CN216706068U - Aircraft skin self-adaptation normal alignment dimple device - Google Patents
Aircraft skin self-adaptation normal alignment dimple device Download PDFInfo
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- CN216706068U CN216706068U CN202122898947.7U CN202122898947U CN216706068U CN 216706068 U CN216706068 U CN 216706068U CN 202122898947 U CN202122898947 U CN 202122898947U CN 216706068 U CN216706068 U CN 216706068U
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Abstract
The utility model relates to the technical field of countersinking in the manufacturing process of aircraft skin, and discloses a self-adaptive normal alignment countersinking device for the aircraft skin. The sleeve and the countersink guide assembly jointly form a guide cavity, a drill chuck positioned in the guide cavity clamps a countersink drill, and the countersink drill can extend out of the countersink guide assembly to perform countersink processing on a part; the bearing gland is installed at the lower end of the sleeve and jointly forms a bearing installation part for installing the angular contact knuckle bearing; the outer ring of the angular contact knuckle bearing is connected with the bearing gland, and the inner ring of the angular contact knuckle bearing is connected with the countersink guide assembly; the bearing gland is connected with the dimple guide assembly through a spring. The utility model solves the problem that the dimple device cannot be aligned in a self-adaptive manner by arranging the angular contact knuckle bearing and the spring.
Description
Technical Field
The utility model relates to the technical field of countersinking in the manufacturing process of aircraft skin, in particular to a self-adaptive method direction alignment countersinking device for aircraft skin, which is used for countersinking.
Background
Spot facing machining, also called spot facing drilling machining, refers to a machining method for spot facing a conical counter bore (spot facing hole) on a machined rivet hole on a part.
The existing dimple technology usually depends on the working experience of an operator to ensure the dimple precision, and when the requirement on the dimple precision is higher, the precision requirement is difficult to ensure. Although some automatic dimple equipment is applied to scenes such as aircraft skins and the like with high requirements on dimple machining precision, the existing automatic dimple equipment is large in size, complex in positioning process and low in positioning efficiency. Therefore, a self-adaptive method for aligning the dimple positioning device is designed to meet wide requirements.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide an aircraft skin self-adaptive normal alignment dimple device, wherein a sleeve and a dimple guide assembly are connected through an angular contact knuckle bearing and a spring, and a rigid connection structure between the sleeve and the dimple guide assembly in the prior art is replaced, so that the dimple guide assembly can self-adaptively adjust the normal direction of a guide hole according to stress balance during dimple operation, and the problem that the dimple device cannot self-adaptively align in the normal direction is solved.
The utility model is realized by the following technical scheme: the aircraft skin self-adaptive normal alignment socket device comprises a drill chuck, a socket drill, a sleeve and a socket guide assembly, wherein the sleeve and the socket guide assembly form a guide cavity together; the dimple device also comprises an angular contact joint bearing, a bearing gland and a spring; the bearing gland is installed at the lower end of the sleeve and jointly forms a bearing installation part for installing the angular contact knuckle bearing; the outer ring of the angular contact knuckle bearing is connected with the bearing gland, and the inner ring of the angular contact knuckle bearing is connected with the countersink guide assembly; the bearing gland is connected with the dimple guide assembly through a spring.
In order to better implement the utility model, further, the dimple guide assembly comprises a dimple guide head and a dimple guide flange which are fixedly connected with each other; the dimple guide head is provided with a guide hole for guiding the dimple drill; integrated structure dimple flange has set gradually location boss, inner circle connection boss, gland connection boss from inside to outside, the outer wall of location boss with the inner wall contact of angular contact joint bearing inner circle just the terminal surface of inner circle connection boss with the terminal surface contact of angular contact joint bearing inner circle, simultaneously the gland connection boss pass through the spring with the bearing gland is connected.
In order to better implement the utility model, further, the dimple guide head and the dimple guide flange are connected by a long bolt.
In order to better implement the utility model, further, the positioning boss is in interference fit with the angular contact knuckle bearing inner ring.
In order to better realize the utility model, further, the dimple device further comprises a gland connecting bolt and a positioning pin; the other end of the spring is connected with the positioning pin arranged on the bearing gland, and the gland connecting bolt is not in contact with the end part of the positioning pin.
