CN114012688B - Symmetrical point marking device for semi-enclosed space of airplane - Google Patents
Symmetrical point marking device for semi-enclosed space of airplane Download PDFInfo
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- CN114012688B CN114012688B CN202111237952.1A CN202111237952A CN114012688B CN 114012688 B CN114012688 B CN 114012688B CN 202111237952 A CN202111237952 A CN 202111237952A CN 114012688 B CN114012688 B CN 114012688B
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- sliding
- rocker arm
- auxiliary
- auxiliary sliding
- main
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H7/00—Marking-out or setting-out work
- B25H7/04—Devices, e.g. scribers, for marking
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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
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to an airplane semi-closed space symmetry point marking device which comprises a main sliding guide groove, a first main sliding guide sliding block, a second main sliding guide sliding block and a second auxiliary sliding rocker arm, wherein the first auxiliary sliding guide groove is arranged on the first auxiliary sliding rocker arm; the auxiliary sliding rocker arm telescopic rod is arranged on the second auxiliary sliding rocker arm sliding block, the first auxiliary sliding rocker arm sliding block is provided with a first fixing mechanism, and the second auxiliary sliding rocker arm sliding block is provided with a second fixing mechanism. The invention can effectively promote the correct confirmation of the opening position of an operator, prevent the damage of the machine body caused by the error of the opening position and improve the structural quality of the airplane.
Description
Technical Field
The invention relates to the technical field of aircraft production and assembly, in particular to an aircraft semi-enclosed space symmetrical point marking device.
Background
The frame and the beam of the aircraft are main stress components of the aircraft. The frames and beams supporting the aircraft structure are asymmetric in manufacture due to the structural design requirements. When the hole is made on the asymmetric structure frame, the method is to use a steel rule to determine the position of the hole by using a measuring reference plane according to the given size of the data model. Because the reinforcing rib structure on the frame is asymmetric, whether the other end of the measured open hole position can interfere with the reinforcing rib or drill on the reinforcing rib cannot be determined, and once the open hole is wrong, parts can be damaged or even the cost is reported, so that the structural strength of the aircraft is affected. And only the size of the opening at one end of the digital-analog standard is marked, if the other end is marked and confirmed by using a steel rule, the lead needs to be crossed by the structure, the lead angle deviation precision is not high easily, the measuring time is long, the production efficiency is low, and the operation is inconvenient.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide the symmetrical point marking device for the semi-enclosed space of the airplane, and aims to rapidly confirm the positions of openings at two ends of an asymmetric frame in the semi-enclosed space of the airplane, prevent the openings from being formed on a reinforcing rib, ensure the quality of products, improve the life efficiency and facilitate the subsequent work.
In order to solve the problems, the technical scheme adopted by the invention is as follows:
an aircraft semi-enclosed space symmetry point marking device is characterized in that: comprising
The device comprises a main sliding guide groove (1), a first main sliding guide slide block (2) and a second main sliding guide slide block (13), wherein the first main sliding guide slide block (2) and the second main sliding guide slide block (13) are arranged in the main sliding guide groove and can slide along the main sliding guide groove;
a first auxiliary sliding rocker arm (3) fixedly arranged on the first main sliding guide sliding block and a second auxiliary sliding rocker arm (8) fixedly arranged on the second main sliding guide sliding block (13);
the first auxiliary sliding rocker arm (3) is provided with a first auxiliary sliding groove, and a first auxiliary sliding rocker arm sliding block (7) is arranged in the first auxiliary sliding groove in a sliding manner; the second auxiliary sliding rocker arm (8) is provided with a second auxiliary sliding groove, and a second auxiliary sliding rocker arm sliding block (9) is arranged in the second auxiliary sliding groove in a sliding manner;
a main sliding rocker telescopic rod (6) with the rod length direction perpendicular to the length direction of the first auxiliary sliding rocker is arranged on the first auxiliary sliding rocker sliding block (7); the auxiliary sliding rocker arm telescopic rod (10) with the rod length direction perpendicular to the length direction of the second auxiliary sliding rocker arm is arranged on the second auxiliary sliding rocker arm sliding block (9), wherein in the process that the first auxiliary sliding rocker arm (3) and the second auxiliary sliding rocker arm (8) slide in the main sliding guide groove, at least the end of the main sliding rocker arm telescopic rod (6) and the end of the auxiliary sliding rocker arm telescopic rod (10) can be in contact alignment in opposite directions, the rod length is positioned in the same straight line, and the rod length can be respectively telescopic in the straight line;
the first auxiliary sliding rocker slider (7) and/or the first auxiliary sliding rocker (3) are/is further provided with a first fixing mechanism for locking the first auxiliary sliding rocker slider (7) on the first auxiliary sliding rocker (3), and the second auxiliary sliding rocker slider (9) or the second auxiliary sliding rocker (8) is/are further provided with a second fixing mechanism for locking the second auxiliary sliding rocker slider (9) on the second auxiliary sliding rocker (8).
