CN113650803B - Mechanical positioning and locking device of aircraft tool - Google Patents
Mechanical positioning and locking device of aircraft tool Download PDFInfo
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- CN113650803B CN113650803B CN202110988222.9A CN202110988222A CN113650803B CN 113650803 B CN113650803 B CN 113650803B CN 202110988222 A CN202110988222 A CN 202110988222A CN 113650803 B CN113650803 B CN 113650803B
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- 230000007246 mechanism Effects 0.000 claims abstract description 16
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical group [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 29
- 230000006835 compression Effects 0.000 claims description 14
- 238000007906 compression Methods 0.000 claims description 14
- 230000006698 induction Effects 0.000 claims description 5
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000006073 displacement reaction Methods 0.000 abstract description 12
- 238000009434 installation Methods 0.000 description 14
- 230000001939 inductive effect Effects 0.000 description 8
- 230000008859 change Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 4
- 238000005299 abrasion Methods 0.000 description 3
- 229910052802 copper Inorganic materials 0.000 description 3
- 239000010949 copper Substances 0.000 description 3
- 239000000047 product Substances 0.000 description 3
- 230000009471 action Effects 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012467 final product Substances 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Abstract
The invention discloses a mechanical positioning and locking device of an aircraft tool, which comprises a locking assembly and a tool joint assembly, wherein the locking assembly comprises a locking sleeve, a handle mechanism, an end cover, a positioning ring and a locking ring which are sequentially arranged in the locking sleeve from bottom to top; the locking ring is rotatably arranged in the locking sleeve, a through hole is formed in the side wall of the locking sleeve, and the handle mechanism penetrates through the through hole and is connected with the locking ring; the circumference of the lateral wall of the opposite side of frock joint has set gradually the locating pin, locating pin from top to bottom, the locating clip groove has been seted up to the locating ring correspondence locating pin, the inner wall of locking ring corresponds the locating pin and is provided with the locking groove of slope, and the highest department of locking groove link up is provided with dodges the hole. The invention uses the locating pin and the locking pin as the realization medium of the locating and locking functions, and controls the tool joint assembly to generate axial displacement to complete locking by rotating the handle, thereby having the characteristics of stable and reliable structure, convenient operation and good repeated locating property.
Description
Technical Field
The invention belongs to the technical field of aviation manufacturing assembly devices, and relates to a mechanical positioning and locking device of an aircraft tool.
Background
In the manufacturing fields of large aircrafts, ships and the like, the products are generally manufactured in a sectional manner due to the irregularity and complexity of the appearance of the products, and then the final products are formed by assembling the components in a butt joint way. In the process of adjusting and assembling the large parts of the airplane, the mode of adjusting and assembling the pose of the large parts by adopting a numerical control positioner is becoming wider and wider, and in the application scene of using a special airplane tool as a large part assembling connecting piece, the method can be realized by fixing the special airplane tool on the special numerical control positioner as a reference standard for the adjusting and assembling movement of the large parts, so that the pose movement precision of the large parts and the positioning precision of the tool are important factors for ensuring that the final product is accurately assembled. In order to ensure that the positioning precision of the aircraft tool and the repeated positioning performance of repeated disassembly and assembly meet the assembling requirement, a mechanical positioning and locking device is adopted to realize the accurate positioning and reliable locking of the aircraft tool, so that the attitude adjustment assembling precision and the comprehensive efficiency of the large aircraft parts are improved.
Disclosure of Invention
The invention aims to provide a mechanical positioning and locking device of an aircraft tool, and aims to solve the problems.
The tool joint assembly is locked by using the positioning pin and the locking pin as the realization media of the positioning and locking functions and controlling the tool joint assembly to generate axial displacement through rotating the handle, and has the characteristics of stable and reliable structure, convenient operation and good repeated positioning property.
The invention is realized mainly by the following technical scheme:
the mechanical positioning and locking device for the aircraft tool comprises a locking assembly and a tool joint assembly, wherein the tool joint assembly comprises a tool joint, a positioning pin and a locking pin, and the locking assembly comprises a locking sleeve, a handle mechanism, an end cover, a positioning ring and a locking ring which are sequentially arranged inside the locking sleeve from bottom to top; the top of the locking sleeve is provided with an annular end cover, the locking ring is rotatably arranged in the locking sleeve, the locking sleeve is provided with a through hole along the circumferential direction, and the handle mechanism penetrates through the through hole and is connected with the locking ring; one side of the tool joint is connected with an aircraft tool, the other side of the tool joint stretches into the locking sleeve and is connected with the locking sleeve, a locking pin and a positioning pin are sequentially arranged on the circumference of the side wall of the other side of the tool joint from top to bottom, a positioning clamping groove is formed in the positioning ring corresponding to the positioning pin, an inclined locking groove is formed in the inner wall of the locking ring corresponding to the locking pin, and an avoidance hole is formed in the highest position of the locking groove in a penetrating mode.