In order to better implement the utility model, further, the positioning pin is in interference fit with the pin hole of the bearing gland.
In order to better implement the utility model, further, one end of the gland connecting bolt connected with the dimple guide flange is provided with threads, and one end of the gland connecting bolt connected with the spring is provided with a first mounting hole for connecting the spring.
In order to better implement the utility model, further, one end of the positioning pin, which is connected with the spring, is provided with a second mounting hole for connecting the spring.
In order to better realize the utility model, further, the dimple device further comprises a limiting block; be provided with the notch that link up on the telescopic lateral wall, the stopper is installed it is right just can stretch into the direction chamber on the sleeve drill chuck or it is spacing to ream drill bit axial motion position.
In order to better implement the present invention, further, the number of the springs is plural, and the plural springs are uniformly arranged along the circumferential direction of the sleeve.
Compared with the prior art, the utility model has the following advantages and beneficial effects:
(1) according to the dimple device, the sleeve and the dimple guide assembly are connected through the angular contact knuckle bearing and the spring, a rigid connection structure between the sleeve and the dimple guide assembly in the prior art is replaced, and the dimple guide assembly can adaptively adjust the normal direction of a guide hole according to stress balance during dimple operation; on the premise of ensuring the spot facing machining precision, the spot facing time is greatly shortened;
(2) according to the dimple device, the limiting block is arranged, so that the descending position of a dimple drill during working can be controlled, the depth and the size of a dimple are guaranteed, and meanwhile, the precision requirement of dimple machining is guaranteed;
(3) the utility model can effectively reduce the reject ratio of spot facing of products.
Drawings
The utility model is further described in connection with the following figures and examples, all of which are intended to be open ended and within the scope of the utility model.
Fig. 1 is an exploded schematic view of an aircraft skin self-adaptive normal alignment dimple device according to the present invention.
Fig. 2 is a schematic cross-sectional structure view of the aircraft skin self-adaptive normal alignment dimple device.
Wherein: 1. a dimple guide head; 2. a dimple guide flange; 201. positioning the boss; 202. the inner ring is connected with a boss; 203. the gland is connected with the boss; 3. an angular contact spherical plain bearing; 4. a gland connecting bolt; 5. a spring; 6. positioning pins; 7. a bearing gland; 8. a sleeve; 801. a flange hole; 802. a notch; 9. a limiting block; 10. a drill chuck; 11. a countersink drill.
Detailed Description
Example 1:
the embodiment provides an aircraft skin self-adaptive normal alignment dimple device, which comprises a drill chuck 10, a dimple drill 11, a sleeve 8, a dimple guide assembly, an angular contact spherical plain bearing 3, a bearing gland 7 and a spring 5. The bit holder 10 holding the countersink bit 11 is mounted on the spindle of the countersink device and is driven by the spindle of the countersink device.
The sleeve 8 and the socket guide assembly jointly form a guide cavity, the drill chuck 10 positioned in the guide cavity clamps the socket drill 11, and the socket drill 11 can extend out of the socket guide assembly to perform spot facing on a part; the bearing gland 7 is arranged at the lower end of the sleeve 8 and jointly forms a bearing mounting part for mounting the angular contact joint bearing 3; the outer ring of the angular contact knuckle bearing 3 is connected with the bearing gland 7, and the inner ring of the angular contact knuckle bearing 3 is connected with the dimple guide assembly; the bearing gland 7 is connected with the dimple guide assembly through a spring 5.
The upper end of the sleeve 8 is installed on a main shaft of the socket equipment, the lower end of the sleeve 8 is fixedly connected with the bearing gland 7, and the bearing gland 7 is connected with an outer ring of the angular contact knuckle bearing 3. Therefore, the relative position of the axis of the outer ring of the angular contact knuckle bearing 3 and the axis of the main shaft of the socket equipment is fixed; and the relative position of the axial line of the inner ring of the angular contact joint bearing 3 and the axial line of the main shaft of the socket equipment is variable. The angular contact knuckle bearing 3 is just utilized, and the elasticity provided by the spring 5 during deformation is combined, so that the normal direction of the countersink guide assembly is adaptively adjusted according to the external force received by the countersink guide assembly during countersink processing.
