CN116499337A - Frock is used in measurement of aviation auxiliary material product - Google Patents
Frock is used in measurement of aviation auxiliary material product Download PDFInfo
- Publication number
- CN116499337A CN116499337A CN202310775493.5A CN202310775493A CN116499337A CN 116499337 A CN116499337 A CN 116499337A CN 202310775493 A CN202310775493 A CN 202310775493A CN 116499337 A CN116499337 A CN 116499337A
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- Prior art keywords
- clamping mechanism
- rotating cylinder
- longitudinal
- transverse
- aviation auxiliary
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- 238000005259 measurement Methods 0.000 title claims abstract description 7
- 230000007246 mechanism Effects 0.000 claims abstract description 69
- 230000001360 synchronised effect Effects 0.000 claims abstract description 17
- 230000002457 bidirectional effect Effects 0.000 claims description 37
- 230000000903 blocking effect Effects 0.000 claims description 18
- 230000005540 biological transmission Effects 0.000 description 6
- 230000000694 effects Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- 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
- G01B5/02—Measuring arrangements characterised by the use of mechanical techniques for measuring length, width or thickness
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Jigs For Machine Tools (AREA)
Abstract
The invention relates to the technical field of measurement and discloses a tool for measuring aviation auxiliary products, which comprises a tool body, a tool body and a tool body, wherein the tool body is used for accommodating the aviation auxiliary products; and the transverse clamping mechanism is connected to the tool body. This frock is used in aviation auxiliary material product measurement when using, the first rotary drum of drive rotates clockwise, can drive vertical drive assembly, make vertical fixture carry out vertical centre gripping to aviation auxiliary material product, the first rotary drum of drive anticlockwise rotates, can drive horizontal drive assembly, make horizontal fixture carry out horizontal centre gripping to aviation auxiliary material product, promote first rotary drum and remove backward, horizontal drive assembly and vertical drive assembly can not normally operate, can drive horizontal fixture and vertical fixture synchronous operation through synchronous drive assembly this moment, thereby remove the centre gripping to aviation auxiliary material product, need not the staff and move the position and control the operation respectively, it is more convenient to use.
Description
Technical Field
The invention relates to the technical field of measurement, in particular to a tool for measuring aviation auxiliary products.
Background
The aviation auxiliary material is a generic name of various auxiliary materials used for manufacturing aircrafts, aeroengines, airborne equipment and the like, and the length and the width of an aviation auxiliary material product need to be measured after the aviation auxiliary material product is produced, so that whether the aviation auxiliary material product is qualified or not is judged.
The measurement tool in the related art generally pushes two transverse clamping plates to be close to each other and clamp aviation auxiliary materials transversely, then pushes two longitudinal clamping plates to be close to each other and clamp aviation auxiliary materials longitudinally, length values and width values of the aviation auxiliary materials are measured by checking length scale marks on the tool, however, the operation positions for controlling the two transverse clamping plates to be close to each other and the operation positions for controlling the two longitudinal clamping plates to be close to each other are not usually the same operation position, workers are required to move the positions to perform respective control operation, the process is complex, and the use is very inconvenient.
Disclosure of Invention
The invention aims to provide a tool for measuring aviation auxiliary products, which aims to solve the problems that in the related art, the transverse clamping and the longitudinal clamping of aviation auxiliary products are controlled and operated respectively by a worker in a moving position, the process is complicated, and the use is very inconvenient.
The embodiment of the application adopts the following technical scheme:
the tool for measuring the aviation auxiliary material product comprises a tool body for containing the aviation auxiliary material product; the transverse clamping mechanism is connected to the tool body and used for transversely clamping the aviation auxiliary material product; the longitudinal clamping mechanism is connected to the tool body and used for longitudinally clamping the aviation auxiliary material product; the control mechanism is connected to the tool body and used for intensively controlling the transverse clamping mechanism and the longitudinal clamping mechanism, the control mechanism comprises a first rotating cylinder and a second rotating cylinder, a transverse driving assembly, a longitudinal driving assembly and a synchronous driving assembly are arranged between the first rotating cylinder and the second rotating cylinder, the transverse driving assembly is used for driving the transverse clamping mechanism to operate, the longitudinal driving assembly is used for driving the longitudinal clamping mechanism to operate, and the synchronous driving assembly is used for simultaneously driving the transverse clamping mechanism and the longitudinal clamping mechanism to operate; and the reading assembly is arranged on the transverse clamping mechanism and the longitudinal clamping mechanism and is used for reading the length value and the width value of the aviation auxiliary material product.
