CN110879033B - High-precision automatic type comparison measuring device for airplane tire shape detection - Google Patents
High-precision automatic type comparison measuring device for airplane tire shape detection Download PDFInfo
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- CN110879033B CN110879033B CN201911143078.8A CN201911143078A CN110879033B CN 110879033 B CN110879033 B CN 110879033B CN 201911143078 A CN201911143078 A CN 201911143078A CN 110879033 B CN110879033 B CN 110879033B
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- 238000001514 detection method Methods 0.000 title description 9
- 238000009434 installation Methods 0.000 claims abstract description 22
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- 238000003466 welding Methods 0.000 claims description 7
- 230000007246 mechanism Effects 0.000 claims description 6
- 238000004804 winding Methods 0.000 claims description 5
- 229910000838 Al alloy Inorganic materials 0.000 claims description 4
- 238000010030 laminating Methods 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 7
- 238000005259 measurement Methods 0.000 abstract description 3
- 230000033001 locomotion Effects 0.000 description 6
- 230000009471 action Effects 0.000 description 4
- 229910000997 High-speed steel Inorganic materials 0.000 description 3
- 238000011179 visual inspection Methods 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
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- 230000006835 compression Effects 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/20—Measuring arrangements characterised by the use of mechanical techniques for measuring contours or curvatures
Abstract
The invention discloses a high-precision automatic type comparison and measurement device for detecting the shape of an airplane tire, which comprises a support frame, a driving motor, an airplane tire body, a vortex spring and a recording paper tape, wherein the driving motor is fixed at the back of the vertical part of the support frame, the recording paper tapes are respectively installed on a first horizontal shaft and a second horizontal shaft, the recording paper tapes are attached to the bottom end of a recording pen and the upper end surface of the horizontal part of an installation plate, a fixed threaded rod is fixed on the side of a function plate, the fixed threaded rod penetrates through a track groove, and the track groove is formed in the vertical part of the support frame. This aircraft tire shape detects uses high accuracy automatic type contrast measuring device adopts neotype structural design, and this device can carry out aircraft tire's shape automatically and detect, and can take notes the result that detects, can get off the audio-visual record of size of form error, is convenient for compare, and more artifical range estimation, the degree of accuracy that this device detected is higher, and is fast, can also detect the aircraft tire of different diameters.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a high-precision automatic type comparison measuring device for detecting the shape of an airplane tire.
Background
The airplane is an aircraft and is provided with one or more engines, the engines generate strong forward thrust, the airplane is enabled to move at a high speed, lift force is generated by fixed wings of a fuselage, the airplane can fly in the atmosphere, when the airplane arrives at a destination and lands, the airplane tire is required to bear load generated by the airplane when the airplane lands and the ground, impact and vibration load generated when the airplane slides on the ground are buffered, the airplane can be ensured to land and stop safely, the airplane tire is an indispensable component of the airplane, the airplane tire consists of a hub and an outer composite tire body, when the airplane leaves a factory, the hub and the outer composite tire body are assembled into a whole, in order to control the quality of the airplane tire leaving the factory, the shape of the airplane tire must be detected and compared, and deformed defective products are prevented from flowing out.
With the continuous detection of the shape of the airplane tire, the following problems are found in the actual detection comparison process:
the existing machine tire shape detection comparison is manual visual inspection or rigid ferrule comparison, and because the rubber part outside the tire has elasticity, the rigid ferrule cannot be accurately measured, and the manual visual inspection error is large, so that the accuracy is low, the speed is low, and the efficiency is low.
Therefore, it is necessary to design a high-precision automatic contrast measuring device for detecting the shape of an aircraft tire in order to solve the above problems.
