CN220853665U - Test device for simulating eccentric hole machining of airplane docking intersection point - Google Patents
Test device for simulating eccentric hole machining of airplane docking intersection point Download PDFInfo
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- CN220853665U CN220853665U CN202322799614.8U CN202322799614U CN220853665U CN 220853665 U CN220853665 U CN 220853665U CN 202322799614 U CN202322799614 U CN 202322799614U CN 220853665 U CN220853665 U CN 220853665U
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- joint simulation
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- positioning seat
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- 238000003754 machining Methods 0.000 title claims abstract description 21
- 238000003032 molecular docking Methods 0.000 title claims abstract description 14
- 238000004088 simulation Methods 0.000 claims abstract description 65
- 230000000670 limiting effect Effects 0.000 claims description 20
- 210000001503 joint Anatomy 0.000 description 5
- 230000007547 defect Effects 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008094 contradictory effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
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Abstract
The utility model discloses a test device for simulating eccentric hole machining of an airplane docking intersection point, and aims to provide a test device for simulating eccentric hole machining of an airplane docking intersection point, which has the advantages of strong universality, high repeatability and low test cost. The utility model comprises a base, wherein a positioning seat is arranged on the base, a first joint simulation piece, a second joint simulation piece and an eccentric adjusting block are arranged on the positioning seat, the first joint simulation piece and the second joint simulation piece are oppositely arranged, test holes are formed in the first joint simulation piece and the second joint simulation piece, a first lining is arranged in the test holes, the eccentric adjusting block is arranged on the first joint simulation piece and the positioning seat, and the position of the first joint simulation piece is adjusted when the eccentric adjusting block moves. The utility model is applied to the technical field of aerospace.
Description
Technical Field
The utility model relates to the technical field of aerospace, in particular to a test device for simulating eccentric hole machining of an airplane butt joint intersection point.
Background
At present, the hole diameter of a common airplane butt joint intersection point hole is large and deep, a certain eccentric amount exists between the airplane butt joint intersection point holes due to the fact that pose adjustment is needed between airplane components, high-strength materials are difficult to cut due to the fact that high-strength materials are selected, manual air drills are difficult to cut, and the machining quality of the holes is poor; moreover, the numerical control center is large in size, high in cost and difficult to integrate on the production line of the airplane docking. Therefore, there is a need to develop a test device for simulating eccentric hole machining of an aircraft butt joint intersection point with strong universality, high repeatability and low test cost based on an automatic feed drill machining process, so as to verify and optimize machining process parameters meeting requirements through multiple tests.
Disclosure of utility model
The utility model aims to solve the technical problems of overcoming the defects of the prior art, and providing the test device for simulating the eccentric hole machining of the airplane butt joint intersection point, which has strong universality, high repeatability and low test cost.
The technical scheme adopted by the utility model is as follows: the utility model comprises a base, wherein a positioning seat is arranged on the base, a first joint simulation piece, a second joint simulation piece and an eccentric adjusting block are arranged on the positioning seat, the first joint simulation piece and the second joint simulation piece are oppositely arranged, test holes are formed in the first joint simulation piece and the second joint simulation piece, a first lining is arranged in the test holes, the eccentric adjusting block is arranged on the first joint simulation piece and the positioning seat, and the position of the first joint simulation piece is adjusted when the eccentric adjusting block moves.
Further, the first joint simulation piece is a single-ear joint simulation piece and is provided with the test hole; the second joint simulation piece is a double-lug joint simulation piece and is provided with two test holes; the first bushing is detachably mounted in the test hole.
Further, the first joint simulation piece and the second joint simulation piece are both provided with auxiliary mounting rings.
Further, be provided with first spacing terminal surface and locking groove on the first bush, first joint simulation spare with all be provided with on the second joint simulation spare with first spacing terminal surface complex second spacing terminal surface, first joint simulation spare with all be provided with on the second joint simulation spare and lock the locking pin in the locking groove.
Further, the front end of positioning seat is provided with preceding direction subassembly and stopper, the rear end of positioning seat is provided with back direction subassembly, first joint simulation spare cooperation sets up on the stopper, preceding direction subassembly with all be provided with the guiding hole on the back direction subassembly, be provided with the second bush in the guiding hole, back direction subassembly be connected with locking screw on the second bush.
Further, the second bushing is detachably mounted in the guide hole.
Further, the front guide assembly, the rear guide assembly and the limiting block are connected to the positioning seat through positioning pins and bolts.
Further, a limiting groove is formed in the base, the positioning seat is matched with the limiting groove, and the positioning seat is connected to the base.
Further, the eccentric adjusting block is provided with a plurality of bosses with different thicknesses.