In the locking process, the outer cylindrical surface of the locking pin is kept in contact with the inclined surface above the locking groove; one end of the tool joint is provided with the locating pin and the locking pin, and the other end of the tool joint is fixedly connected with the aircraft tool. According to the invention, the locating pin and the locking pin are used as a medium for realizing the locating and locking functions, and the tool joint assembly is controlled to generate axial displacement by rotating the handle mechanism to complete locking.
In order to better realize the invention, further, the locking ring consists of a plurality of arc-shaped inclined blocks, the adjacent arc-shaped inclined blocks are connected through compression springs, and inclined locking grooves are formed in the arc-shaped inclined blocks; the number of the arc-shaped inclined blocks is greater than or equal to the number of the locking pins.
According to the invention, the locating pin and the locking pin are used as the realization mediums of locating and locking functions, and the rotating handle controls the inclined plane at the upper part of the locking groove of the arc-shaped inclined block to change in the thickness direction, so that the tool joint assembly generates axial displacement to complete locking. The arc-shaped inclined blocks are flexibly connected through the compression springs, and the inclined planes of the locking grooves of each arc-shaped inclined block are guaranteed to be reliably contacted with the locking pins. In the in-service use, the setting position of locking pin is not necessarily regular, has certain error or dislocation, in order to adapt to different installation environment, realizes flexible installation through setting up compression spring between adjacent arc sloping block, has further improved the range of application of locking, has improved the installation accuracy, has better practicality.
In order to better realize the invention, the locking sleeve is further provided with a plurality of through holes corresponding to the arc-shaped inclined blocks along the circumferential direction.
In order to better realize the invention, further, the two ends of the through hole are respectively provided with a stepped hole, the handle mechanism comprises a handle, a handle sleeve and a return spring, one end of the handle penetrates through the through hole and is connected with the locking ring, the other end of the handle is connected with the handle, the handle sleeve is sleeved on the outer side of the handle in a sliding manner, the return spring is arranged between the handle sleeve and the handle, and the outer diameter of the handle sleeve is larger than the width of the through hole and smaller than or equal to the width of the stepped hole.
In order to better realize the invention, further, the bottom of the stepped hole is provided with a sensing groove, and a proximity sensing switch is arranged in the sensing groove.
The handle is characterized in that two ends of a through hole formed in the side wall of the locking sleeve are provided with stepped holes which are expanded along two sides in the axial direction, and when the handle rotates to the stepped holes, the reset spring can rebound the handle sleeve, and the handle can be fixed at the stepped holes. The proximity inductive switch is arranged on the locking sleeve, and the periphery of the handle sleeve is an inductive detection point of the proximity inductive switch. The proximity inductive switch is the prior art, so the description is not repeated.
In order to better realize the invention, further, the outer side wall of the locking ring is provided with a threaded hole, and one end of the handle is in threaded connection with the threaded hole.
In order to better realize the invention, the tool joint further comprises a positioning surface and a connecting sleeve arranged below the positioning surface, wherein a plurality of locking pins and positioning pins are arranged on the side wall of the connecting sleeve from top to bottom in sequence along the circumferential direction; the locating surface corresponds the aircraft frock and is provided with a plurality of installation connecting hole along circumference.
Blind holes along the radial direction are formed in the side wall of the bottom of the connecting sleeve, corresponding to the locking pin and the positioning pin, and the locking screw can penetrate through the blind holes to position the locking pin and the positioning pin.
In order to better realize the invention, further, the top side wall of the locking sleeve is provided with positioning holes along the circumferential direction, the end cover is correspondingly provided with a plurality of connecting and mounting holes along the circumferential direction, and the end cover is fixedly connected with the locking sleeve through bolts.
The end cover with locking sleeve fixed connection, the end cover covers the copper circle with locking sleeve surrounding edge, the end cover center is offered and is used for the dodge space that frock joint assembly passed through.
In order to better realize the invention, the locking assembly further comprises copper rings, wherein the copper rings are respectively arranged between the upper side and the lower side of the locking ring, the positioning ring and the end cover; the edge of copper circle is provided with a plurality of recess along circumference, the copper circle passes through the fixed setting of stop screw in locking sleeve inside. The copper ring can effectively reduce abrasion caused by rotation friction of the locking ring, and the flexibility of rotation of the handle can be adjusted by changing the thickness of the copper ring.
In order to better realize the invention, further, the top of the positioning ring is provided with a mounting groove corresponding to the locking ring, and a copper ring is arranged between the locking ring and the mounting groove.