Disclosure of Invention
The invention aims to provide a high-precision automatic type comparison measuring device for detecting the shape of an airplane tire, which aims to solve the problems of large manual measurement error, low accuracy, low speed and low efficiency in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: a high-precision automatic type comparison measuring device for detecting the shape of an airplane tire comprises a support frame, a driving motor, an airplane tire body, a vortex spring and a recording paper tape, wherein the driving motor is fixed on the back of a vertical part of the support frame, a base disc is fixed at the output end of the driving motor, the airplane tire body is installed on the base disc, meanwhile, the airplane tire body is attached to the bottom of a contact wheel installation sleeve, the contact wheel installation sleeve is installed on a function board, a positioning bolt is installed at the top of the contact wheel installation sleeve, the tail end of the positioning bolt is attached to the function board, the function board is fixed on a trigger gear, the trigger gear is fixed on a middle shaft, the middle shaft penetrates through the vertical part of the support frame, the vortex spring is fixed on the back of the vertical part of the support frame, the bottom end of the trigger gear is, the movable plate penetrates through the stabilizing sleeve and the mounting plate, the stabilizing sleeve and the mounting plate are both fixed on the front surface of the vertical part of the support frame, meanwhile, a recording pen is fixed on the lower end face of the movable plate, a first driving gear and a second driving gear are fixed on the middle shaft, the first driving gear is connected with a first driven gear, and the first driven gear is fixed on the first horizontal shaft, and the first horizontal shaft is arranged on the mounting plate, the second driving gear is connected with the second driven gear which is fixed on the second horizontal shaft, and a second horizontal shaft is mounted on the mounting plate, the first horizontal shaft and the second horizontal shaft are both provided with a recording paper tape, and the recording paper tape is attached to the upper end surfaces of the bottom end of the recording pen and the horizontal part of the mounting plate, a fixed threaded rod is fixed on the side of the functional plate, the fixed threaded rod penetrates through the track groove, and the track groove is formed in the vertical part of the support frame.
Preferably, 18 strip-shaped windows are formed in the base plate at equal angles with respect to the center of the base plate, and the width of the strip-shaped windows in the base plate increases gradually from the position close to the center of the base plate to the position far from the center of the base plate.
Preferably, the pulley of the high-speed steel material of terminal surface installation closely laminates with the aircraft tire body outside under the contact wheel installation cover, and contact wheel installation cover and function board be sliding connection to function board and trigger gear are welded connection, and the function board is made by hollow aluminum alloy plate simultaneously.
Preferably, the function board is welded with the fixed threaded rod, the fixed threaded rod is in sliding connection with the track groove, the track groove is arc-shaped, and the circle center of the circle where the arc-shaped edge of the track groove is located coincides with the center of the center shaft.
Preferably, the trigger gear is in meshed connection with the movable plate, and the movable plate is in sliding connection with the stabilizing sleeve and the mounting plate.
Preferably, the first driving gear, the second driving gear, the first driven gear and the second driven gear are all bevel gears, and the diameters of the first driving gear, the second driving gear, the first driven gear and the second driven gear are all equal.
Preferably, the first driving gear and the second driving gear are both connected with the middle shaft in a welding mode, and the middle shaft and the support frame form a rotating mechanism through a bearing installed at the connecting position of the middle shaft and the vertical portion of the support frame.
Preferably, the first driven gear and the second driven gear are respectively connected with the first horizontal shaft and the second horizontal shaft in a welding mode, the first horizontal shaft and the second horizontal shaft form a rotating mechanism through bearings mounted at the tail ends of the first horizontal shaft and the second horizontal shaft and the mounting plate, and the winding directions of the recording paper tapes wound on the first horizontal shaft and the second horizontal shaft are opposite.
Compared with the prior art, the invention has the beneficial effects that: the high-precision automatic type comparison and measurement device for detecting the shape of the airplane tire adopts a novel structural design, so that the device can automatically detect the shape of the airplane tire, can record a detection result, can visually record the size of a shape error, is convenient for comparison and confirmation, has higher detection accuracy and high speed compared with manual visual inspection, and can detect the airplane tires with different diameters;
1. the structure formed by the contact wheel mounting sleeve, the function plate and the positioning bolt enables the triggering structure of the device to be suitable for airplane tires with different diameters;
2. the structure composed of the trigger gear, the middle shaft, the vortex spring, the movable plate, the stabilizing sleeve, the mounting plate and the recording pen can move under the driving of the trigger structure, and is a structural basis for realizing the detection and recording functions;
3. the structure that first drive gear, second drive gear, first driven gear, second driven gear, first horizontal axis and second horizontal axis are constituteed is opposite at aircraft tire protrusion and sunken motion direction, can pull the record paper tape and carry out the opposite direction's motion, and the cooperation detects the record structure, and the discernment aircraft tire protrusion and sunken that can be clear is.