The beneficial effects of the utility model are as follows:
Compared with the defects of the prior art, in the utility model, the test requirements of different eccentric amounts can be completed by adjusting the position of the eccentric adjusting block, the requirement of repeated tests can be completed by replacing the first bushing on the first joint simulation piece and the second joint simulation piece, the universality is strong, the structure is simple, the ingenious and the test cost is low, and the device is easy to popularize and apply in various aircraft manufacturers, so that the device has the advantages of strong universality, high repeatability and low test cost.
Drawings
In order to more clearly illustrate the embodiments of the present utility model or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, and it is obvious that the drawings in the following description are only some embodiments of the present utility model, and other drawings may be obtained according to the structures shown in these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic perspective view of the present utility model;
FIG. 2 is a schematic perspective view of a first joint simulator of the present utility model;
FIG. 3 is a schematic perspective view of a first joint simulator according to the present utility model;
FIG. 4 is a schematic perspective view of a second joint simulator of the present utility model;
FIG. 5 is a schematic perspective view of a second joint simulator of the utility model;
FIG. 6 is a schematic perspective view of a first bushing of the present utility model;
FIG. 7 is a schematic perspective view of a positioning seat according to the present utility model;
FIG. 8 is a schematic diagram of a positioning seat according to a second embodiment of the present utility model;
FIG. 9 is a schematic plan view of a positioning seat according to the present utility model;
FIG. 10 is a schematic perspective view of a base of the present utility model;
fig. 11 is a schematic perspective view of an eccentric adjusting block of the present utility model.
The reference numerals are as follows:
1. A base; 2. a positioning seat; 3. a first joint simulator; 5. a second joint simulator; 6. an eccentric adjusting block; 7. a test hole; 8. a first bushing; 9. an auxiliary mounting ring; 10. the first limiting end face; 11. a locking groove; 12. the second limiting end face; 13. a locking pin; 15. a front guide assembly; 16. a limiting block; 17. a rear guide assembly; 18. a guide hole; 19. a second bushing; 20. a locking screw; 21. a limit groove; 22. a boss.
The achievement of the objects, functional features and advantages of the present utility model will be further described with reference to the accompanying drawings, in conjunction with the embodiments.
Detailed Description
The following description of the embodiments of the present utility model will be made clearly and fully with reference to the accompanying drawings, in which it is evident that the embodiments described are only some, but not all embodiments of the utility model. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
It should be noted that all directional indicators in the embodiments of the present utility model, such as up, down, left, right, front, rear, clockwise, counterclockwise, etc., are merely used to explain the relative positional relationship between the components, the movement condition, etc. in a specific posture, if the specific posture is changed, the directional indicator is changed accordingly.
Furthermore, the description of "first," "second," etc. in this disclosure is for descriptive purposes only and is not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In addition, the technical solutions of the embodiments may be combined with each other, but it is necessary to base that the technical solutions can be realized by those skilled in the art, and when the technical solutions are contradictory or cannot be realized, the technical solutions should be considered that the combination does not exist and is not within the scope of protection claimed by the present utility model.
As shown in fig. 1 to 6, in this embodiment, the present utility model includes a base 1, a positioning seat 2 is provided on the base 1, a first joint simulator 3, a second joint simulator 5, and an eccentric adjusting block 6 are provided on the positioning seat 2, the first joint simulator 3 and the second joint simulator 5 are disposed opposite to each other, and are each provided with a test hole 7, a first bushing 8 is provided in the test hole 7, the eccentric adjusting block 6 is disposed on the first joint simulator 3 and the positioning seat 2, and the eccentric adjusting block 6 adjusts the position of the first joint simulator 3 when moving.
As the arrow mark direction of fig. 1 is the automatic feeding direction, during the test, the automatic feeding drill sequentially penetrates the first bushing 8 of the second joint simulator 5 and the first bushing 8 of the first joint simulator 3; in the process, the eccentric adjustment block 6 is moved to adjust the eccentric amount between the first joint simulation piece 3 and the second joint simulation piece 5, so that the test requirements of different eccentric amounts can be met, and the test is finished.
Compared with the defects of the prior art, in the utility model, the test requirements of different eccentric amounts can be completed by adjusting the position of the eccentric adjusting block 6, the requirement of repeated tests can be completed by replacing the first bushing 8 on the first joint simulation piece 3 and the second joint simulation piece 5, the universality is strong, the structure is simple, the ingenious performance is realized, the test cost is low, and the device is easy to popularize and apply in various aircraft manufacturers, so that the device has the advantages of strong universality, high repeatability and low test cost.
