CN212829144U - A antitorque test device for aircraft wing intensity - Google Patents
A antitorque test device for aircraft wing intensity Download PDFInfo
- Publication number
- CN212829144U CN212829144U CN202021485898.3U CN202021485898U CN212829144U CN 212829144 U CN212829144 U CN 212829144U CN 202021485898 U CN202021485898 U CN 202021485898U CN 212829144 U CN212829144 U CN 212829144U
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- sleeve
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- 238000003466 welding Methods 0.000 claims abstract description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 11
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 230000006835 compression Effects 0.000 claims description 2
- 238000007906 compression Methods 0.000 claims description 2
- 238000005728 strengthening Methods 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
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Abstract
The utility model relates to a wing antitorque song tests technical field, discloses an antitorque song testing arrangement for aircraft wing intensity, the upper surface of connecting plate is provided with the motor, the drive end of motor is connected with the rotation axis, the one end of rotation axis is provided with the adapter sleeve, one side welding of adapter sleeve has the pinch-off blades and the inside of pinch-off blades is provided with the wing, one side slidable mounting that the upper surface of base is located the fixed plate has the movable plate, one side of movable plate is provided with propelling movement subassembly, and the top of movable plate installs the clamping unit, the inside of clamping unit is provided with the wing. The utility model can effectively reduce the labor intensity of workers and visually see whether the wings are distorted or not by arranging the pushing component; through setting up clamping component, can avoid fixed not firm of wing and take place not hard up and lead to unable to carry out the distortion test to the wing.
Description
Technical Field
The utility model relates to an antitorque test technical field of wing specifically is an antitorque testing arrangement for aircraft wing intensity.
Background
The wing is one of important parts of an airplane, is arranged on the airplane body, has the main function of generating lift force, and forms good stability and maneuverability together with the empennage.
However, when the wing is subjected to an anti-twist test at present, the wing is generally moved to a test position manually, so that the labor intensity of workers is increased, and when the wing is tested, if one end of the wing is not fixed firmly, the wing is easy to move, so that the wing cannot be tested. Accordingly, one skilled in the art provides an anti-twist test device for aircraft wing strength to address the problems set forth in the background above.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an antitorque bent testing arrangement for aircraft wing intensity to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
the utility model provides an antitorque test device for aircraft wing intensity, includes the base, the fixed plate is installed to the border position department integral type of base, one side fixed mounting of fixed plate has the connecting plate, the upper surface of connecting plate is provided with the motor, the drive end of motor is connected with the rotation axis, the one end of rotation axis is provided with the adapter sleeve, one side welding of adapter sleeve has the pinch-off blades and the inside of pinch-off blades is provided with the wing, one side slidable mounting that the upper surface of base is located the fixed plate has the movable plate, one side of movable plate is provided with the propelling movement subassembly, and the top of movable plate installs clamping component, clamping component's inside is provided with.
As a further aspect of the present invention: the connecting sleeve is characterized in that a through hole is formed in the outer portion of the rotating shaft, a through hole is also formed in the outer portion of the connecting sleeve, a first bolt is arranged in the outer portion of the connecting sleeve, one end of the first bolt penetrates through the through hole formed in the outer portion of the connecting sleeve and extends to the through hole formed in the rotating shaft to be in threaded connection with the through hole.
As a further aspect of the present invention: two clamping plates are symmetrically arranged on one side of the connecting sleeve in a rectangular shape, and the distance between the two clamping plates is the same as the thickness of the wing.
As a further aspect of the present invention: the clamping assembly comprises a clamping sleeve arranged on the upper surface of the movable plate in a U-shaped mode, a first anti-skid layer is arranged on the inner upper surface of the clamping sleeve, a second bolt is installed on the upper surface of the clamping sleeve in a rotating mode, a screw hole in threaded connection with the second bolt is formed in the clamping sleeve, the tail end of the second bolt extends into the pressing plate, a limiting block is arranged on the outer portion of the second bolt, a limiting groove matched with the second bolt is formed in the pressing plate, and a second anti-skid layer is arranged on the lower surface of the pressing plate.
As a further aspect of the present invention: the second anti-slip layer is the same as the first anti-slip layer in size and shape, and anti-slip bumps are arranged on the surfaces of the second anti-slip layer and the first anti-slip layer.
As a further aspect of the present invention: the propelling movement subassembly is including installing the locating lever in movable plate one side, the inside of locating lever is provided with the strengthening rib, the locating hole that matches each other with the strengthening rib is seted up to the inside of fixed plate, the below of movable plate is connected with the connecting rod, the slider is installed to the lower extreme of connecting rod, the inside of base is seted up with the gliding spout of slider, electric telescopic handle is installed to one side of movable plate.