Drawings
FIG. 1 is a schematic front view of the present invention;
FIG. 2 is a schematic front sectional view of the present invention;
FIG. 3 is a schematic top view of the present invention;
FIG. 4 is a schematic side view of the present invention;
FIG. 5 is a side view of the first and second driven gears of the present invention;
FIG. 6 is a schematic view of the structure of the base plate of the present invention.
In the figure: 1. a support frame; 2. a drive motor; 3. a base plate; 4. an aircraft tire body; 5. a contact wheel mounting sleeve; 6. a function board; 7. positioning the bolt; 8. triggering a gear; 9. a middle shaft; 10. a scroll spring; 11. a movable plate; 12. a stabilizing sleeve; 13. mounting a plate; 14. a stylus pen; 15. a first drive gear; 16. a second drive gear; 17. a first driven gear; 18. a second driven gear; 19. a first horizontal axis; 20. a second horizontal axis; 21. recording paper tape; 22. fixing a threaded rod; 23. a track groove.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6, the present invention provides a technical solution: a high-precision automatic type comparison measuring device for detecting the shape of an airplane tire comprises a support frame 1, a driving motor 2, a base plate 3, an airplane tire body 4, a contact wheel mounting sleeve 5, a function plate 6, a positioning bolt 7, a trigger gear 8, a middle shaft 9, a vortex spring 10, a movable plate 11, a stabilizing sleeve 12, a mounting plate 13, a recording pen 14, a first driving gear 15, a second driving gear 16, a first driven gear 17, a second driven gear 18, a first horizontal shaft 19, a second horizontal shaft 20, a recording paper tape 21, a fixed threaded rod 22 and a track groove 23, wherein the driving motor 2 is fixed on the back of the vertical part of the support frame 1, the base plate 3 is fixed on the output end of the driving motor 2, the airplane tire body 4 is mounted on the base plate 3, the airplane tire body 4 is attached to the bottom of the contact wheel mounting sleeve 5, the contact wheel mounting sleeve 5 is mounted on the function plate 6, the top of the contact wheel mounting sleeve 5 is provided with a positioning bolt 7, the tail end of the positioning bolt 7 is attached to the function board 6, the function board 6 is fixed on a trigger gear 8, the trigger gear 8 is fixed on a middle shaft 9, the middle shaft 9 penetrates through the vertical part of the support frame 1, the tail end of the middle shaft 9 is fixed with a vortex spring 10, the vortex spring 10 is fixed on the back of the vertical part of the support frame 1, the bottom end of the trigger gear 8 is connected with the upper end face of a movable plate 11, the movable plate 11 penetrates through a stabilizing sleeve 12 and a mounting plate 13, the stabilizing sleeve 12 and the mounting plate 13 are both fixed on the front face of the vertical part of the support frame 1, the lower end face of the movable plate 11 is fixed with a recording pen 14, the middle shaft 9 is fixed with a first driving gear 15 and a second driving gear 16, the first driving gear 15 is connected, meanwhile, a first horizontal shaft 19 is installed on the installation plate 13, a second driving gear 16 and a second driven gear 18 are connected with each other, the second driven gear 18 is fixed on a second horizontal shaft 20, the second horizontal shaft 20 is installed on the installation plate 13, recording paper tapes 21 are installed on the first horizontal shaft 19 and the second horizontal shaft 20, the recording paper tapes 21 are attached to the bottom end of the recording pen 14 and the upper end face of the horizontal part of the installation plate 13, a fixed threaded rod 22 is fixed on the side of the function board 6, the fixed threaded rod 22 penetrates through a track groove 23, and the track groove 23 is formed in the vertical part of the support frame 1.
