
3. After the calibration instrument 5 is powered on and preheated for 10 minutes, the sensor 501 is placed directly under the cylinder, the sensor is kept substantially coaxial with the cylinder 401, the force reading of the display 502 is read, and the precision pressure regulating valve 410 is adjusted according to the reading so that the force reading of the display 502 is in a specified range.
4. After sequentially calibrating the output forces of all the cylinders 401 one by one, the calibration apparatus 5 is withdrawn.
5. The fin 1 to be tested is arranged at the corresponding position of the positioning module 3, and the fastening screw 306 is screwed to tightly press the fin.
6. The reversing valve 409 is shifted, the piston rod of the air cylinder 401 descends to press the pressure head 403 on the corresponding load point of the wing, and the load deformation of the detected wing 1 is measured.
7. The reversing valve 409 is shifted, the piston rod of the cylinder 401 moves upward, and the residual deformation of the tested fin 1 is measured.
8. Unscrewing the screw 306 removes the flap 1 under test.
9. Repeating the above steps or ending the test.
Claims (8)
1. A kind of fin modularization strength testing device, characterized by: the device comprises a base, a positioning module and a loading module; the positioning module is arranged on the base, and the loading module is arranged on the positioning module;
the positioning module comprises a positioning base and a pressing plate; a step groove is formed in one side surface of the positioning base, a pressing plate is arranged at the upper part of the step groove, and a wing panel is arranged at the lower part of the step groove; the upper side wall of the step groove is provided with a plurality of set screw holes and 2 unthreaded holes, set screws are arranged in the set screw holes, and the screws in the unthreaded holes are connected with the pressing plate;
the loading module comprises a plurality of air cylinders which are fixed on the positioning base through air cylinder seats; the piston rods of the cylinders are oriented uniformly and all face downwards for loading the fins.
2. The airfoil modular strength testing apparatus of claim 1, wherein: the rod cavity and the rodless cavity of each cylinder are respectively connected with two air outlets of the reversing valve through a pipeline, and a precise pressure regulating valve is arranged on the pipeline connected with the rodless cavity; the air inlets of the reversing valves connected with the cylinders are connected with the air outlets of the primary pressure regulating valve through pipelines, and the air inlets of the primary pressure regulating valve are sequentially connected with the slide valve and the air inlet connector through pipelines.
3. The airfoil modular strength testing apparatus of claim 2, wherein: the primary pressure regulating valve is arranged on the valve bracket, and the valve bracket is arranged on the base.
4. The airfoil modular strength testing apparatus of claim 1, wherein: a positioning pin hole is processed on the bottom surface of the cylinder seat, and a positioning pin is arranged in the positioning pin hole; the positioning pin is in interference fit with the positioning pin hole, and the positioning pin is in clearance fit with a corresponding pin hole on the positioning base; the cylinder seat is fixedly arranged on the positioning base through a screw.
5. The airfoil modular strength testing apparatus of claim 1, wherein: the end part of the cylinder piston rod is fixedly provided with a pressure head, and the pressure head is made of brass.
6. The airfoil modular strength testing apparatus of claim 5, wherein: the pressure head is in threaded connection with the piston rod of the air cylinder, and the lower end of the pressure head is a convex spherical surface.
7. The airfoil modular strength testing apparatus of claim 1, wherein: the base comprises a rectangular section frame, a bottom plate and four supporting feet; the bottom plate is matched with the profile frame and fixedly connected with the profile frame; four corners of the bottom plate are respectively provided with a supporting foot.
8. The airfoil modular strength testing apparatus of claim 1, wherein: the device also comprises a calibration device, wherein the calibration device comprises a force sensor and a display; the force sensor is electrically connected with the display and is used for calibrating the output force of the air cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321884156.1U CN220626036U (en) | 2023-07-18 | 2023-07-18 | Wing panel modularization strength testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202321884156.1U CN220626036U (en) | 2023-07-18 | 2023-07-18 | Wing panel modularization strength testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220626036U true CN220626036U (en) | 2024-03-19 |
Family
ID=90218158
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202321884156.1U Active CN220626036U (en) | 2023-07-18 | 2023-07-18 | Wing panel modularization strength testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220626036U (en) |
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2023
- 2023-07-18 CN CN202321884156.1U patent/CN220626036U/en active Active
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