As shown in fig. 2 to 6, in some embodiments, the first joint simulator 3 is a monaural joint simulator, and is provided with one of the test holes 7; the second joint simulation piece 5 is a double-lug joint simulation piece and is provided with two test holes 7; the first bushing 8 is detachably arranged in the test hole 7; the first joint simulator 3 and the second joint simulator 5 are provided with auxiliary mounting rings 9. Wherein, all open a plurality of mounting holes on first joint simulation spare 3 and the second joint simulation spare 5, first joint simulation spare 3 and the second joint simulation spare 5 are connected to on the positioning seat 2 through the mounting hole respectively.
Specifically, the auxiliary mounting ring 9 is used for assisting the movement and adjustment mounting of the first joint simulator 3 and the second joint simulator 5; is detachably mounted in the test hole 7 through the first bushing 8 to meet the test requirement of repeated tests.
As shown in fig. 2 to 6, in some embodiments, the first bushing 8 is provided with a first limiting end surface 10 and a locking groove 11, the first joint simulator 3 and the second joint simulator 5 are each provided with a second limiting end surface 12 matched with the first limiting end surface 10, and the first joint simulator 3 and the second joint simulator 5 are each provided with a locking pin 13 locked in the locking groove 11. Wherein the locking groove 11 is a V-shaped groove formed on the outer wall of the first bushing 8; the first joint simulation piece 3 and the second joint simulation piece 5 are respectively provided with a lock hole communicated with the upper part of the test hole 7, and the locking pin 13 is locked in the lock holes.
Specifically, when the first bushing 8 is installed in the test hole 7, due to the limiting effect of the second limiting end surface 12 on the first limiting end surface 10, the first bushing 8 can be quickly installed, and the risk of rotation of the first bushing 8 during the processing process can be avoided; further, the locking pin 13 abuts against the locking groove 11 of the first bushing 8 to tightly press the first bushing 8, wherein the locking pin 13 is a full-thread screw of an inner hexagon head so as to adjust the locking depth.
As shown in fig. 7 to 9, in some embodiments, a front guide assembly 15 and a limiting block 16 are disposed at the front end of the positioning seat 2, a rear guide assembly 17 is disposed at the rear end of the positioning seat 2, the first joint simulator 3 is cooperatively disposed on the limiting block 16, guide holes 18 are disposed on the front guide assembly 15 and the rear guide assembly 17, a second bushing 19 is disposed in the guide holes 18, and a locking screw 20 is connected to the second bushing 19 of the rear guide assembly 17; the second bushing 19 is detachably mounted in the guide hole 18. Wherein the second bushing 19 is a steel bushing.
Specifically, the front guide assembly 15 is used for supporting a front guide rod of the hole machining tool, and the rear guide assembly 17 is used for supporting a drill bushing of the automatic feed drill; locking on the second bushing 19 of the rear guide assembly 17 by means of a locking screw 20 to fix the automatic feed drill; the second bush 19 is embedded in the guide hole 18, and the second bush 19 can be detached to reuse the device.
As shown in fig. 7 to 9, in some embodiments, the front guide assembly 15, the rear guide assembly 17 and the stopper 16 are all connected to the positioning base 2 by positioning pins and bolts. Specifically, two ends of the front guide assembly 15 and the rear guide assembly 17 are respectively positioned on the positioning seat 2 through two groups of positioning pins so as to ensure that the guide holes 18 of the front guide assembly 15 and the rear guide assembly 17 are concentric, and the front guide assembly 15 and the rear guide assembly 17 are firmly connected through four groups of bolts; the limiting block 16 is positioned on the positioning seat 2 through two groups of positioning pins and is connected through two groups of bolts so as to serve as an adjusting and positioning reference of the eccentric adjusting block 6.
As shown in fig. 10, in some embodiments, the base 1 is provided with a limiting groove 21, the positioning seat 2 is cooperatively disposed on the limiting groove 21, and the positioning seat 2 is connected to the base 1. Wherein, base 1 is T type structure, has strengthening rib, a plurality of M10 screw holes on the base 1, and a plurality of M10 screw holes are used for positioning seat 2 to connect on base 1.
As shown in fig. 11, in some embodiments, the eccentric adjustment block 6 has a plurality of bosses 22 of different thicknesses thereon. Wherein the plurality of bosses 22 are different in thickness with 0.2mm as adjustment amount (e.g., 14mm, 14.2mm, 14.4mm, 14.6mm, 14.8mm, and 15 mm) for adjustment of the eccentric amount, and divided between the plurality of bosses 22 by dividing grooves.
Specifically, the first joint simulator 3 is positioned on the stopper 16, and the stopper 16 is used as an adjustment reference, and the eccentric adjustment block 6 is further moved to adjust the eccentric amounts of the first joint simulator 3 and the second joint simulator 5.