In the embodiment, 18 strip-shaped windows are formed in the base plate 3 at equal angles relative to the center of the base plate 3, the width of each strip-shaped window in the base plate 3 is gradually increased from the position close to the center of the base plate 3 to the position far away from the center of the base plate 3, and the structural design enables the base plate 3 to stabilize airplane tire bodies 4 with different diameters through the strip-shaped windows and the bolts formed in the base plate 3;
the pulley made of high-speed steel installed on the lower end face of the contact wheel installation sleeve 5 is tightly attached to the outer side of the airplane tire body 4, the contact wheel installation sleeve 5 is in sliding connection with the function board 6, the function board 6 is in welding connection with the trigger gear 8, meanwhile, the function board 6 is made of hollow aluminum alloy plates, the contact wheel installation sleeve 5 can drive the pulley installed on the lower end face to slide on the function board 6 to change the position, so that the pulley installed on the lower end face of the contact wheel installation sleeve 5 can be attached to the proper positions of the airplane tire bodies 4 with different diameters, the pulley made of high-speed steel is wear-resistant and not prone to deformation, the function board 6 made of the hollow aluminum alloy plates is high in strength and light in weight, and extrusion on the airplane tire body 4 is reduced;
the function board 6 is connected with the fixed threaded rod 22 in a welding mode, the fixed threaded rod 22 is connected with the track groove 23 in a sliding mode, the track groove 23 is arc-shaped, the circle center of the circle where the arc-shaped edge of the track groove 23 is located coincides with the center of the middle shaft 9, the function board 6 can drive the fixed threaded rod 22 to slide stably along the track of the track groove 23 due to the structural design, and the rotating stability of the function board 6 is guaranteed;
the trigger gear 8 is in meshed connection with the movable plate 11, and the movable plate 11 is in sliding connection with the stabilizing sleeve 12 and the mounting plate 13, so that the trigger gear 8 can drive the movable plate 11 to stably slide and displace in the channels formed in the stabilizing sleeve 12 and the mounting plate 13 by utilizing the meshed connection relation when rotating;
the first driving gear 15, the second driving gear 16, the first driven gear 17 and the second driven gear 18 are all bevel gears, the diameters of the first driving gear 15, the second driving gear 16, the first driven gear 17 and the second driven gear 18 are all equal, and the above structural design enables the first driving gear 15, the second driving gear 16, the first driven gear 17 and the second driven gear 18 to perform rotary motion with the same speed;
the first driving gear 15 and the second driving gear 16 are both connected with the middle shaft 9 in a welding mode, the middle shaft 9 and the support frame 1 form a rotating mechanism through a bearing arranged at the joint of the middle shaft and the vertical part of the support frame 1, and the first driving gear 15 and the second driving gear 16 can perform rotary motion and perform stable power transmission through the structural design;
the first driven gear 17 and the second driven gear 18 are respectively connected with the first horizontal shaft 19 and the second horizontal shaft 20 in a welding mode, the first horizontal shaft 19 and the second horizontal shaft 20 form a rotating mechanism with the mounting plate 13 through bearings mounted at the tail ends of the first horizontal shaft 19 and the second horizontal shaft 20, and the winding directions of the recording paper tape 21 wound on the first horizontal shaft 19 and the second horizontal shaft 20 are opposite, so that the first driven gear 17 and the second driven gear 18 can drive the first horizontal shaft 19 and the second horizontal shaft 20 to rotate in the same direction when rotating, and the operation of pulling out the recording paper tape 21 from one of the first horizontal shaft 19 and the second horizontal shaft 20 and winding the recording paper tape on the other one of the first horizontal shaft 19 and the second horizontal shaft 20 is realized.