The working principle of the invention is as follows:
make locking component be in the initial position of unclamping the state, put into frock joint subassembly and make the locating pin get into locking sleeve's location draw-in groove, the locking pin is located arc sloping block dodge downthehole, the handle sleeve makes reset spring be in compression state, the twist grip makes arc sloping block rotate, the inclined plane of arc sloping block's locking groove top drives the locking pin through following thickness direction's change, make frock joint subassembly produce axial displacement, reach locking state after the locating surface that end cover surface and frock connect is hugged closely, the handle gets into the shoulder hole at this moment, loosen the handle sleeve, handle sleeve resets under reset spring bullet's effect, handle sleeve joint is in the shoulder hole at this moment, the handle can't produce not hard up or rollback, effectively stabilize locking state. The proximity inductive switch installed at the inductive groove can monitor and feed back the status signal through the outer circumferential surface of the inductive handle sleeve. After the work is completed, the handle sleeve is lifted, so that the reset spring is compressed and deformed until the handle sleeve is separated from the stepped hole, the handle is reversely rotated, the arc-shaped inclined block is retracted to the initial position, and the tool joint assembly can axially withdraw at the moment, so that unlocking is realized.
The invention has the beneficial effects that:
(1) The tool joint assembly is locked by using the positioning pin and the locking pin as the realization mediums of the positioning and locking functions and controlling the tool joint assembly to generate axial displacement through rotating the handle, and the tool joint assembly has the characteristics of stable and reliable structure, convenient operation and good repeated positioning property;
(2) According to the invention, the handle is rotated to control the inclined plane at the upper part of the locking groove of the arc-shaped inclined block to change in the thickness direction, so that the tool joint assembly generates axial displacement to complete locking. The arc-shaped inclined blocks are flexibly connected through the compression springs, so that the inclined plane of the locking groove of each arc-shaped inclined block is ensured to be reliably contacted with the locking pin, and the practicability is better;
(3) When the handle rotates to the stepped hole, the return spring can rebound the handle sleeve, the handle can be fixed at the stepped hole, the position of the locking ring can be fixed, the locking state can be flexibly fixed, and the practicability is good;
(4) The copper ring can effectively reduce abrasion caused by rotation friction of the locking ring, and the flexibility of rotation of the handle can be adjusted by changing the thickness of the copper ring, so that the copper ring has good practicability;
(5) The invention adopts mechanical positioning and locking, uses the positioning pin and the locking pin as the realization media of positioning and locking functions, improves the positioning performance through the positioning pin and the positioning clamping groove, drives the arc-shaped inclined block to move through the handle to control the locking state, ensures the stability and reliability of the locking state through the reset spring, monitors and feeds back the locking state through the proximity sensing switch, and has better practicability.
Drawings
FIG. 1 is an exploded view of a tool joint assembly;
FIG. 2 is an exploded view of the locking assembly;
FIG. 3 is a schematic view of a three-dimensional assembly structure of the mechanical positioning and locking device of the present invention;
fig. 4 is a schematic sectional view of an assembly of the mechanical positioning and locking device of the present invention.
Wherein: 1. the locking sleeve is characterized by comprising a locking sleeve body, a handle sleeve body, a return spring, a handle, a copper ring, an arc-shaped inclined block, a compression spring, an end cover, a locating pin, a locking pin, a tool joint and a proximity induction switch.
1101. Positioning surface 1102, first stop screw mounting hole 1103, second stop screw mounting hole 1104, mounting connection hole;
101. the device comprises a through hole, a step hole, a sensing groove, a positioning hole, a positioning clamping groove and a positioning ring, wherein the through hole is 102, the step hole is 103, the sensing groove is 104, the positioning hole is 105, the positioning clamping groove is 106;
501. groove 601 dodges the hole, 602 the screw hole, 603 the inclined plane, 801 the connection installation hole site.
Detailed Description
Example 1:
1-4, the mechanical positioning and locking device of the aircraft tool comprises a locking assembly and a tool joint 11 assembly, wherein the tool joint 11 assembly comprises a tool joint 11, a positioning pin 9 and a locking pin 10, and the locking assembly comprises a locking sleeve 1, a handle mechanism, an end cover 8, a positioning ring 106 and a locking ring which are sequentially arranged inside the locking sleeve 1 from bottom to top; the top of the locking sleeve 1 is provided with an annular end cover 8, the locking ring is rotatably arranged in the locking sleeve 1, the locking sleeve 1 is circumferentially provided with a through hole 101, and the handle mechanism penetrates through the through hole 101 and is connected with the locking ring; one side of the tool joint 11 is connected with an aircraft tool, the other side of the tool joint extends into the locking sleeve 1 and is connected with the locking sleeve 1, a locking pin 10 and a positioning pin 9 are sequentially arranged on the side wall of the other side of the tool joint 11 from top to bottom in the circumferential direction, a positioning clamping groove 105 is formed in the positioning ring 106 corresponding to the positioning pin 9, an inclined locking groove is formed in the inner wall of the locking ring corresponding to the locking pin 10, and an avoidance hole 601 is formed in the highest penetrating position of the locking groove.
