CN220437715U - Three-component balance module - Google Patents
Three-component balance module Download PDFInfo
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- CN220437715U CN220437715U CN202322113723.XU CN202322113723U CN220437715U CN 220437715 U CN220437715 U CN 220437715U CN 202322113723 U CN202322113723 U CN 202322113723U CN 220437715 U CN220437715 U CN 220437715U
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- bottom plate
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- wing
- resistance
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- 230000000149 penetrating effect Effects 0.000 claims description 5
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 230000006978 adaptation Effects 0.000 claims description 2
- 238000002474 experimental method Methods 0.000 abstract description 11
- 238000000429 assembly Methods 0.000 abstract description 9
- 230000000712 assembly Effects 0.000 abstract description 9
- 238000001514 detection method Methods 0.000 abstract description 6
- 230000009286 beneficial effect Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model relates to the technical field of wing aerodynamic experimental devices, in particular to a three-component balance module. The device comprises a base plate, three universal joints which are arranged in a triangular array are fixedly arranged on one side of the base plate, one force measuring plate is fixedly arranged at the other ends of the three universal joints, an angle calibration assembly is fixedly arranged on the force measuring plate and located between the three universal joints, two lift force sensing assemblies are fixedly arranged on the base plate, a resistance sensing assembly is fixedly arranged on the base plate, the lift force sensing assemblies and the resistance sensing assemblies are matched with the force measuring plate, and one resistance spring is arranged between the base plate and the force measuring plate. Through simple wing three component comprehensive detection structure to can effectively reduce the complexity of structure, can effectively improve the reliability, and be convenient for carry out arbitrary angle adjustment to the wing, thereby be convenient for satisfy the actual demand of wing aerodynamic experiment.
Description
Technical Field
The utility model relates to the technical field of wing aerodynamic experimental devices, in particular to a three-component balance module.
Background
With the continuous development of technology, aviation technology has made very big progress, and a large amount of aircraft are designed and manufactured, and the aircraft often need carry out wind tunnel experiment in designing and manufacturing process, especially the wing part of aircraft to detect its aerodynamic characteristics, mainly including the lift, resistance and the pitching moment of wing, consequently need use three component balance module to detect the lift, resistance and the pitching moment that the wing produced in the wind tunnel, conveniently carry out comprehensive data information display. However, the existing three-component balance module is found in use, the structure is complex, the reliability is low, the angle adjustment is inconvenient, the experiment under any angle is difficult to be carried out on the wing, and the actual requirement of the wing aerodynamic experiment is difficult to be met.
Disclosure of Invention
In view of the above problems, an object of the present utility model is to: a three-component balance module is provided that solves the problems set forth in the background art described above.
In order to achieve the above purpose, the utility model adopts the technical scheme that: the three-component balance module comprises a bottom plate, three universal joints which are arranged in a triangular array are fixedly arranged on one side of the bottom plate, one force measuring plate is fixedly arranged at the other ends of the universal joints, an angle calibration assembly is fixedly arranged on the force measuring plate and positioned between the three universal joints, two lift force sensing assemblies are fixedly arranged on the bottom plate, a resistance sensing assembly is fixedly arranged on the bottom plate, the lift force sensing assemblies and the resistance sensing assemblies are all matched with the force measuring plate, one resistance spring is arranged between the bottom plate and the force measuring plate, and two ends of the resistance spring are fixedly arranged on the bottom plate and the force measuring plate respectively.
In order to facilitate rapid installation and fixation of the wing:
as a further improvement of the above technical scheme: the force measuring plate further comprises two fixing blocks, the fixing blocks are welded on the force measuring plate, slots are formed in the fixing blocks, a first inserting rod is mounted in each slot in a sliding mode, two identical wing connecting plates are arranged on the fixing blocks, the first inserting rod is welded with the wing connecting plates, insertion holes are formed in the first inserting rods in a penetrating mode, second inserting rods are arranged in the insertion holes in a sliding mode, first through holes are formed in one side, away from the angle calibration assembly, of each slot in a penetrating mode, the second inserting rods penetrate through the first through holes in a sliding mode, one connecting plate is arranged on one side, away from the angle calibration assembly, of each fixing block, one end of each second inserting rod is welded on the connecting plate, a vertical plate is welded on one side of the bottom plate, the vertical plate is located on one side, away from the angle calibration assembly, a screw rod penetrates through the connecting plates in a penetrating mode, and screw threads of the screw rod penetrate through the connecting plates.