The working principle is as follows: when the device is used, firstly, a standard aircraft tire body 4 is fixed on a base disc 3 through bolts and nuts and a window arranged on the base disc 3 in figure 6, the center of the aircraft tire body 4 is aligned with the center of the base disc 3, a function plate 6 is stirred to drive a trigger gear 8 and a center shaft 9 to rotate, as a vortex spring 10 in figure 3 is in a compression and rolling state in an initial state, clockwise force is applied to the center shaft 9 in figure 1, a pulley arranged on the lower end face of a contact wheel mounting sleeve 5 is pressed on the surface of the aircraft tire body 4 through the function plate 6, in order to ensure stable attachment, the positioning bolt 7 can be unscrewed, the positioning bolt 7 does not extrude the function plate 6 any more, the contact wheel mounting sleeve 5 is stirred to slide to a proper position on the function plate 6, the extension line of the connecting line of the center of the aircraft tire body 4 and the center of the contact wheel mounting sleeve 5 is ensured to be vertical to the function plate 6, namely, the function plate 6 is ensured, screwing down the positioning bolt 7, and extruding the functional plate 6 by the positioning bolt 7 to fix the position of the contact wheel mounting sleeve 5;
the driving motor 2 in figure 3 is powered by an external power supply circuit, the driving motor 2 drives the aircraft tire body 4 fixed on the base disc 3 through an output shaft of the driving motor 2, and as the standard aircraft tire is nearly perfect circle, when the standard aircraft tire rotates, no protrusion pushes a pulley arranged on the lower end face of the contact wheel mounting sleeve 5, and no depression exists, so that the contact wheel mounting sleeve 5, the function plate 6 and the middle shaft 9 rotate under the action of the vortex spring 10, namely the trigger gear 8 does not rotate, the movable plate 11 is not driven by the trigger gear 8, the recording pen 14 is driven to displace in the horizontal direction, the recording pen 14 does not leave marks on the recording paper tape 21, the power supply for the driving motor 2 is stopped, and in the adjusting process of the function plate 6, the fixed threaded rod 22 is driven to slide and displace in the track groove 23, when the driving motor 2 is powered off, after the aircraft tire body 4 and the base disc 3 stop rotating, screwing a nut arranged at the tail end of the fixed threaded rod 22 in the figure 5, enabling the nut and a gasket fixed on the fixed threaded rod 22 to clamp the vertical part of the support frame 1, and enabling the contact wheel mounting sleeve 5 and the function board 6 to be in standard comparison positions at the moment;
the standard aircraft tire body 4 is taken down, the aircraft tire body 4 to be detected is installed on the base disc 3, the nut installed at the tail end of the fixed threaded rod 22 is unscrewed, the fixed threaded rod 22 can freely slide in the track groove 23, the driving motor 2 is powered again, the aircraft tire body 4 rotates, when the aircraft tire body 4 is convex, the convex position of the aircraft tire body 4 can jack the contact wheel installation sleeve 5 and the function plate 6 upwards, the function plate 6 drives the trigger gear 8 and the middle shaft 9 to rotate anticlockwise and extrude the contraction vortex spring 10, the trigger gear 8 drives the movable plate 11 in the figure 2 to drive the recording pen 14 to stably move rightwards under the action of the stabilizing sleeve 12 and the installation plate 13, the recording pen 14 leaves marks on the horizontal part of the recording paper tape 21 in the figure 5, when the middle shaft 9 rotates anticlockwise, the first driving gear 15 and the second driving gear 16 synchronously rotate anticlockwise, the first driving gear 15 drives the first driven gear 17 in fig. 5 to rotate counterclockwise with the first horizontal shaft 19, the first horizontal shaft 19 discharges the recording paper tape 21 wound thereon, the second driving gear 16 drives the second driven gear 18 to rotate counterclockwise synchronously with the second horizontal shaft 20, but since the recording paper tape 21 is wound on the second horizontal shaft 20 in the direction opposite to that on the first horizontal shaft 19, the second horizontal shaft 20 winds and stores the recording paper tape 21 discharged on the first horizontal shaft 19, the recording paper tape 21 is pulled rightward, and when the center shaft 9 is stationary, the contact point of the recording pen 14 with the recording paper tape 21 is taken as the recording origin, the origin after the movement on the recording paper tape 21 is located on the right side of the recording pen 14, and at this time, the recording pen 14 is moved rightward following the flap 11 in fig. 2, so that the recording pen 14 leaves a sine-like locus on the side of the vertical portion of the recording origin near the carriage 1, and the line salient parts similar to the wave crests point to the right;