Further, as shown in fig. 1, the tool joint 11 includes a positioning surface and a connecting sleeve disposed below the positioning surface, and a plurality of locking pins 10 and positioning pins 9 are sequentially disposed on a side wall of the connecting sleeve from top to bottom along a circumferential direction; the locating surface is provided with a plurality of mounting connection holes 1104 corresponding to the aircraft tool along the circumferential direction. Blind holes in the radial direction are formed in the bottom side wall of the connecting sleeve, corresponding to the locking pin 10 and the positioning pin 9, and the locking screw can penetrate through the blind holes to position the locking pin 10 and the positioning pin 9.
The invention uses the locating pin 9 and the locking pin 10 as the realization media of the locating and locking functions, and controls the tool joint 11 assembly to generate axial displacement to complete locking by rotating the handle, thus the invention has the characteristics of stable and reliable structure, convenient operation and good repeated locating property. During the locking process, the outer cylindrical surface of the locking pin 10 is kept in contact with the inclined surface 603 above the locking groove; one end of the tool joint 11 is provided with the positioning pin 9 and the locking pin 10, and the other end of the tool joint is fixedly connected with an aircraft tool. The invention uses the locating pin 9 and the locking pin 10 as the realization media of the locating and locking functions, and controls the tool joint 11 assembly to generate axial displacement to complete locking by rotating the handle mechanism.
Example 2:
the embodiment is optimized on the basis of embodiment 1, as shown in fig. 2, the locking ring is composed of a plurality of arc-shaped inclined blocks 6, adjacent arc-shaped inclined blocks 6 are connected through compression springs 7, and inclined locking grooves are formed in the arc-shaped inclined blocks 6; the number of the arc-shaped inclined blocks 6 is greater than or equal to the number of the locking pins 10.
Further, the locking sleeve 1 is provided with a plurality of through holes 101 corresponding to the arc-shaped inclined blocks 6 along the circumferential direction.
According to the invention, the locating pin 9 and the locking pin 10 are used as the realization media of the locating and locking functions, and the rotating handle controls the inclined plane 603 at the upper part of the locking groove of the arc-shaped inclined block 6 to change in the thickness direction, so that the tool joint 11 assembly generates axial displacement to complete locking. The arc-shaped inclined blocks 6 are flexibly connected through the compression springs 7, so that the inclined plane 603 of the locking groove of each arc-shaped inclined block 6 is guaranteed to be reliably contacted with the locking pin 10. In the actual use, the setting position of the locking pin 10 is not necessarily regular, and certain errors or misplacement exists, so that the flexible installation is realized by arranging the compression spring 7 between the adjacent arc-shaped inclined blocks 6 in order to adapt to different installation environments, the application range of locking is further improved, the installation precision is improved, and the locking pin has good practicability.
Other portions of this embodiment are the same as those of embodiment 1, and thus will not be described in detail.
Example 3:
in this embodiment, optimization is performed on the basis of embodiment 1 or 2, as shown in fig. 2 and fig. 4, two ends of the through hole 101 are respectively provided with a stepped hole 102, the handle mechanism includes a handle, a handle 4, a handle sleeve 2 and a return spring 3, one end of the handle passes through the through hole 101 and is connected with the locking ring, the other end is connected with the handle 4, the handle sleeve 2 is slidably sleeved on the outer side of the handle, the return spring 3 is arranged between the handle sleeve 2 and the handle, and the outer diameter of the handle sleeve 2 is greater than the width of the through hole 101 and is smaller than or equal to the width of the stepped hole 102.
Further, a sensing groove 103 is formed at the bottom of the stepped hole 102, and a proximity sensing switch 110112 is arranged in the sensing groove 103.
The two ends of a through hole 101 formed in the side wall of the locking sleeve 1 are provided with stepped holes 102 which are expanded along the two sides in the axial direction, when the handle rotates to the stepped holes 102, the return spring 3 can rebound the handle sleeve 2, and the handle can be fixed at the stepped holes 102. The proximity switch 110112 is mounted on the locking sleeve 1, and the periphery of the handle sleeve 2 is an induction detection point of the proximity switch 110112. The proximity sensor 110112 is a prior art, and will not be described in detail.
Further, a threaded hole 602 is formed in the outer side wall of the locking ring, and one end of the handle is in threaded connection with the threaded hole 602.
Further, a positioning hole 104 is formed in the top side wall of the locking sleeve 1 along the circumferential direction, a plurality of connection mounting holes 801 are correspondingly formed in the end cover 8 along the circumferential direction, and the end cover 8 is fixedly connected with the locking sleeve 1 through bolts. The end cover 8 is fixedly connected with the locking sleeve 1, the end cover 8 covers the copper ring 5 and the surrounding edge of the locking sleeve 1, and an avoidance space for the tool joint 11 assembly to pass through is formed in the center of the end cover 8.