The beneficial effects of the invention are as follows: when using, the first rotary cylinder of drive clockwise rotation can drive vertical drive assembly for vertical fixture carries out vertical centre gripping to aviation auxiliary material product, and the anticlockwise rotation of drive first rotary cylinder can drive horizontal drive assembly, makes horizontal fixture carry out horizontal centre gripping to aviation auxiliary material product, promotes first rotary cylinder and reciprocates, and horizontal drive assembly and vertical drive assembly can't normal operating, can drive horizontal fixture and vertical fixture synchronous operation through synchronous drive assembly this moment, thereby relieve the centre gripping to aviation auxiliary material product, need not the staff and move the position and carry out the control operation respectively, and it is more convenient to use.
Preferably, the transverse driving assembly comprises a first bevel gear connected to the outer side of the second rotating cylinder, a second bevel gear connected to the transverse clamping mechanism, a first tooth set arranged on the outer side of the second rotating cylinder, and a first pushing tooth and a first blocking part connected to the inner side of the first rotating cylinder, wherein the first rotating cylinder rotates anticlockwise, the first blocking part blocks the first pushing tooth, and the first pushing tooth can push the first tooth set to enable the second rotating cylinder to rotate anticlockwise, so that the transverse clamping mechanism is driven to operate. The effect is that: the transverse clamping mechanism can be driven to operate through the transverse driving assembly, so that the aviation auxiliary material product is transversely clamped.
Preferably, the longitudinal driving assembly comprises a second tooth set arranged on the longitudinal clamping mechanism, and a second pushing tooth and a second blocking part which are connected to the inner side of the first rotating cylinder, the first rotating cylinder rotates clockwise, the second blocking part blocks the second pushing tooth, and the second pushing tooth can push the second tooth set to enable the longitudinal clamping mechanism to operate. The effect is that: the longitudinal clamping mechanism can be driven to operate through the longitudinal driving assembly, so that the aviation auxiliary material product is longitudinally clamped.
Preferably, the synchronous driving assembly comprises a third tooth set arranged on the inner side of the second rotating cylinder, a fourth tooth set arranged on the longitudinal clamping mechanism and a flat gear, wherein when the flat gear is in meshed connection with the third tooth set and the fourth tooth set, the transverse driving assembly and the longitudinal driving assembly cannot operate, and the flat gear can drive the third tooth set and the fourth tooth set to rotate so as to enable the transverse clamping mechanism and the longitudinal clamping mechanism to operate synchronously. The effect is that: the operation of the transverse clamping mechanism and the longitudinal clamping mechanism can be controlled simultaneously through the synchronous driving assembly, so that the clamping of the aviation auxiliary material product is relieved, and the aviation auxiliary material product can be conveniently disassembled.
Preferably, the first rotating cylinder and the second rotating cylinder are coaxially arranged, and the first rotating cylinder is sleeved on the outer side of the second rotating cylinder.
Preferably, the transverse clamping mechanism comprises a first bidirectional screw rod and two transverse clamping parts connected to the first bidirectional screw rod, and the first bidirectional screw rod can drive the two transverse clamping parts to move reversely by rotating. The effect is that: two transverse clamping parts can be driven to be close to each other or to be far away from each other through the first bidirectional screw rod so as to transversely clamp aviation auxiliary material products.
Preferably, the longitudinal clamping mechanism comprises a second bidirectional screw rod and two longitudinal clamping parts connected to the second bidirectional screw rod, and the rotation of the second bidirectional screw rod can drive the two longitudinal clamping parts to move reversely. The effect is that: the two longitudinal clamping parts can be driven to be close to or far away from each other through the second bidirectional screw rod so as to longitudinally clamp the aviation auxiliary material product.