As a further aspect of the present invention: the strengthening rib is the rectangle setting, and the strengthening rib is provided with ten at the inside equidistance of locating lever, the slider is the T type setting with the connecting rod, and slider and connecting rod are stainless steel material.
Compared with the prior art, the beneficial effects of the utility model are that:
1. the utility model discloses a set up the propelling movement subassembly, the effect that utilizes electric telescopic handle makes and promotes the movable plate on the base, the slider of movable plate below slides in the spout promptly to can make the locating lever run through in the locating hole of seting up in the fixed plate, be provided with the strengthening rib in the inside of locating lever, thereby increase holistic stability, prevent to take place to empty when the motor during operation distorts the wing, its degree of automation is high, can effectually alleviate staff's intensity of labour, and can audio-visually see whether the wing takes place to distort.
2. Through setting up clamping unit, utilize second bolt and screw threaded connection and rotate downwards in the screw to make the pressure strip lapse to move down and press from both sides tight fixedly to placing the wing inside the clamping sleeve, and be provided with second skid resistant course and first skid resistant course on the lower surface of pressure strip and the inside upper surface of clamping sleeve, can avoid fixed not firm of wing and take place not hard up and lead to can't distort the test to the wing.
Drawings
FIG. 1 is a schematic diagram of an anti-twist test apparatus for aircraft wing strength;
FIG. 2 is an enlarged view of portion A of FIG. 1;
FIG. 3 is a cross-sectional view of a clamp assembly in an anti-twist test setup for aircraft wing strength;
FIG. 4 is an enlarged view of portion B of FIG. 3;
FIG. 5 is a schematic diagram of a push assembly of an anti-twist test apparatus for aircraft wing strength;
fig. 6 is a schematic diagram of the connection between the sliding block and the sliding groove in the anti-twisting test device for the strength of the airplane wing.
In the figure: 1. a fixing plate; 2. a motor; 3. a connecting plate; 4. a base; 5. a rotating shaft; 6. a first bolt; 7. connecting sleeves; 8. an airfoil; 9. a clamping assembly; 10. a push assembly; 11. moving the plate; 12. a clamping plate; 91. a clamping sleeve; 92. a compression plate; 93. a first non-slip layer; 94. a second non-slip layer; 95. a second bolt; 96. a screw hole; 97. a limiting block; 98. a limiting groove; 101. an electric telescopic rod; 102. reinforcing ribs; 103. positioning holes; 104. positioning a rod; 105. a connecting rod; 106. a slider; 107. a chute.
Detailed Description
Referring to fig. 1 to 6, in an embodiment of the present invention, an anti-distortion testing device for aircraft wing strength includes a base 4, a fixing plate 1 is integrally installed at an edge position of the base 4, a connecting plate 3 is fixedly installed at one side of the fixing plate 1, a motor 2 is installed on an upper surface of the connecting plate 3, a driving end of the motor 2 is connected to a rotating shaft 5, a connecting sleeve 7 is installed at one end of the rotating shaft 5, a through hole is opened at an outer portion of the rotating shaft 5, a through hole is also opened at an outer portion of the connecting sleeve 7, a first bolt 6 is installed at an outer portion of the connecting sleeve 7, one end of the first bolt 6 penetrates through the through hole opened at the outer portion of the connecting sleeve 7 and extends to the through hole opened at the inner portion of the rotating shaft 5 to be in threaded connection therewith, a clamping plate 12 is welded at one, and the distance between the two clamping plates 12 is the same as the thickness of the wing 8, and the connecting sleeve 7 and the rotating shaft 5 can be conveniently detached and replaced through the arrangement of the first bolt 6, so that the distance between the clamping plates 12 arranged on one side of the connecting sleeve 7 is replaced, and the requirement that the wings 8 with different thicknesses are clamped and fixed is met.
In fig. 5 and 6: a movable plate 11 is slidably mounted on one side of the fixed plate 1 on the upper surface of the base 4, a pushing assembly 10 is arranged on one side of the movable plate 11, the pushing assembly 10 comprises a positioning rod 104 mounted on one side of the movable plate 11, a reinforcing rib 102 is arranged inside the positioning rod 104, a positioning hole 103 matched with the reinforcing rib 102 is formed inside the fixed plate 1, a connecting rod 105 is connected below the movable plate 11, a sliding block 106 is mounted at the lower end of the connecting rod 105, a sliding groove 107 sliding with the sliding block 106 is formed inside the base 4, an electric telescopic rod 101 is mounted on one side of the movable plate 11, the reinforcing rib 102 is arranged in a rectangular shape, ten reinforcing ribs 102 are equidistantly arranged inside the positioning rod 104, the sliding block 106 and the connecting rod 105 are arranged in a T shape, the sliding block 106 and the connecting rod 105 are made of stainless steel, namely, the sliding block 106 below the moving plate 11 slides in the sliding groove 107, the positioning rod 104 can penetrate through the positioning hole 103 formed in the fixing plate 1, and the reinforcing rib 102 is arranged inside the positioning rod 104, so that the overall stability is improved, the wing 8 is prevented from being toppled when the motor 2 works, the automation degree is high, the labor intensity of workers can be effectively relieved, and whether the wing 8 is distorted or not can be visually seen.