Specifically, when the dimple guide assembly is in contact with a hole of an aircraft skin to be dimpled, the dimple guide assembly transmits the reaction force of the skin to the angular contact knuckle bearing 3 and the spring 5; if the atress is uneven, dimple guide assembly will drive angular contact joint bearing 3 takes place to deflect under the effect of power, simultaneously dimple guide assembly deflects the adjustment of gesture under the spring action of spring 5, and until the atress is balanced, the normal direction of the hole of treating the dimple is looked for to the realization is automatic this moment to improve machining precision and machining efficiency greatly.
Further, in order to guarantee that the dimple device can have stable self-adaptive normal alignment performance when the stress is applied to any direction, the springs 5 are arranged in the circumferential direction of the main shaft of the dimple device, and are distributed uniformly and better. Naturally, since the working axes of the drill chuck 10, the socket drill 11 and the sleeve 8 are usually designed coaxially with the socket tool spindle, it is sufficient if the plurality of springs 5 connecting the sleeve 8 and the socket guide assembly are arranged circumferentially along the sleeve 8 or the socket guide assembly.
Example 2:
the structure of the dimple guide assembly is optimized on the basis of the above embodiment.
In the embodiment, the dimple guide assembly comprises a dimple guide head 1 and a dimple guide flange 2 which are fixedly connected with each other; the dimple guide head 1 is provided with a guide hole for guiding the dimple drill 11; integrated structure dimple guide flange 2 has set gradually location boss 201, inner circle connection boss 202, gland connection boss 203 from inside to outside, the outer wall of location boss 201 with the inner wall contact of 3 inner circles of angular contact joint bearing just the terminal surface that the boss 202 was connected to the inner circle with the terminal surface contact of 3 inner circles of angular contact joint bearing, simultaneously the gland connection boss 203 pass through spring 5 with bearing gland 7 is connected.
As shown in fig. 1 and 2, the outer diameter of the positioning boss 201, the outer diameter of the inner ring connecting boss 202, and the outer diameter of the gland connecting boss 203 are sequentially increased, the outer wall of the positioning boss 201 contacts the inner wall of the inner ring of the angular contact spherical plain bearing 3, and the end surface of the inner ring connecting boss 202 contacts the end surface of the inner ring of the angular contact spherical plain bearing 3, so that the inner ring of the angular contact spherical plain bearing 3 and the dimple guide flange 2 are stably connected as a whole. The gland connecting boss 203 has the largest outer diameter and a larger outline, so that the spring 5 is convenient to mount.
Further, the dimple guide head 1 and the dimple guide flange 2 are connected by a long bolt.
Further, the positioning boss 201 is in interference fit with the inner ring of the angular contact spherical plain bearing 3.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 3:
on the basis of the above embodiments, the present embodiment provides a structure that facilitates the installation, replacement, and adjustment of the spring 5.
The dimple device also comprises a gland connecting bolt 4 and a positioning pin 6; threaded connection is in on the gland connection boss 203 the gland connecting bolt 4 with the one end of spring 5 is connected, the other end of spring 5 with install on the bearing gland 7 the locating pin 6 is connected, just the gland connecting bolt 4 with the tip of locating pin 6 does not contact.
Further, the positioning pin 6 is in interference fit with a pin hole of the bearing gland 7.
Further, the gland connecting bolt 4 with the one end that the dimple guide flange 2 is connected is provided with the screw thread, the gland connecting bolt 4 with the one end that spring 5 is connected is provided with the first mounting hole that is used for connecting spring 5.
Further, one end of the positioning pin 6 connected with the spring 5 is provided with a second mounting hole for connecting the spring 5.
In addition, the bearing gland 7 and the gland connecting boss 203 are respectively provided with a guide short column, the two guide short columns correspond to each other one by one and have a certain distance, and the spring 5 is sleeved on a group of guide short columns corresponding to the positions under the structure, so that the installation of the spring 5 can be realized without influencing the function of the spring 5.