The specific test flow of the utility model is as follows:
During the test, the device is fixedly connected to a test platform, the first bushing 8 is installed in the test hole 7 of the first joint simulation piece 3, and the first bushing 8 is propped against the locking groove 11 through the locking pin 13 so as to tightly prop up the first bushing 8, and the first joint simulation piece 3 is installed on the positioning seat 2; likewise, the first bushing 8 is mounted in the test hole 7 of the second joint simulator 5 and is abutted against the locking groove 11 by the locking pin 13 to tightly jack the first bushing 8, the eccentric adjusting block 6 is inserted into the second joint simulator 5, and the second joint simulator 5 is mounted on the positioning seat 2;
After the hole machining test is finished, the first joint simulation piece 3, the eccentric adjusting block 6 and the second joint simulation piece 5 are disassembled, then the first bushing 8 on the first joint simulation piece 3 and the second joint simulation piece 5 is disassembled, and the requirements of the aperture, the roughness and the like of the first bushing 8 are checked;
if the test is required again, repeating the above test steps.
The foregoing description is only of the preferred embodiments of the present utility model and is not intended to limit the scope of the utility model, and all equivalent structural changes made by the description of the present utility model and the accompanying drawings or direct/indirect application in other related technical fields are included in the scope of the utility model.
Claims (9)
1. A test device for simulating eccentric hole machining of an aircraft docking intersection point is characterized in that: the automatic positioning device comprises a base (1), wherein a positioning seat (2) is arranged on the base (1), a first joint simulation piece (3), a second joint simulation piece (5) and an eccentric adjusting block (6) are arranged on the positioning seat (2), the first joint simulation piece (3) and the second joint simulation piece (5) are oppositely arranged, test holes (7) are formed in the second joint simulation piece, a first bushing (8) is arranged in the test holes (7), the eccentric adjusting block (6) is arranged on the first joint simulation piece (3) and the positioning seat (2), and the position of the first joint simulation piece (3) is adjusted when the eccentric adjusting block (6) moves.
2. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 1, wherein: the first joint simulation piece (3) is a single-lug joint simulation piece and is provided with a test hole (7); the second joint simulation piece (5) is a double-lug joint simulation piece and is provided with two test holes (7); the first bushing (8) is detachably mounted in the test hole (7).
3. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 2, wherein: the first joint simulation piece (3) and the second joint simulation piece (5) are respectively provided with an auxiliary mounting ring (9).
4. A test device for simulating the machining of an eccentric hole at an aircraft docking intersection according to any one of claims 1-3, wherein: be provided with first spacing terminal surface (10) and locking groove (11) on first bush (8), first joint simulation spare (3) with all be provided with on second joint simulation spare (5) with first spacing terminal surface (10) complex second spacing terminal surface (12), first joint simulation spare (3) with all be provided with on second joint simulation spare (5) locking pin (13) in locking groove (11).
5. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 1, wherein: the front end of positioning seat (2) is provided with preceding direction subassembly (15) and stopper (16), the rear end of positioning seat (2) is provided with back direction subassembly (17), first joint simulation spare (3) cooperation sets up on stopper (16), preceding direction subassembly (15) with all be provided with guiding hole (18) on back direction subassembly (17), be provided with second bush (19) in guiding hole (18), be connected with locking screw (20) on second bush (19) of back direction subassembly (17).
6. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 5, wherein: the second bushing (19) is detachably mounted in the guide hole (18).
7. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 5, wherein: the front guide assembly (15), the rear guide assembly (17) and the limiting block (16) are connected to the positioning seat (2) through positioning pins and bolts.
8. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 1, wherein: the base (1) is provided with a limiting groove (21), the positioning seat (2) is matched with the limiting groove (21), and the positioning seat (2) is connected to the base (1).
9. The test device for simulating eccentric hole machining of an aircraft docking intersection of claim 1, wherein: the eccentric adjusting block (6) is provided with a plurality of bosses (22) with different thicknesses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322799614.8U CN220853665U (en) | 2023-10-18 | 2023-10-18 | Test device for simulating eccentric hole machining of airplane docking intersection point |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322799614.8U CN220853665U (en) | 2023-10-18 | 2023-10-18 | Test device for simulating eccentric hole machining of airplane docking intersection point |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220853665U true CN220853665U (en) | 2024-04-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322799614.8U Active CN220853665U (en) | 2023-10-18 | 2023-10-18 | Test device for simulating eccentric hole machining of airplane docking intersection point |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220853665U (en) |
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2023
- 2023-10-18 CN CN202322799614.8U patent/CN220853665U/en active Active
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