Preferably, the reading assembly comprises a first scale mark arranged on the transverse clamping mechanism and a second scale mark arranged on the longitudinal clamping mechanism. The effect is that: the reading assembly is used for conveniently reading the width value and the length value of the aviation auxiliary material product.
Preferably, the tool body comprises a containing part, a notch and a limiting chute are arranged on the containing part, the notch is used for installing the transverse clamping mechanism, and the limiting chute is used for installing the longitudinal clamping mechanism.
Preferably, the bottom of the containing part is connected with supporting legs for supporting the containing part.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It will be apparent to those skilled in the art from this disclosure that the drawings described below are merely exemplary and that other embodiments may be derived from the drawings provided without undue effort.
The structures, proportions, sizes, etc. shown in the present specification are shown only for the purposes of illustration and description, and are not intended to limit the scope of the invention, which is defined by the claims, so that any structural modifications, changes in proportions, or adjustments of sizes, which do not affect the efficacy or the achievement of the present invention, should fall within the ambit of the technical disclosure.
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic perspective view of the front view of the present invention;
FIG. 3 is a schematic perspective view of the transverse and longitudinal clamping mechanisms of the present invention;
FIG. 4 is an enlarged schematic view of the structure of FIG. 3A according to the present invention;
FIG. 5 is a schematic view of the transverse driving assembly of the present invention;
FIG. 6 is an enlarged schematic view of the structure of FIG. 5B according to the present invention;
FIG. 7 is a schematic perspective view of a synchronous drive assembly according to the present invention;
fig. 8 is a schematic perspective view of a synchronous driving assembly according to the present invention.
In the figure: 1. a tool body; 11. a containing part; 12. support legs; 13. a notch; 14. limiting sliding grooves; 2. a transverse clamping mechanism; 21. a lateral clamping portion; 22. a movable part; 23. the first bidirectional screw rod; 24. a first transmission member; 3. a longitudinal clamping mechanism; 31. a longitudinal clamping portion; 32. a support part; 33. a second bi-directional lead screw; 4. a control mechanism; 41. a mounting base; 42. a first rotary drum; 43. a second rotary drum; 44. a lateral drive assembly; 441. a first bevel gear; 442. a second bevel gear; 443. a first tooth set; 444. a first mounting portion; 445. a first pushing tooth; 446. a first blocking portion; 45. a longitudinal drive assembly; 451. a second tooth set; 452. a second mounting portion; 453. a second pushing tooth; 454. a second blocking portion; 46. a synchronous drive assembly; 461. a third tooth set; 462. a fourth tooth set; 463. a flat gear; 464. a connecting shaft; 465. a first driving section; 47. a second driving section; 48. a positioning part; 5. a reading assembly; 51. a first scale line; 52. and a second graduation mark.
Detailed Description
The following describes the embodiments of the present invention further with reference to the drawings.
1-8, a tool for measuring aviation auxiliary products; including the frock body 1 for splendid attire aviation auxiliary material product is connected with horizontal fixture 2 on the frock body 1 for to the horizontal centre gripping of aviation auxiliary material product, be connected with vertical fixture 3 on the frock body 1, be used for the vertical centre gripping of aviation auxiliary material product, be connected with control mechanism 4 on the frock body 1, be used for centralized control horizontal fixture 2 and vertical fixture 3, need not the staff and move the position and operate the control respectively, it is convenient to use, be provided with reading subassembly 5 on horizontal fixture 2 and the vertical fixture 3, be used for reading aviation auxiliary material product's length value and width value.
As shown in fig. 1 and 2, the tool body 1 comprises a holding portion 11 for supporting aviation auxiliary products, the bottom of the holding portion 11 is connected with supporting legs 12 for supporting the holding portion 11, notches 13 are formed in the front side and the rear side of the holding portion 11 and used for installing a transverse clamping portion 21, a limiting sliding groove 14 is formed in the top of the holding portion 11, the limiting sliding groove 14 is perpendicular to the notches 13, and the longitudinal clamping mechanism 3 can be limited.