Of course, if the replacement and adjustment of the spring 5 are not considered, the function of the spring 5 is not affected by directly welding the end of the spring 5 to the bearing cover 7 and the cover connecting boss 203.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 4:
the embodiment is further optimized on the basis of any one of the embodiments 1 to 3, and the dimple device further comprises a limiting block 9; be provided with the notch 802 that link up on the lateral wall of sleeve 8, stopper 9 is installed it is right just can stretch into the direction chamber on the sleeve 8 drill chuck 10 or 11 axial motion positions of counter bit are spacing.
As shown in fig. 1, the bottom of the sleeve 8 is a flange structure provided with a plurality of flange holes 801, the limiting block 9 is provided with an installation groove, and the limiting block 9 can be installed on the sleeve 8 through connecting members such as bolts, screws, pins and the like which can be connected with the flange holes 801. When the limiting block 9 extends into the guide cavity from the notch 802 and is located on the working travel path of the drill chuck 10 and the socket drill 11, the lower limit positions of the drill chuck 10 and the socket drill 11 can be limited. Of course, the lower limit positions of the drill chuck 10 and the countersink drill 11 can be adjusted by replacing the stopper 9 with a different size and a different structure or changing the installation position of the stopper 9. The adjustment of the lower limit position is well known in the art and is not an improvement of the present application, and therefore will not be described in detail.
Other parts of this embodiment are the same as those of the above embodiment, and thus are not described again.
Example 5:
as shown in fig. 1 and 2, the aircraft skin self-adaptive normal alignment socket device comprises a drill chuck 10, a socket drill 11, a sleeve 8, a socket guide assembly, an angular contact knuckle bearing 3, a bearing gland 7, a spring 5, a gland connecting bolt 4 and a positioning pin 6. And the drill chuck 10 and the sleeve 8 are both arranged on a main shaft of the dimpling equipment. Sleeve 8 with the common direction chamber that forms of dimple guide assembly is located the direction intracavity 10 centre gripping of drill chuck dimple drill bit 11, just dimple drill bit 11 can stretch out dimple guide assembly and carry out spot facing processing to the part.
The dimple guide assembly comprises a dimple guide head 1 and a dimple guide flange 2 which are fixedly connected with each other; the dimple guide head 1 is provided with a guide hole for guiding the dimple drill 11; integrated structure dimple flange 2 has set gradually location boss 201, inner circle connection boss 202, gland connection boss 203 from inside to outside, the outer wall of location boss 201 with the inner wall contact of angular contact joint bearing 3 inner circle just the terminal surface of inner circle connection boss 202 with the terminal surface contact of angular contact joint bearing 3 inner circle, simultaneously the gland connection boss 203 through spring 5 with bearing gland 7 is connected.
The bearing gland 7 is arranged at the lower end of the sleeve 8 and jointly forms a bearing mounting part for mounting the angular contact joint bearing 3; the outer ring of the angular contact knuckle bearing 3 is connected with the bearing gland 7, and the inner ring of the angular contact knuckle bearing 3 is connected with the dimple guide flange 2 of the dimple guide assembly.
Threaded connection is in on the gland connection boss 203 the gland connecting bolt 4 with the one end of spring 5 is connected, the other end of spring 5 with install on the bearing gland 7 the locating pin 6 is connected, just the gland connecting bolt 4 with the tip of locating pin 6 does not contact.
Further, the positioning pin 6 is in interference fit with a pin hole of the bearing gland 7.
Further, the gland connecting bolt 4 with the one end that the dimple guide flange 2 is connected is provided with the screw thread, the gland connecting bolt 4 with the one end that spring 5 is connected is provided with the first mounting hole that is used for connecting spring 5. And a second mounting hole for connecting the spring 5 is formed in one end of the positioning pin 6 connected with the spring 5.
Other parts of this embodiment are the same as any of embodiments 1 to 4, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (10)
1. The aircraft skin self-adaptive normal alignment socket device comprises a drill chuck (10), a socket drill bit (11), a sleeve (8) and a socket guide assembly, wherein the sleeve (8) and the socket guide assembly jointly form a guide cavity, the drill chuck (10) positioned in the guide cavity clamps the socket drill bit (11), and the socket drill bit (11) can extend out of the socket guide assembly to perform socket machining on a part; the method is characterized in that:
the socket device also comprises an angular contact joint bearing (3), a bearing gland (7) and a spring (5); the bearing gland (7) is arranged at the lower end of the sleeve (8) and jointly forms a bearing mounting part for mounting the angular contact joint bearing (3); the outer ring of the angular contact joint bearing (3) is connected with the bearing gland (7), and the inner ring of the angular contact joint bearing (3) is connected with the dimple guide assembly; the bearing gland (7) is connected with the dimple guide assembly through a spring (5).