Other portions of this embodiment are the same as those of embodiment 1 or 2 described above, and thus will not be described again.
Example 4:
in this embodiment, optimization is performed on the basis of any one of embodiments 1 to 3, as shown in fig. 2, the locking assembly further includes copper rings 5, and copper rings 5 are respectively disposed between the upper and lower sides of the locking ring, the positioning ring 106, and the end cover 8; the edge of the copper ring 5 is provided with a plurality of grooves 501 along the circumferential direction, and the copper ring 5 is fixedly arranged inside the locking sleeve 1 through a stop screw.
Further, an installation groove is formed at the top of the positioning ring 106 corresponding to the locking ring, and a copper ring 5 is arranged between the locking ring and the installation groove.
The copper ring 5 can effectively reduce abrasion caused by rotation friction of the locking ring, and the flexibility of handle rotation can be adjusted by changing the thickness of the copper ring 5.
The working principle of the invention is as follows:
the locking assembly is in the initial position of the loosening state, the tool joint 11 assembly is placed in the positioning clamping groove 105 of the tool joint 11 assembly, the positioning pin 9 enters the locking sleeve 1, the locking pin 10 is located in the avoiding hole 601 of the arc-shaped inclined block 6, the handle sleeve 2 is pulled to enable the reset spring 3 to be in a compressed state, the arc-shaped inclined block 6 is rotated by rotating the handle, the inclined surface 603 above the locking groove of the arc-shaped inclined block 6 drives the locking pin 10 through the change along the thickness direction, the tool joint 11 assembly generates axial displacement, the locking state is achieved after the outer surface of the end cover 8 and the positioning surface of the tool joint 11 are close to each other, at the moment, the handle enters the stepped hole 102, the handle sleeve 2 is loosened, the handle sleeve 2 is reset under the action of the spring 3, the handle sleeve 2 is clamped in the stepped hole 102, at the moment, the handle cannot loose or fall back, and the locking state is effectively stabilized. The proximity sensor 110112 installed at the sensing groove 103 can perform status signal monitoring feedback through sensing the outer circumferential surface of the handle sleeve 2. After the work is completed, the handle sleeve 2 is lifted to enable the reset spring 3 to generate compression deformation until the handle sleeve 2 is separated from the stepped hole 102, the handle is reversely rotated to enable the arc-shaped inclined block 6 to retract to the initial position, and at the moment, the tool joint 11 assembly can axially retract to realize unlocking.
Other portions of this embodiment are the same as any of embodiments 1 to 3 described above, and thus will not be described again.
Example 5:
the utility model provides a mechanical type location locking device of aircraft frock, as shown in fig. 1-4, includes locking subassembly and frock joint 11 subassembly, frock joint 11 subassembly includes frock joint 11, locating pin 9, locking pin 10, the one end installation of frock joint 11 locating pin 9 and locking pin 10, and the other end and aircraft frock fixed connection. The locking assembly comprises a locking sleeve 1, a handle mechanism, an end cover 8, a positioning ring 106 and a locking ring which are sequentially arranged inside the locking sleeve 1 from bottom to top. The locking ring is rotatably arranged in the locking sleeve 1, a through hole 101 is formed in the locking sleeve 1 along the circumferential direction, and the handle mechanism penetrates through the through hole 101 and is connected with the locking ring; the locating ring 106 is provided with a locating clamping groove 105 corresponding to the locating pin 9, the inner wall of the locking ring is provided with an inclined locking groove corresponding to the locking pin 10, and the highest part of the locking groove is provided with a through hole 601.
Further, as shown in fig. 2 and 4, the two ends of the through hole 101 are respectively provided with a stepped hole 102, the handle mechanism comprises a handle, a handle 4, a handle sleeve 2 and a return spring 3, one end of the handle penetrates through the through hole 101 and is connected with the locking ring, the other end of the handle is connected with the handle 4, the handle sleeve 2 is sleeved on the outer side of the handle in a sliding manner, the return spring 3 is arranged between the handle sleeve 2 and the handle, and the outer diameter of the handle sleeve 2 is larger than the width of the through hole 101 and smaller than or equal to the width of the stepped hole 102.
Further, as shown in fig. 2, the locking ring is composed of a plurality of arc-shaped inclined blocks 6, and adjacent arc-shaped inclined blocks 6 are connected through compression springs 7, and inclined locking grooves are formed in the arc-shaped inclined blocks 6; the number of the arc-shaped inclined blocks 6 is greater than or equal to the number of the locking pins 10.