In fig. 2, 3 and 4: the clamping assembly 9 is mounted at the top end of the moving plate 11, the wing 8 is arranged inside the clamping assembly 9, the clamping assembly 9 comprises a clamping sleeve 91 which is mounted on the upper surface of the moving plate 11 and is in a U-shaped arrangement, a first anti-skid layer 93 is arranged on the upper surface inside the clamping sleeve 91, a second bolt 95 is rotatably mounted on the upper surface of the clamping sleeve 91, a screw hole 96 in threaded connection with the second bolt 95 is formed inside the clamping sleeve 91, the tail end of the second bolt 95 extends into the pressing plate 92, a limiting block 97 is arranged outside the second bolt 95, a limiting groove 98 matched with the second bolt 95 is formed inside the pressing plate 92, a second anti-skid layer 94 is arranged on the lower surface of the pressing plate 92, the second anti-skid layer 94 is the same as the first anti-skid layer 93 in size and shape, anti-skid layers 94 and the first anti-skid layer 93 are both provided with anti-skid surfaces, protruding points are connected with the screw hole 96 through threads of the second bolt 95 and rotate downwards in the screw hole 96, therefore, the pressing plate 92 moves downwards to clamp and fix the wing 8 placed in the clamping sleeve 91, the second anti-skid layer 94 and the first anti-skid layer 93 are arranged on the lower surface of the pressing plate 92 and the inner upper surface of the clamping sleeve 91, and the situation that the wing 8 cannot be subjected to torsion testing due to looseness caused by the fact that the wing 8 is not firmly fixed can be avoided.
The utility model discloses a theory of operation is: when the wing buckling and clamping device is used, the wing 8 is firstly placed into the clamping sleeve 91 in the clamping assembly 9, the second bolt 95 above the clamping sleeve 91 is rotated, the second bolt 95 moves downwards in the screw hole 96, the tail end of the second bolt 95 rotates in the pressing plate 92, the pressing plate 92 moves downwards, the pressing plate 92 is in contact with the surface of the wing 8, the second bolt 95 is continuously screwed, the wing 8 is clamped and fixed through the pressing plate 92, the second anti-skid layer 94 is arranged on the lower surface of the pressing plate 92, the first anti-skid layer 93 is arranged in the clamping sleeve 91, the first anti-skid layer 93 and the second anti-skid layer 94 are both provided with anti-skid convex points, the stability of the wing 8 in the clamping sleeve 91 can be ensured, the situation that the wing 8 cannot be subjected to a torsion test due to looseness caused by the fact that the wing 8 is not firmly fixed is avoided, and the electric telescopic rod 101 in the pushing assembly 10 is used for working, the movable plate 11 is pushed towards the fixed plate 1, namely, a sliding block 106 connected with the lower part of the movable plate 11 through a connecting rod 105 slides in a sliding groove 107, after the movable plate is pushed by an electric telescopic rod 101, one end of the wing 8 clamped in a clamping sleeve 91 can enter the clamping plate 12 arranged on one side of a connecting sleeve 7, meanwhile, a positioning rod 104 can penetrate through the positioning hole 103, a reinforcing rib 102 is arranged in the positioning rod 104, the integral stability can be improved, the wing 8 is prevented from being toppled when the motor 2 works, the automation degree is high, the labor intensity of workers can be effectively relieved, whether the wing 8 is distorted or not can be visually seen, the motor 2 arranged on the connecting plate 3 works, the rotating shaft 5 connected with the driving end of the motor 2 works, and the clamping plate 12 arranged on one side of the connecting sleeve 7 rotates, thereby enabling the wing 8 to be twisted, enabling a worker to visually observe the twist resistance of the wing 8.
The above-mentioned, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.