on the contrary, when there is a dent on the aircraft tire body 4, under the action of the compressed and contracted scroll spring 10, the function board 6 drives the trigger gear 8 and the middle shaft 9 to rotate clockwise, so that the pulley mounted on the lower end surface of the contact wheel mounting sleeve 5 is tightly attached to the surface of the aircraft tire body 4, the trigger gear 8 drives the movable board 11 in fig. 2 to carry the recording pen 14 to move left stably under the action of the stabilizing sleeve 12 and the mounting plate 13, the first driving gear 15 and the second driving gear 16 synchronously rotate clockwise while the middle shaft 9 rotates clockwise, the first driving gear 15 drives the first driven gear 17 in fig. 5 to carry the first horizontal shaft 19 to rotate clockwise, the first horizontal shaft 19 winds the recording paper tape 21, and the second driving gear 16 drives the second driven gear 18 to carry the second horizontal shaft 20 to rotate clockwise synchronously, but because the winding direction of the recording paper tape 21 on the second horizontal shaft 20 is opposite to that on the first horizontal shaft 19, so that the recording paper tape 21 on the second horizontal shaft 20 is paid out and the recording paper tape 21 is pulled leftward, and at this time, the origin of the movement on the recording paper tape 21 is located on the left side of the recording pen 14, and since the recording pen 14 follows the moving plate 11 in fig. 2 to the left, the recording pen 14 leaves a sine-like locus on the side of the recording origin away from the vertical portion of the supporting frame 1, and the peak-like line projected portion is directed to the left side;
in conclusion, when the shape standard of the aircraft tire body 4 is detected, the clockwise or counterclockwise rotation of the central shaft 9 cannot be triggered, the recording pen 14 only leaves a recording original point on the recording paper tape 21, if the aircraft tire body 4 has a protrusion, the recording pen 14 can leave a protrusion curve pointing to the right side of the device in fig. 2 on the recording paper tape 21 at the position where the original point is close to the vertical part of the support frame 1, otherwise, if the aircraft tire body 4 has a depression, the recording pen 14 can leave a protrusion curve pointing to the left side of the device in fig. 2 at the position where the original point is far from the vertical part of the support frame 1 on the recording paper tape 21, so that the comparison effect is achieved, and whether the protrusion or the depression exists is determined through the protrusion direction, after the detection is finished, the aircraft tire body 4 only needs to be taken down, and the.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (8)
1. The utility model provides an aircraft tire shape detects uses automatic type contrast measuring device of high accuracy, includes support frame (1), driving motor (2), aircraft tire body (4), vortex spring (10) and recording paper tape (21), its characterized in that: the back of the vertical part of the support frame (1) is fixed with a driving motor (2), the output end of the driving motor (2) is fixed with a base disc (3), an aircraft tire body (4) is installed on the base disc (3), the bottom of the aircraft tire body (4) is attached to the bottom of a contact wheel installation sleeve (5), the contact wheel installation sleeve (5) is installed on a function plate (6), the top of the contact wheel installation sleeve (5) is provided with a positioning bolt (7), the tail end of the positioning bolt (7) is attached to the function plate (6), the function plate (6) is fixed on a trigger gear (8), the trigger gear (8) is fixed on a middle shaft (9), the middle shaft (9) penetrates through the vertical part of the support frame (1), the tail end of the middle shaft (9) is fixed with a vortex spring (10), and the vortex spring (10) is fixed on the back of the vertical part of the support frame, the bottom end of the trigger gear (8) is connected with the upper end face of the movable plate (11) mutually, the movable plate (11) penetrates through the stabilizing sleeve (12) and the mounting plate (13), the stabilizing sleeve (12) and the mounting plate (13) are fixed on the front face of the vertical part of the support frame (1), the lower end face of the movable plate (11) is fixed with a recording pen (14), a first driving gear (15) and a second driving gear (16) are fixed on the middle shaft (9), the first driving gear (15) is connected with a first driven gear (17) mutually, the first driven gear (17) is fixed on a first horizontal shaft (19), the first horizontal shaft (19) is installed on the mounting plate (13), the second driving gear (16) is connected with a second driven gear (18), the second driven gear (18) is fixed on a second horizontal shaft (20), and the second horizontal shaft (20) is installed on the mounting plate (13), all install record paper tape (21) on first horizontal axis (19) and second horizontal axis (20), and record paper tape (21) and the laminating of recording pen (14) bottom and mounting panel (13) horizontal part up end, function board (6) avris is fixed with fixed threaded rod (22), and fixed threaded rod (22) run through orbit groove (23) to the vertical part at support frame (1) is seted up in orbit groove (23).
2. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: 18 strip-shaped windows are formed in the base plate (3) at equal angles relative to the center of the base plate (3), and the width of each strip-shaped window in the base plate (3) is gradually increased from the position close to the center of the base plate (3) to the position far away from the center of the base plate (3).
3. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: contact wheel installation cover (5) end face installation's pulley and aircraft tire body (4) outside closely laminate, and contact wheel installation cover (5) and function board (6) are sliding connection to function board (6) are welded connection with trigger gear (8), and function board (6) are made by hollow aluminum alloy plate simultaneously.
4. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: the function board (6) is welded with the fixed threaded rod (22), the fixed threaded rod (22) is in sliding connection with the track groove (23), the track groove (23) is arc-shaped, and the circle center of the circle where the arc-shaped edge of the track groove (23) is located coincides with the center of the middle shaft (9).
5. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: the trigger gear (8) is in meshed connection with the movable plate (11), and the movable plate (11), the stabilizing sleeve (12) and the mounting plate (13) are in sliding connection.
6. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: the first driving gear (15), the second driving gear (16), the first driven gear (17) and the second driven gear (18) are all bevel gears, and the diameters of the first driving gear (15), the second driving gear (16), the first driven gear (17) and the second driven gear (18) are all equal.
7. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: the first driving gear (15) and the second driving gear (16) are both in welded connection with the middle shaft (9), and the middle shaft (9) and the support frame (1) form a rotating mechanism through a bearing installed at the joint of the middle shaft and the vertical part of the support frame (1).
8. The high-precision automatic type contrast measuring device for detecting the shape of an aircraft tire according to claim 1, characterized in that: the first driven gear (17) and the second driven gear (18) are respectively connected with the first horizontal shaft (19) and the second horizontal shaft (20) in a welding mode, the first horizontal shaft (19) and the second horizontal shaft (20) form a rotating mechanism through bearings mounted at the tail ends of the first horizontal shaft and the second horizontal shaft, and the winding directions of the recording paper tapes (21) wound on the first horizontal shaft (19) and the second horizontal shaft (20) are opposite.
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| CN201911143078.8A CN110879033B (en) | 2019-11-20 | 2019-11-20 | High-precision automatic type comparison measuring device for airplane tire shape detection |
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| CN201911143078.8A CN110879033B (en) | 2019-11-20 | 2019-11-20 | High-precision automatic type comparison measuring device for airplane tire shape detection |
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| CN110879033B true CN110879033B (en) | 2021-07-02 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05172502A (en) * | 1991-12-24 | 1993-07-09 | Hitachi Constr Mach Co Ltd | Device for measuring gear |
| CN102192720A (en) * | 2010-02-24 | 2011-09-21 | 施耐宝仪器股份有限公司 | Method and apparatus for determining geometrical dimensions of a wheel |
| JP2015021928A (en) * | 2013-07-23 | 2015-02-02 | 株式会社ブリヂストン | Tire outer shape measurement device, tire outer shape measurement method, and tire outer shape measurement program |
| JP2015143693A (en) * | 2013-04-26 | 2015-08-06 | 株式会社東京精密 | Shape measurement/calibration device |
| CN105539025A (en) * | 2016-01-07 | 2016-05-04 | 西华大学 | Tire safety monitoring device |
| CN206891327U (en) * | 2017-07-11 | 2018-01-16 | 北京求实工程管理有限公司 | Level detection recorder |
-
2019
- 2019-11-20 CN CN201911143078.8A patent/CN110879033B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05172502A (en) * | 1991-12-24 | 1993-07-09 | Hitachi Constr Mach Co Ltd | Device for measuring gear |
| CN102192720A (en) * | 2010-02-24 | 2011-09-21 | 施耐宝仪器股份有限公司 | Method and apparatus for determining geometrical dimensions of a wheel |
| JP2015143693A (en) * | 2013-04-26 | 2015-08-06 | 株式会社東京精密 | Shape measurement/calibration device |
| JP2015021928A (en) * | 2013-07-23 | 2015-02-02 | 株式会社ブリヂストン | Tire outer shape measurement device, tire outer shape measurement method, and tire outer shape measurement program |
| CN105539025A (en) * | 2016-01-07 | 2016-05-04 | 西华大学 | Tire safety monitoring device |
| CN206891327U (en) * | 2017-07-11 | 2018-01-16 | 北京求实工程管理有限公司 | Level detection recorder |
Non-Patent Citations (1)
| Title |
|---|
| 《浅析挤出胎面断面轮廓厚度检测》;张占兴等;《橡塑技术与装备》;20141231;第40卷(第17期);全文 * |
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