The beneficial effects of this improvement are: through such setting to be convenient for carry out quick installation to the wing and fix, avoided loaded down with trivial details dismouting operation, labour saving and time saving can effectively improve the efficiency of wing aerodynamic experiment.
In order to ensure structural stability:
as a further improvement of the above technical scheme: the bottom plate is made of aluminum alloy, and is of an inverted cone structure.
The beneficial effects of this improvement are: through this setting to can improve the intensity of bottom plate, thereby guarantee the stability of structure.
In order to facilitate effective and accurate detection of lift and drag:
as a further improvement of the above technical scheme: the lifting force sensing assembly and the resistance sensing assembly are fixedly connected with the center position of one side, close to the bottom plate, of the force measuring plate through steel ropes.
The beneficial effects of this improvement are: through such setting to be convenient for carry out effective accurate detection to lift and resistance.
In order to be able to firmly fix the lift sensing assembly and the drag sensing assembly:
as a further improvement of the above technical scheme: the lift force sensing assembly and the resistance sensing assembly are fixedly connected with the bottom plate through bolts.
The beneficial effects of this improvement are: by this arrangement, the lift force sensing assembly and the resistance force sensing assembly can be firmly fixed.
In order to facilitate the lead screw to drive the connecting plate to move:
as a further improvement of the above technical scheme: the connecting plate is penetrated with a threaded through hole, and the screw rod is penetrated with the threaded through hole.
The beneficial effects of this improvement are: through setting up the screw thread through-hole to be convenient for the lead screw drives the connecting plate and removes.
In order to prevent the screw from coming off the connection plate:
as a further improvement of the above technical scheme: the top end of the screw rod is welded with a limiting plate, and the limiting plate is of a circular structure.
The beneficial effects of this improvement are: through setting up the limiting plate to can prevent that the lead screw from breaking away from the connecting plate.
In order to make the screw rotation more stable:
as a further improvement of the above technical scheme: the vertical plate is penetrated with a second through hole, and the screw rod rotates to penetrate through the second through hole.
The beneficial effects of this improvement are: through setting up the second through-hole to be convenient for carry out spacing and support to the lead screw, make the lead screw rotate more stably.
The beneficial effects of the utility model are as follows: through simple wing three component comprehensive detection structure to can effectively reduce the complexity of structure, can effectively improve the reliability, and be convenient for carry out arbitrary angle adjustment to the wing, thereby be convenient for satisfy the actual demand of wing aerodynamic experiment.
Drawings
FIG. 1 is a schematic diagram of a front view of the present utility model;
FIG. 2 is a schematic view of a front cross-sectional structure of the present utility model;
FIG. 3 is an enlarged schematic view of the portion A of FIG. 1 according to the present utility model;
FIG. 4 is a schematic perspective sectional assembly structure of a first bayonet and wing attachment panel of the present utility model.
In the figure: 1. a bottom plate; 2. a universal joint; 3. a force measuring plate; 4. an angle calibration assembly; 5. a lift force sensing assembly; 6. a resistance spring; 7. a resistance sensing assembly; 8. a fixed block; 9. a slot; 10. a first plunger; 11. a wing connection plate; 12. a jack; 13. a second plunger; 14. a first through hole; 15. a connecting plate; 16. a vertical plate; 17. and a screw rod.
Detailed Description
In order that those skilled in the art may better understand the technical solutions of the present utility model, the following detailed description of the present utility model with reference to the accompanying drawings is provided for exemplary and explanatory purposes only and should not be construed as limiting the scope of the present utility model.