As shown in fig. 1-3, the transverse clamping mechanism 2 includes two transverse clamping portions 21 that can be close to each other or far away from each other and two first bidirectional screw rods 23 that are respectively connected in two notches 13 in a rotating way, the two transverse clamping portions 21 are respectively connected on two sections of threads with opposite screw directions on the first bidirectional screw rods 23 in a threaded way, a first transmission piece 24 is connected between the two first bidirectional screw rods 23, the two first bidirectional screw rods 23 can synchronously and co-rotate through the first transmission piece 24, the transverse clamping portions 21 are in an inverted U shape and are used for avoiding the longitudinal clamping mechanism 3, a plurality of movable portions 22 are inserted into the inner top sides of the transverse clamping portions 21, the lower half portions of the movable portions 22 are triangular, and the front side and the rear side of the lower half portions of the movable portions 22 are inclined planes, and the movable portions 22 can prevent aviation auxiliary material products from passing through the transverse clamping portions 21, so that the auxiliary clamping mechanism 2 can effectively clamp aviation material products.
When one of the first two-way lead screws 23 rotates, the other first two-way lead screw 23 simultaneously rotates in the same direction through the first transmission piece 24, at the moment, the two transverse clamping parts 21 are driven to simultaneously move reversely, and when the two transverse clamping parts 21 are close to each other, the aviation auxiliary material products are transversely clamped.
As shown in fig. 1-3, the longitudinal clamping mechanism 3 includes a longitudinal clamping portion 31 that can be close to each other or far away from each other, and a supporting portion 32 connected to the bottom of the accommodating portion 11, where the two longitudinal clamping portions 31 are both slidably connected to the limiting chute 14, a second bidirectional screw 33 is rotatably connected to the supporting portion 32, the two longitudinal clamping portions 31 are respectively screwed onto two sections of threads of the second bidirectional screw 33 with opposite screw directions, the longitudinal clamping portions 31 respectively penetrate through the two transverse clamping portions 21, the top of the longitudinal clamping portion 31 is in a triangle shape, both front and rear sides of the top of the longitudinal clamping portion 31 are inclined planes, and the longitudinal clamping portion 31 can push the movable portion 22 to move upwards, so that the longitudinal clamping portion 31 can cross the movable portion 22.
The second bidirectional screw rod 33 rotates to drive the two longitudinal clamping parts 31 to move reversely, and the aviation auxiliary product is longitudinally clamped when the two longitudinal clamping parts 31 are close to each other.
As shown in fig. 1-3, the reading assembly 5 includes a first scale line 51 disposed on the transverse clamping portion 21, the first scale line 51 being used to read the width value of the aviation auxiliary product, and a second scale line 52 disposed on the longitudinal clamping portion 31, the second scale line 52 being used to read the length value of the aviation auxiliary product.
As shown in fig. 1-8, the control mechanism 4 includes a mounting seat 41 connected to the front end of the bottom of the containing portion 11, the mounting seat 41 is in a U shape, the inner rear side of the mounting seat 41 is rotatably connected with a second rotating cylinder 43, the front side of the mounting seat 41 is inserted with a first rotating cylinder 42, the front end of the outer side of the first rotating cylinder 42 is connected with a second driving portion 47 so as to drive the first rotating cylinder 42, the first rotating cylinder 42 is sleeved on the outer side of the second rotating cylinder 43 and is not in contact with the second rotating cylinder 43, the second rotating cylinder 43 is coaxially arranged with the first rotating cylinder 42, the second bidirectional screw 33 extends into the inner side of the second rotating cylinder 43, and the second bidirectional screw 33 is coaxially arranged with the second rotating cylinder 43, a transverse driving assembly 44, a longitudinal driving assembly 45 and a synchronous driving assembly 46 are connected between the second rotating cylinder 43 and the first rotating cylinder 42, the transverse driving assembly 44 is used for driving the transverse clamping mechanism 2, the longitudinal driving assembly 45 is used for driving the longitudinal clamping mechanism 3, the synchronous driving assembly 46 can simultaneously drive the transverse clamping mechanism 2 and the longitudinal clamping mechanism 3, the first rotating cylinder 42 is sleeved on the outer side of the first rotating cylinder 42 and is not in contact with the longitudinal assembly 48, and the front side 48 is positioned on the front side of the mounting seat 48, and can not normally contact with the front side 48 of the first rotating cylinder 45, and can be positioned on the front side of the mounting seat 48, and the front side of the front assembly is positioned normally, and the front side of the longitudinal assembly is positioned on the front side of the front assembly 48 can be positioned normally, and can be positioned with the front side 48 is positioned on the front side 48.