As shown in fig. 1, two sets of locating pins 9 and three sets of locking pins 10 are installed on the tool joint 11, wherein a first stop screw installation hole 1102 and a second stop screw installation hole 1103 are correspondingly arranged on the bottom side wall of the tool joint 11 respectively, and an installation connection hole 1104 for a special aircraft tool is arranged on the top of the tool joint 11.
As shown in fig. 2 and 3, through holes 101 extending along the circumferential direction are formed in the peripheral side wall of the locking sleeve 1, stepped holes 102 extending along the two sides of the axial direction are respectively formed at two ends of the through holes 101, three groups of arc-shaped inclined blocks 6 are mounted on the inner side of the locking sleeve 1, compression springs 7 are mounted between every two arc-shaped inclined blocks 6, copper rings 5 are mounted on the front side and the rear side of each arc-shaped inclined block 6, grooves 501 are formed in the edges of the copper rings 5, and the grooves 501 in the copper rings 5 are used for preventing the copper rings 5 from rotating. The end cover 8 is provided with a connecting and installing hole position 801 corresponding to the positioning hole 104 on the locking sleeve 1. The handle passes through the through hole 101 and is fixedly connected with the threaded hole 602 on the arc-shaped inclined block 6, and the arc-shaped inclined block 6 can be driven to rotate together by rotating the handle.
The specific working procedure of this example is as follows:
1) The locking working process is as follows: the locking assembly is in the initial position of the loosening state, the tool joint 11 assembly is placed in the positioning clamping groove 105 of the tool joint 11 assembly, the positioning pin 9 enters the locking sleeve 1, the locking pin 10 is located in the avoiding hole 601 of the arc-shaped inclined block 6, the handle sleeve 2 is pulled to enable the reset spring 3 to be in a compressed state, the arc-shaped inclined block 6 is rotated by rotating the handle, the inclined surface 603 above the locking groove of the arc-shaped inclined block 6 drives the locking pin 10 through the change along the thickness direction, the tool joint 11 assembly generates axial displacement, the locking state is achieved after the outer surface of the end cover 8 and the positioning surface of the tool joint 11 are close to each other, at the moment, the handle enters the stepped hole 102, the handle sleeve 2 is loosened, the handle sleeve 2 is reset under the action of the spring 3, the handle sleeve 2 is clamped in the stepped hole 102, at the moment, the handle cannot loose or fall back, and the locking state is effectively stabilized. The proximity sensor 110112 installed at the sensing groove 103 can perform state signal monitoring feedback through sensing the outer circumferential surface of the handle sleeve 2;
2) After the work is completed, the handle sleeve 2 is lifted to enable the reset spring 3 to generate compression deformation until the handle sleeve 2 is separated from the stepped hole 102, the handle is reversely rotated to enable the arc-shaped inclined block 6 to retract to the initial position, and at the moment, the tool joint 11 assembly can axially retract to realize unlocking.
The mechanical positioning and locking device for the aircraft tool can effectively control the locking and unlocking states through the handle; meanwhile, the reset spring 3 of the handle and the stepped hole 102 of the locking sleeve 1 can effectively stabilize the locking state, and the loosening or the rollback of the handle caused by vibration or false touch is avoided; the proximity inductive switch 110112 can realize effective feedback of the locking state and has better practicability.
The foregoing description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and any simple modification, equivalent variation, etc. of the above embodiment according to the technical matter of the present invention fall within the scope of the present invention.
Claims (9)
1. The mechanical positioning and locking device for the aircraft tool is characterized by comprising a locking assembly and a tool joint (11) assembly, wherein the tool joint (11) assembly comprises a tool joint (11), a positioning pin (9) and a locking pin (10), and the locking assembly comprises a locking sleeve (1), a handle mechanism, an end cover (8) and a positioning ring (106) and a locking ring which are sequentially arranged inside the locking sleeve (1) from bottom to top; the top of the locking sleeve (1) is provided with an annular end cover (8), the locking ring is rotatably arranged in the locking sleeve (1), the locking sleeve (1) is circumferentially provided with a through hole (101), and the handle mechanism penetrates through the through hole (101) and is connected with the locking ring; one side of the tool joint (11) is connected with an aircraft tool, the other side of the tool joint stretches into the locking sleeve (1) and is connected with the locking sleeve (1), a locking pin (10) and a positioning pin (9) are sequentially arranged on the circumference of the side wall of the other side of the tool joint (11) from top to bottom, a positioning clamping groove (105) is formed in the positioning ring (106) corresponding to the positioning pin (9), an inclined locking groove is formed in the inner wall of the locking ring corresponding to the locking pin (10), and an avoidance hole (601) is formed in the highest position of the locking groove in a penetrating mode;
the locking ring consists of a plurality of arc-shaped inclined blocks (6), wherein adjacent arc-shaped inclined blocks (6) are connected through compression springs (7), and inclined locking grooves are formed in the arc-shaped inclined blocks (6); the number of the arc-shaped inclined blocks (6) is more than or equal to the number of the locking pins (10).