Claims (7)
1. The utility model provides an antitorque test device for aircraft wing intensity, includes base (4), its characterized in that, fixed plate (1) is installed to the border position department integral type of base (4), one side fixed mounting of fixed plate (1) has connecting plate (3), the upper surface of connecting plate (3) is provided with motor (2), the drive end of motor (2) is connected with rotation axis (5), the one end of rotation axis (5) is provided with adapter sleeve (7), one side welding of adapter sleeve (7) has pinch-off blades (12) and the inside of pinch-off blades (12) is provided with wing (8), one side slidable mounting that the upper surface of base (4) is located fixed plate (1) has movable plate (11), one side of movable plate (11) is provided with propelling movement subassembly (10), and clamping assembly (9) are installed to the top of movable plate (11), the clamping assembly (9) is internally provided with a wing (8).
2. The device for testing the strength of the wings of the airplane as claimed in claim 1, wherein a through hole is formed in the outer portion of the rotating shaft (5), a through hole is also formed in the outer portion of the connecting sleeve (7), the first bolt (6) is arranged on the outer portion of the connecting sleeve (7), and one end of the first bolt (6) penetrates through the through hole formed in the outer portion of the connecting sleeve (7) and extends to the through hole formed in the inner portion of the rotating shaft (5) to be in threaded connection with the through hole.
3. The torsion resistance testing device for the strength of the airplane wing is characterized in that two clamping plates (12) are arranged on one side of the connecting sleeve (7) in a rectangular and symmetrical mode, and the distance between the two clamping plates (12) is the same as the thickness of the airplane wing (8).
4. An anti-twist test device for aircraft wing strength according to claim 1, characterized in that the clamping component (9) comprises a clamping sleeve (91) which is arranged on the upper surface of the moving plate (11) in a U shape, the upper surface of the inner part of the clamping sleeve (91) is provided with a first anti-skid layer (93), a second bolt (95) is rotatably arranged on the upper surface of the clamping sleeve (91), a screw hole (96) in threaded connection with the second bolt (95) is formed inside the clamping sleeve (91), the tail end of the second bolt (95) extends to the inside of the pressing plate (92), a limiting block (97) is arranged outside the second bolt (95), a limit groove (98) matched with the second bolt (95) is arranged in the compression plate (92), the lower surface of the compacting plate (92) is provided with a second anti-slip layer (94).
5. The device for testing the strength of the wings of the airplane as claimed in claim 4, wherein the second anti-skid layer (94) and the first anti-skid layer (93) are the same in size and shape, and anti-skid bumps are arranged on the surfaces of the second anti-skid layer (94) and the first anti-skid layer (93).
6. The anti-distortion testing device for the strength of the wings of the aircraft as claimed in claim 1, wherein the pushing assembly (10) comprises a positioning rod (104) installed on one side of the moving plate (11), a reinforcing rib (102) is arranged inside the positioning rod (104), a positioning hole (103) matched with the reinforcing rib (102) is formed inside the fixing plate (1), a connecting rod (105) is connected below the moving plate (11), a sliding block (106) is installed at the lower end of the connecting rod (105), a sliding groove (107) sliding with the sliding block (106) is formed inside the base (4), and an electric telescopic rod (101) is installed on one side of the moving plate (11).
7. The device for testing the strength of the wings of the airplane as claimed in claim 6, wherein the reinforcing ribs (102) are arranged in a rectangular shape, ten reinforcing ribs (102) are arranged inside the positioning rod (104) at equal intervals, the sliding block (106) and the connecting rod (105) are arranged in a T shape, and the sliding block (106) and the connecting rod (105) are made of stainless steel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021485898.3U CN212829144U (en) | 2020-07-24 | 2020-07-24 | A antitorque test device for aircraft wing intensity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021485898.3U CN212829144U (en) | 2020-07-24 | 2020-07-24 | A antitorque test device for aircraft wing intensity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212829144U true CN212829144U (en) | 2021-03-30 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021485898.3U Expired - Fee Related CN212829144U (en) | 2020-07-24 | 2020-07-24 | A antitorque test device for aircraft wing intensity |
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| Country | Link |
|---|---|
| CN (1) | CN212829144U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113176090A (en) * | 2021-06-11 | 2021-07-27 | 丰县森侠智能设备有限公司 | Wing strength detection device for unmanned aerial vehicle manufacturing |
-
2020
- 2020-07-24 CN CN202021485898.3U patent/CN212829144U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113176090A (en) * | 2021-06-11 | 2021-07-27 | 丰县森侠智能设备有限公司 | Wing strength detection device for unmanned aerial vehicle manufacturing |
| CN113176090B (en) * | 2021-06-11 | 2022-01-18 | 丰县森侠智能设备有限公司 | Wing strength detection device for unmanned aerial vehicle manufacturing |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20210330 |
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| CF01 | Termination of patent right due to non-payment of annual fee |