With continued reference to fig. 1-8, the transverse driving assembly 44 includes a first bevel gear 441 connected to the outside of the second rotating cylinder 43, a second bevel gear 442 connected to the front side first bi-directional screw 23, a first tooth set 443 disposed on the outside of the second rotating cylinder 43, and a first mounting portion 444 connected to the inside of the first rotating cylinder 42, the first bevel gear 441 and the second bevel gear 442 are engaged with each other, the first mounting portion 444 is connected with a first pushing tooth 445 and a first blocking portion 446, the first pushing tooth 445 is rotatably connected with the first mounting portion 444 through a first rotation shaft, and a first torsion spring is connected between the first pushing tooth 445 and the first mounting portion 444 for driving the first pushing tooth 445 to reset (not shown in the drawings).
When the first rotating cylinder 42 rotates clockwise, the first blocking part 446 does not block the first pushing teeth 445, the first pushing teeth 445 continuously shake on the first tooth set 443 under the action of the first torsion spring, when the first rotating cylinder 42 rotates anticlockwise, the first pushing teeth 445 are blocked by the first blocking part 446, at this time, the first pushing teeth 445 can push the first tooth set 443 to enable the second rotating cylinder 43 to rotate anticlockwise, and when the second rotating cylinder 43 rotates, the first bevel gear 441 and the second bevel gear 442 are driven to mesh and drive, so that the first bidirectional screw rod 23 rotates, and the first bidirectional screw rod 23 drives the two transverse clamping parts 21 to approach each other and transversely clamp aviation auxiliary materials.
With continued reference to fig. 1-8, the longitudinal driving assembly 45 includes a second tooth set 451 disposed outside the second bidirectional screw 33, and a second mounting portion 452 connected to the inner side of the first rotating barrel 42, wherein the second mounting portion 452 is connected to a second pushing tooth 453 and a second blocking portion 454, the second pushing tooth 453 is rotatably connected to the second mounting portion 452 through a second rotating shaft, and a second torsion spring is connected between the second pushing tooth 453 and the second mounting portion 452, so as to drive the second pushing tooth 453 to reset (not shown in the drawings).
When the first rotating cylinder 42 rotates anticlockwise, the second blocking part 454 does not block the second pushing teeth 453, the second pushing teeth 453 continuously shake on the second tooth set 451 under the action of the second torsion spring, when the first rotating cylinder 42 rotates clockwise, the second pushing teeth 453 are blocked by the second blocking part 454, at this time, the second pushing teeth 453 can push the second tooth set 451, so that the second bidirectional screw 33 rotates clockwise, and the two longitudinal clamping parts 31 are driven to be close to each other through the clockwise rotation of the second bidirectional screw 33, and longitudinally clamp aviation auxiliary products.
With continued reference to fig. 1-8, the synchronous drive assembly 46 includes a third set of teeth 461 disposed inside the second rotating barrel 43, a fourth set of teeth 462 disposed outside the second bi-directional screw 33, and a flat gear 463, the flat gear 463 being capable of meshing with the third set of teeth 461 and the fourth set of teeth 462, a connecting shaft 464 being connected to a front side of the flat gear 463, the connecting shaft 464 being rotatably connected to the first rotating barrel 42, and the connecting shaft 464 passing through a front side of the first rotating barrel 42 and being connected to a first drive portion 465.
The first rotating cylinder 42 is pushed backwards to drive the flat gear 463 to move between the third tooth set 461 and the fourth tooth set 462, the third tooth set 461 and the fourth tooth set 462 are connected with the flat gear 463 in a meshed mode, at the moment, the first driving part 465 is manually driven to drive the connecting shaft 464 to rotate clockwise, meshing transmission between the flat gear 463 and the third tooth set 461 and the fourth tooth set 462 can be driven, the second bidirectional screw 33 rotates anticlockwise, when the second rotating cylinder 43 rotates clockwise, the second bidirectional screw 33 drives the two longitudinal clamping parts 31 to be away from each other when rotating anticlockwise, so that longitudinal clamping of an aviation auxiliary product is eliminated, when the second rotating cylinder 43 rotates clockwise, the two transverse clamping parts 21 can be away from each other, transverse clamping of the aviation auxiliary product is eliminated, and the clamping of the aviation auxiliary product is quickly eliminated, so that the aviation auxiliary product is detached.