2. The mechanical positioning and locking device of an aircraft tool according to claim 1, wherein the locking sleeve (1) is provided with a plurality of through holes (101) corresponding to the arc-shaped inclined blocks (6) along the circumferential direction.
3. The mechanical positioning and locking device of an aircraft tool according to claim 1 or 2, wherein stepped holes (102) are respectively formed in two ends of the through hole (101), the handle mechanism comprises a handle, a handle (4), a handle sleeve (2) and a return spring (3), one end of the handle penetrates through the through hole (101) and is connected with the locking ring, the other end of the handle is connected with the handle (4), the handle sleeve (2) is sleeved on the outer side of the handle in a sliding manner, a return spring (3) is arranged between the handle sleeve (2) and the handle, and the outer diameter of the handle sleeve (2) is larger than the width of the through hole (101) and smaller than or equal to the width of the stepped hole (102).
4. A mechanical positioning and locking device for an aircraft tool according to claim 3, wherein an induction groove (103) is arranged at the bottom of the stepped hole (102), and a proximity induction switch (12) is arranged in the induction groove (103).
5. A mechanical positioning and locking device for an aircraft tooling according to claim 3, wherein the outer side wall of the locking ring is provided with a threaded hole (602), and one end of the handle is in threaded connection with the threaded hole (602).
6. The mechanical positioning and locking device of the aircraft tool according to claim 1, wherein the tool joint (11) comprises a positioning surface (1101) and a connecting sleeve arranged below the positioning surface (1101), and a plurality of locking pins (10) and positioning pins (9) are sequentially arranged on the side wall of the connecting sleeve from top to bottom along the circumferential direction; the positioning surface (1101) is provided with a plurality of mounting connection holes (1104) corresponding to the aircraft tool along the circumferential direction.
7. The mechanical positioning and locking device of the aircraft tool according to claim 1, wherein positioning holes (104) are formed in the top side wall of the locking sleeve (1) along the circumferential direction, a plurality of connecting and mounting hole sites (801) are correspondingly formed in the end cover (8) along the circumferential direction, and the end cover (8) is fixedly connected with the locking sleeve (1) through bolts.
8. The mechanical positioning and locking device of the aircraft tool according to claim 1, wherein the locking assembly further comprises copper rings (5), and the copper rings (5) are respectively arranged between the upper side and the lower side of the locking ring, the positioning ring (106) and the end cover (8); the edge of the copper ring (5) is provided with a plurality of grooves (501) along the circumferential direction, and the copper ring (5) is fixedly arranged inside the locking sleeve (1) through a stop screw.
9. The mechanical positioning and locking device of the aircraft tooling according to claim 8, wherein the top of the positioning ring (106) is provided with a mounting groove corresponding to the locking ring, and a copper ring (5) is arranged between the locking ring and the mounting groove.
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| CN202110988222.9A CN113650803B (en) | 2021-08-26 | 2021-08-26 | Mechanical positioning and locking device of aircraft tool |
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| CN202110988222.9A CN113650803B (en) | 2021-08-26 | 2021-08-26 | Mechanical positioning and locking device of aircraft tool |
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| CN113650803B true CN113650803B (en) | 2023-11-10 |
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Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1132100A (en) * | 1965-04-05 | 1968-10-30 | Lyonnaise Articles Metall | Door handle system |
| JP2003094212A (en) * | 2001-09-27 | 2003-04-03 | Tec Yasuda:Kk | Device for generating axial force, and mechanical chuck cylinder using the same |
| CN201807984U (en) * | 2010-09-08 | 2011-04-27 | 安徽博微长安电子有限公司 | Automatic centering and clamping device |