As shown in fig. 1-4, the three-component balance module comprises a bottom plate 1, three universal joints 2 arranged in a triangle array are fixedly arranged on one side of the bottom plate 1, the other ends of the three universal joints 2 are fixedly provided with the same force measuring plate 3, the force measuring plate 3 is fixedly provided with an angle calibration component 4, the angle calibration component 4 is positioned between the three universal joints 2, the bottom plate 1 is fixedly provided with two lift force sensing components 5, the bottom plate 1 is fixedly provided with a resistance force sensing component 7, the lift force sensing components 5 and the resistance force sensing components 7 are matched with the force measuring plate 3, the same resistance spring 6 is arranged between the bottom plate 1 and the force measuring plate 3, two ends of the resistance spring 6 are fixedly arranged on the bottom plate 1 and the force measuring plate 3 respectively, and the complexity of the structure can be effectively reduced through a simple wing three-component force comprehensive detection structure, can effectively improve the reliability, and be convenient for carry out arbitrary angle adjustment to the wing, thereby be convenient for satisfy the actual demand of wing aerodynamic experiment, dynamometer board 3 still includes two fixed blocks 8, fixed block 8 welds on dynamometer board 3, slot 9 has been seted up on fixed block 8, sliding mounting has first inserted bar 10 in slot 9, two be equipped with same wing connecting plate 11 on the fixed block 8, first inserted bar 10 welds with wing connecting plate 11, it has jack 12 to run through on the first inserted bar 10, the sliding of jack 12 runs through there is second inserted bar 13, the first through-hole 14 is run through to one side of slot 9 that is kept away from angle calibration subassembly 4, second inserted bar 13 slides and runs through first through-hole 14, two one side of fixed block 8 that is kept away from angle calibration subassembly 4 is equipped with same connecting plate 15, the one end welding of second inserted bar 13 is on connecting plate 15, one side welding of bottom plate 1 has riser 16, riser 16 is located one side that connecting plate 15 kept away from angle calibration subassembly 4, it runs through there is lead screw 17 to rotate on the riser 16, lead screw 17 screw thread runs through connecting plate 15, through setting up like this, thereby be convenient for carry out quick installation fixed to the wing, avoided loaded down with trivial details dismouting operation, labour saving and time saving can effectively improve wing aerodynamic experiment's efficiency, bottom plate 1's material is the aluminum alloy, bottom plate 1 is the back taper structure, through setting up like this, thereby can improve bottom plate 1's intensity, thereby guarantee the stability of structure, lift force sensing assembly 5 and resistance sensing assembly 7 all are close to one side central point put fixed connection of bottom plate 1 through wire rope and force measuring plate 3, through setting up like this, thereby be convenient for carry out effective accurate detection to lift force and resistance, lift force sensing assembly 5 and resistance sensing assembly 7 all pass through bolt and bottom plate 1 fixed connection like this, thereby can effectively improve the efficiency of wing aerodynamic experiment, the material of bottom plate 1 is the aluminum alloy, bottom plate 1 is the back taper structure, thereby the screw thread is passed through to the screw thread through 17, thereby the screw thread is passed through to the connecting plate 17, thereby the through the screw thread is passed through to the screw 17 and is rotated to the through to the side of being convenient for 17, thereby the top is realized through the screw 17, and is realized through the screw 17, thereby the through-hole 17, thereby the through the setting up through the screw 17.
The working principle of the utility model is as follows: when in use, the wing connecting plate 11 rotatably arranged on the wing is aligned with the two fixed blocks 8, so that the two first inserting rods 10 are respectively inserted into the corresponding slots 9 in a sliding way, the wing connecting plate 11 is contacted with the two fixed blocks 8, then the screw rod 17 is rotated, the screw rod 17 is rotated on the vertical plate 16, meanwhile, the screw rod 17 drives the connecting plate 15 to move close to the two fixed blocks 8, the two second inserting rods 13 are driven to respectively slide in the corresponding first through holes 14 until the second inserting rods 13 slide to penetrate through the corresponding inserting holes 12, the first inserting rods 10 are fixed, the wing is arranged on the force measuring plate 3, and the arrangement is convenient for carrying out quick installation and fixation on the wing, so that complicated dismounting operation is avoided, time and labor are saved, the efficiency of wing aerodynamic experiments can be effectively improved, and then the two lift force sensing assemblies 5, the resistance sensing assembly 7 and the angle calibration assembly 4 are connected with a display, then the angle of the wing rotatably mounted on the wing connecting plate 11 is limited by the angle calibration assembly 4, then the bottom plate 1 is fixed in the low-speed wind tunnel, the wind tunnel is started, the wing is blown by wind to download the rotation of the wing connecting plate 11 and limited by the angle calibration assembly 4, the experimental angle is maintained for the wing, the pitching moment of the wing is detected, the wing rises under the action of lifting force and drives the force measuring plate 3 to rise, the three universal joints 2 are enabled to rotate upwards, meanwhile, the steel wire ropes of the two lifting force sensing assemblies 5 shrink upwards, lifting force is detected, meanwhile, the wing moves transversely under the action of resistance, the force measuring plate 3 is driven to move transversely, the three universal wheels rotate towards the moving direction of the force measuring plate 3, the resistance spring 6 is stretched, the steel wire ropes of the resistance sensing assemblies 7 shrink, the resistance of the wing is detected, pitching moment, lift and resistance signals of the wing are all collected and displayed through the display, and through the arrangement, the complexity of the structure can be effectively reduced, the reliability can be effectively improved, the wing can be conveniently adjusted at any angle, and therefore the actual requirements of the wing aerodynamic experiment can be conveniently met.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. The principles and embodiments of the present utility model have been described herein with reference to specific examples, the description of which is intended only to facilitate an understanding of the method of the present utility model and its core ideas. The foregoing is merely illustrative of the preferred embodiments of the utility model, and it is noted that there is virtually no limit to the specific structure which may be imposed by those skilled in the art without departing from the spirit of the utility model, and that modifications, adaptations, or variations of the foregoing features may be combined in a suitable manner; such modifications, variations and combinations, or the direct application of the inventive concepts and aspects to other applications without modification, are contemplated as falling within the scope of the present utility model.