In specific use, firstly, aviation auxiliary material products are placed on the top of the containing part 11, the second driving part 47 is manually driven to drive the first rotating cylinder 42 to rotate clockwise, the second pushing teeth 453 are blocked by the second blocking part 454, at the moment, the second pushing teeth 453 can push the second tooth group 451 to enable the second bidirectional screw 33 to rotate clockwise, the two longitudinal clamping parts 31 are driven to be close to each other through the clockwise rotation of the second bidirectional screw 33 and longitudinally clamp the aviation auxiliary material products, the second driving part 47 is manually driven to drive the first rotating cylinder 42 to rotate anticlockwise, the first pushing teeth 445 are blocked by the first blocking part 446, at the moment, the first pushing teeth 445 can push the first tooth group 443 to enable the second rotating cylinder 43 to rotate anticlockwise, and the second rotating cylinder 43 drives the first bevel gear 441 and the second bevel gear 442 to mesh and drive when rotating, the first bidirectional screw 23 is rotated, so that the first bidirectional screw 23 drives the two transverse clamping parts 21 to approach each other, and transversely clamps the aviation auxiliary material product, after clamping, the width value and the length value of the aviation auxiliary material product are read by observing the first scale line 51 on the transverse clamping part 21 and the second scale line 52 on the longitudinal clamping part 31, after measuring, the first rotating cylinder 42 is pushed forward, the flat gear 463 is inserted between the third tooth set 461 and the fourth tooth set 462, the third tooth set 461 and the fourth tooth set 462 are meshed with the flat gear 463, at the moment, the first driving part 465 is manually driven to drive the connecting shaft 464 to rotate clockwise, the flat gear 463 can be driven to rotate clockwise with the meshed transmission between the third tooth set 461 and the fourth tooth set 462, when the second bidirectional screw 33 rotates anticlockwise, the second rotating cylinder 43 rotates clockwise, the second bidirectional screw 33 drives the two longitudinal clamping parts 31 to be away from each other when rotating anticlockwise, so that the longitudinal clamping of the aviation auxiliary product is released, and the second rotating cylinder 43 can drive the two transverse clamping parts 21 to be away from each other when rotating clockwise, so that the transverse clamping of the aviation auxiliary product is released.
Claims (10)
1. Frock is used in aviation auxiliary material product measurement, its characterized in that includes:
the tool body is used for accommodating aviation auxiliary products;
the transverse clamping mechanism is connected to the tool body and used for transversely clamping the aviation auxiliary material product;
the longitudinal clamping mechanism is connected to the tool body and used for longitudinally clamping the aviation auxiliary material product;
the control mechanism is connected to the tool body and used for intensively controlling the transverse clamping mechanism and the longitudinal clamping mechanism, the control mechanism comprises a first rotating cylinder and a second rotating cylinder, a transverse driving assembly, a longitudinal driving assembly and a synchronous driving assembly are arranged between the first rotating cylinder and the second rotating cylinder, the transverse driving assembly is used for driving the transverse clamping mechanism to operate, the longitudinal driving assembly is used for driving the longitudinal clamping mechanism to operate, and the synchronous driving assembly is used for simultaneously driving the transverse clamping mechanism and the longitudinal clamping mechanism to operate;
and the reading assembly is arranged on the transverse clamping mechanism and the longitudinal clamping mechanism and is used for reading the length value and the width value of the aviation auxiliary material product.
2. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the transverse driving assembly comprises a first bevel gear connected to the outer side of the second rotating cylinder, a second bevel gear connected to the transverse clamping mechanism, a first tooth set arranged on the outer side of the second rotating cylinder, and a first pushing tooth and a first blocking part connected to the inner side of the first rotating cylinder, wherein the first rotating cylinder rotates anticlockwise, the first blocking part blocks the first pushing tooth, and the first pushing tooth can push the first tooth set to enable the second rotating cylinder to rotate anticlockwise, so that the transverse clamping mechanism is driven to operate.
3. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the longitudinal driving assembly comprises a second tooth set arranged on the longitudinal clamping mechanism, and a second pushing tooth and a second blocking part which are connected to the inner side of the first rotating cylinder, the first rotating cylinder rotates clockwise, the second blocking part blocks the second pushing tooth, and the second pushing tooth can push the second tooth set to enable the longitudinal clamping mechanism to operate.
4. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the synchronous drive assembly comprises a third tooth set arranged on the inner side of the second rotating cylinder, a fourth tooth set arranged on the longitudinal clamping mechanism and a flat gear, wherein when the flat gear is meshed with the third tooth set and the fourth tooth set, the transverse drive assembly and the longitudinal drive assembly cannot operate, and the flat gear can drive the third tooth set and the fourth tooth set to operate synchronously with the longitudinal clamping mechanism.
5. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the first rotating cylinder and the second rotating cylinder are coaxially arranged, and the first rotating cylinder is sleeved on the outer side of the second rotating cylinder.
6. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the transverse clamping mechanism comprises a first bidirectional screw rod and two transverse clamping parts connected to the first bidirectional screw rod, and the first bidirectional screw rod can rotate to drive the two transverse clamping parts to move reversely.
7. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the longitudinal clamping mechanism comprises a second bidirectional screw rod and two longitudinal clamping parts connected to the second bidirectional screw rod, and the rotation of the second bidirectional screw rod can drive the two longitudinal clamping parts to move reversely.
8. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the reading assembly comprises a first scale mark arranged on the transverse clamping mechanism and a second scale mark arranged on the longitudinal clamping mechanism.
9. The tooling for measuring aviation auxiliary products according to claim 1, wherein: the fixture body comprises a containing part, wherein a notch and a limiting chute are arranged on the containing part, the notch is used for installing a transverse clamping mechanism, and the limiting chute is used for installing a longitudinal clamping mechanism.
10. The tooling for measuring aviation auxiliary products according to claim 9, wherein: the bottom of the containing part is connected with supporting legs for supporting the containing part.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310775493.5A CN116499337B (en) | 2023-06-28 | 2023-06-28 | Frock is used in measurement of aviation auxiliary material product |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310775493.5A CN116499337B (en) | 2023-06-28 | 2023-06-28 | Frock is used in measurement of aviation auxiliary material product |
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| CN116499337A true CN116499337A (en) | 2023-07-28 |
| CN116499337B CN116499337B (en) | 2023-09-08 |
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| DE202017004876U1 (en) * | 2017-09-19 | 2017-12-04 | Gmt Global Inc. | jig |
| CN110153489A (en) * | 2019-06-26 | 2019-08-23 | 青岛黄海学院 | A kind of electrical equipment production cutter device and cutting method |
| CN110375653A (en) * | 2019-09-03 | 2019-10-25 | 长沙秉书智能科技有限公司 | A kind of detection device of wheel hub and auto parts and components product |
| CN111409913A (en) * | 2020-04-27 | 2020-07-14 | 迅得机械（东莞）有限公司 | Automatic auxiliary material placing device |
| CN213164213U (en) * | 2020-08-19 | 2021-05-11 | 苏州派恩精密机械有限公司 | Auxiliary clamping tool for processing step type blind hole |
| CN213135450U (en) * | 2020-09-18 | 2021-05-07 | 聊城市沃尔润激光科技有限公司 | Workpiece clamping device of laser marking machine |
| CN112355939A (en) * | 2020-11-16 | 2021-02-12 | 株洲华信精密工业股份有限公司 | Stable clamping center device for spare and accessory part machining |
| CN113770774A (en) * | 2021-08-16 | 2021-12-10 | 晟光科技股份有限公司 | Numerical control is holder for CNC processing |
| CN115674053A (en) * | 2022-11-22 | 2023-02-03 | 深圳市信捷达金属制品有限公司 | Compound frock of aeronautical material processing |
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