| CN102162509A (en) * | 2011-03-25 | 2011-08-24 | 成都飞机工业（集团）有限责任公司 | Locking device of electric actuating cylinder |
| CN105215888A (en) * | 2015-10-31 | 2016-01-06 | 安徽合力股份有限公司 | A kind of float support for machining |
| CN105889526A (en) * | 2016-05-23 | 2016-08-24 | 杭州吉沃科技有限公司 | Split-type butterfly valve and SIP and CIP method thereof |
| CN107263351A (en) * | 2017-05-09 | 2017-10-20 | 浙江大学 | A kind of mechanical ball head locking device of locator |
| CN206632697U (en) * | 2017-03-27 | 2017-11-14 | 江西洪都航空工业集团有限责任公司 | Suitable for the quick clamping mechanism of flexible fixture support unit |
| CN207058412U (en) * | 2017-05-15 | 2018-03-02 | 天津飞悦航空工业股份有限公司 | A kind of aviation assembly tooling Quick Release set packer |
| CN207437533U (en) * | 2017-09-11 | 2018-06-01 | 杭州圆通线缆科技有限公司 | A kind of axial locking device |
| CN208412187U (en) * | 2018-07-13 | 2019-01-22 | 上海拓璞数控科技股份有限公司 | Retaining mechanism |
| CN209532239U (en) * | 2018-12-29 | 2019-10-25 | 烟台海德机床有限公司 | One kind inserting shallow blind hole key-seating machine knife-clamping device |
| CN210289327U (en) * | 2019-07-08 | 2020-04-10 | 常州朗卓机电科技有限公司 | Mast quick-pull type self-locking device |
| CN111168597A (en) * | 2019-11-19 | 2020-05-19 | 苏州德鑫美电子科技有限公司 | Positioning tool for production and processing of electric connector |
| CN112264953A (en) * | 2020-09-24 | 2021-01-26 | 中国第一汽车股份有限公司 | Self-locking and screwing positioning pin and positioning method thereof |
| CN112873089A (en) * | 2021-01-18 | 2021-06-01 | 丁绍江 | Clamping device for bearing machining |
| CN112894684A (en) * | 2021-05-08 | 2021-06-04 | 成都飞机工业（集团）有限责任公司 | Radial direct-acting type clamping device |
-
2021
- 2021-08-26 CN CN202110988222.9A patent/CN113650803B/en active Active
Patent Citations (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1132100A (en) * | 1965-04-05 | 1968-10-30 | Lyonnaise Articles Metall | Door handle system |
| JP2003094212A (en) * | 2001-09-27 | 2003-04-03 | Tec Yasuda:Kk | Device for generating axial force, and mechanical chuck cylinder using the same |
| CN201807984U (en) * | 2010-09-08 | 2011-04-27 | 安徽博微长安电子有限公司 | Automatic centering and clamping device |
| CN102162509A (en) * | 2011-03-25 | 2011-08-24 | 成都飞机工业（集团）有限责任公司 | Locking device of electric actuating cylinder |
| CN105215888A (en) * | 2015-10-31 | 2016-01-06 | 安徽合力股份有限公司 | A kind of float support for machining |
| CN105889526A (en) * | 2016-05-23 | 2016-08-24 | 杭州吉沃科技有限公司 | Split-type butterfly valve and SIP and CIP method thereof |
| CN206632697U (en) * | 2017-03-27 | 2017-11-14 | 江西洪都航空工业集团有限责任公司 | Suitable for the quick clamping mechanism of flexible fixture support unit |
| CN107263351A (en) * | 2017-05-09 | 2017-10-20 | 浙江大学 | A kind of mechanical ball head locking device of locator |
| CN207058412U (en) * | 2017-05-15 | 2018-03-02 | 天津飞悦航空工业股份有限公司 | A kind of aviation assembly tooling Quick Release set packer |
| CN207437533U (en) * | 2017-09-11 | 2018-06-01 | 杭州圆通线缆科技有限公司 | A kind of axial locking device |
| CN208412187U (en) * | 2018-07-13 | 2019-01-22 | 上海拓璞数控科技股份有限公司 | Retaining mechanism |
| CN209532239U (en) * | 2018-12-29 | 2019-10-25 | 烟台海德机床有限公司 | One kind inserting shallow blind hole key-seating machine knife-clamping device |
| CN210289327U (en) * | 2019-07-08 | 2020-04-10 | 常州朗卓机电科技有限公司 | Mast quick-pull type self-locking device |
| CN111168597A (en) * | 2019-11-19 | 2020-05-19 | 苏州德鑫美电子科技有限公司 | Positioning tool for production and processing of electric connector |
| CN112264953A (en) * | 2020-09-24 | 2021-01-26 | 中国第一汽车股份有限公司 | Self-locking and screwing positioning pin and positioning method thereof |
| CN112873089A (en) * | 2021-01-18 | 2021-06-01 | 丁绍江 | Clamping device for bearing machining |
| CN112894684A (en) * | 2021-05-08 | 2021-06-04 | 成都飞机工业（集团）有限责任公司 | Radial direct-acting type clamping device |
Non-Patent Citations (4)
| Title |
|---|
| Highly Underactuated Radial Gripper for Automated Planner Grasping and Part Fixturing;Vatsal V.Patel;2020 IEEE/RSJ International Conference on Intelligent Robots and Systems(IROS);9910-9916 * |
| 小型活塞发动机装配工装设计及应用;张旭东;《内燃机与配件》(第24期);33-34 * |
| 飞机系统件柔性敏捷制造单元构建方法;潘登;《航空制造技术》;第63卷(第21期);92-97 * |
| 飞机薄壁支座工件加工技术研究;汪际雄;《工艺与制造》(第12期);109-111 * |
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