2. The aircraft skin self-adaptive normal alignment dimple device as claimed in claim 1, wherein: the dimple guide assembly comprises a dimple guide head (1) and a dimple guide flange (2) which are fixedly connected with each other; the dimple guide head (1) is provided with a guide hole for guiding the dimple drill bit (11); integrated structure dimple flange (2) have set gradually location boss (201), inner circle connection boss (202), gland connection boss (203) from inside to outside, the outer wall of location boss (201) with the inner wall contact of angular contact joint bearing (3) inner circle just the terminal surface of inner circle connection boss (202) with the end face contact of angular contact joint bearing (3) inner circle, simultaneously gland connection boss (203) through spring (5) with bearing gland (7) are connected.
3. The aircraft skin self-adaptive normal alignment countersinking device according to claim 2, wherein: the dimple guide head (1) is connected with the dimple guide flange (2) through a long bolt.
4. The aircraft skin self-adaptive normal alignment countersinking device according to claim 2, wherein: the positioning boss (201) is in interference fit with the inner ring of the angular contact knuckle bearing (3).
5. The aircraft skin self-adaptive normal alignment dimple device as claimed in claim 2, wherein: the dimple device also comprises a gland connecting bolt (4) and a positioning pin (6); threaded connection is in on gland connection boss (203) gland connecting bolt (4) with the one end of spring (5) is connected, the other end of spring (5) with install on bearing gland (7) locating pin (6) are connected, just gland connecting bolt (4) with the tip contactless of locating pin (6).
6. The aircraft skin self-adaptive normal alignment countersinking device according to claim 5, wherein: the positioning pin (6) is in interference fit with a pin hole of the bearing gland (7).
7. The aircraft skin self-adaptive normal alignment countersinking device according to claim 5, wherein: the gland connecting bolt (4) is provided with a thread at one end connected with the dimple guide flange (2), and the gland connecting bolt (4) is provided with a first mounting hole used for connecting the spring (5) at one end connected with the spring (5).
8. The aircraft skin self-adaptive normal alignment countersinking device according to claim 5, wherein: and a second mounting hole for connecting the spring (5) is formed in one end, connected with the spring (5), of the positioning pin (6).
9. The aircraft skin adaptive normal alignment countersink device according to any one of claims 1 to 8, wherein: the dimple device also comprises a limiting block (9); be provided with notch (802) that link up on the lateral wall of sleeve (8), stopper (9) are installed it is right just to stretch into the direction chamber on sleeve (8) drill chuck (10) or dimple drill bit (11) axial motion position is spacing.
10. The aircraft skin adaptive normal alignment countersink device according to any one of claims 1 to 8, wherein: the number of the springs (5) is multiple, and the springs (5) are uniformly arranged along the circumferential direction of the sleeve (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122898947.7U CN216706068U (en) | 2021-11-24 | 2021-11-24 | Aircraft skin self-adaptation normal alignment dimple device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122898947.7U CN216706068U (en) | 2021-11-24 | 2021-11-24 | Aircraft skin self-adaptation normal alignment dimple device |
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| CN216706068U true CN216706068U (en) | 2022-06-10 |
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| CN202122898947.7U Active CN216706068U (en) | 2021-11-24 | 2021-11-24 | Aircraft skin self-adaptation normal alignment dimple device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115451882A (en) * | 2022-11-10 | 2022-12-09 | 通用技术集团沈阳机床有限责任公司 | Method for calculating normal vector of axis of skin bottom hole based on space pose of floating pin |
-
2021
- 2021-11-24 CN CN202122898947.7U patent/CN216706068U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115451882A (en) * | 2022-11-10 | 2022-12-09 | 通用技术集团沈阳机床有限责任公司 | Method for calculating normal vector of axis of skin bottom hole based on space pose of floating pin |
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