Claims (8)
1. Three-component balance module, including bottom plate (1), its characterized in that: one side fixed mounting of bottom plate (1) has three universal joint (2) that are triangle-shaped array and arrange, three the other end fixed mounting of universal joint (2) has same dynamometry board (3), fixed mounting has angle calibration subassembly (4) on dynamometry board (3), angle calibration subassembly (4) are located between three universal joint (2), fixed mounting has two lift force sensing components (5) on bottom plate (1), fixed mounting has resistance sensing component (7) on bottom plate (1), lift force sensing component (5) and resistance sensing component (7) all with dynamometry board (3) looks adaptation, be equipped with same resistance spring (6) between bottom plate (1) and dynamometry board (3), the both ends of resistance spring (6) are fixed mounting respectively on bottom plate (1) and dynamometry board (3).
2. The three-component balance module of claim 1, wherein: the force measuring plate (3) further comprises two fixing blocks (8), the fixing blocks (8) are welded on the force measuring plate (3), slots (9) are formed in the fixing blocks (8), first inserting rods (10) are arranged in the slots (9) in a sliding mode, the same wing connecting plates (11) are arranged on the fixing blocks (8), the first inserting rods (10) are welded with the wing connecting plates (11), inserting holes (12) are formed in the first inserting rods (10) in a penetrating mode, second inserting rods (13) are formed in the inserting holes (12) in a sliding mode, first through holes (14) are formed in one side, far away from the angle calibration assembly (4), of the slots (9), the second inserting rods (13) penetrate through the first through holes (14) in a sliding mode, one side, far away from the angle calibration assembly (4), of the two fixing blocks (8) is provided with the same connecting plates (15), one ends of the second inserting rods (13) are welded on the connecting plates (15), one side of the bottom plates (1) is welded with a vertical plate (16), one side of the vertical plate (16) is located on the vertical plate (16), and the screw rod (17) penetrates through the screw rod (17).
3. The three-component balance module of claim 1, wherein: the base plate (1) is made of aluminum alloy, and the base plate (1) is of an inverted cone structure.
4. The three-component balance module of claim 1, wherein: the lifting force sensing assembly (5) and the resistance sensing assembly (7) are fixedly connected with the center position of one side, close to the bottom plate (1), of the force measuring plate (3) through steel wires.
5. The three-component balance module of claim 1, wherein: the lifting force sensing assembly (5) and the resistance sensing assembly (7) are fixedly connected with the bottom plate (1) through bolts.
6. The three-component balance module of claim 2, wherein: threaded through holes are formed in the connecting plates (15) in a penetrating mode, and the screw rods (17) penetrate through the threaded through holes in a threaded mode.
7. The three-component balance module of claim 2, wherein: the top end of the screw rod (17) is welded with a limiting plate, and the limiting plate is of a circular structure.
8. The three-component balance module of claim 2, wherein: the vertical plate (16) is penetrated with a second through hole, and the screw rod (17) penetrates through the second through hole in a rotating mode.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322113723.XU CN220437715U (en) | 2023-08-08 | 2023-08-08 | Three-component balance module |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322113723.XU CN220437715U (en) | 2023-08-08 | 2023-08-08 | Three-component balance module |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220437715U true CN220437715U (en) | 2024-02-02 |
Family
ID=89689177
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322113723.XU Active CN220437715U (en) | 2023-08-08 | 2023-08-08 | Three-component balance module |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220437715U (en) |
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2023
- 2023-08-08 CN CN202322113723.XU patent/CN220437715U/en active Active
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