Further, a first scale line (4) is arranged on the first auxiliary sliding rocker arm (3).
Further, a first scale mark (12) is arranged on the second auxiliary sliding rocker arm (8).
Further, the first fixing mechanism adopts a first positioning stop pin (5), the first positioning stop pin (5) is arranged on the first auxiliary sliding rocker arm sliding block (7), and the end head of the first positioning stop pin can penetrate through the first auxiliary sliding rocker arm sliding block (7) to be in butt joint with the first auxiliary sliding groove.
Further, the second fixing mechanism adopts a second positioning stop nail (11), the second positioning stop nail (11) is arranged on the second auxiliary sliding rocker arm sliding block (9), and the end head of the second positioning stop nail can penetrate through the second auxiliary sliding rocker arm sliding block (9) to be abutted with the second auxiliary sliding groove.
Compared with the prior art, the invention has the beneficial effects that: the technology mainly researches how to quickly confirm the positions of the asymmetric frame and the beam in the aircraft before opening the holes on the opposite surfaces, can effectively promote operators to correctly confirm the positions of the holes, prevent the damage of the aircraft body caused by the error positions of the holes, improve the structural quality of the aircraft, effectively promote the quality of the bulkhead/Liang Kaikong of the operators, prevent the error positions of the holes, ensure the structural strength of the aircraft and the like.
The invention is described in further detail below with reference to the drawings and the detailed description.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a top view of the present invention;
fig. 3 is a side view of the present invention.
Detailed Description
As shown in fig. 1-3, an aircraft semi-enclosed space symmetry point marking device comprises:
the main sliding guide groove 1, a first main sliding guide slide block 2 and a second main sliding guide slide block 13 which are arranged in the main sliding guide groove and can slide along the main sliding guide groove; a first auxiliary sliding rocker arm 3 fixedly arranged on the first main sliding guide sliding block and a second auxiliary sliding rocker arm 8 fixedly arranged on the second main sliding guide sliding block 13.
The first auxiliary sliding rocker arm 3 is provided with a first auxiliary sliding groove, and a first auxiliary sliding rocker arm sliding block 7 is arranged in the first auxiliary sliding groove in a sliding manner; the second auxiliary sliding rocker arm 8 is provided with a second auxiliary sliding groove, a second auxiliary sliding rocker arm sliding block 9 is arranged in the second auxiliary sliding groove in a sliding mode, the first auxiliary sliding rocker arm 3 is also provided with a first scale line 4, the second auxiliary sliding rocker arm 8 is provided with a first scale line 12, and a connecting line of the initial positions of the two scale lines is parallel to the groove direction of the main sliding guide groove.
The first auxiliary sliding rocker sliding block 7 is provided with a main sliding rocker telescopic rod 6 with a rod length direction perpendicular to the length direction of the first auxiliary sliding rocker; the second auxiliary sliding rocker arm sliding block 9 is provided with an auxiliary sliding rocker arm telescopic rod 10 with a rod length direction perpendicular to the length direction of the second auxiliary sliding rocker arm, wherein in the sliding process of the first auxiliary sliding rocker arm 3 and the second auxiliary sliding rocker arm 8 in the main sliding guide groove, at least the contact alignment of the end head of the main sliding rocker arm telescopic rod 6 and the end head of the auxiliary sliding rocker arm telescopic rod 10 in opposite directions can be ensured, the rod length is positioned in the same straight line, and the rod length can be respectively telescopic in the straight line.
The first auxiliary sliding rocker arm sliding block 7 and/or the first auxiliary sliding rocker arm 3 is/are further provided with a first fixing mechanism for locking the first auxiliary sliding rocker arm sliding block 7 on the first auxiliary sliding rocker arm 3, and the second auxiliary sliding rocker arm sliding block 9 or the second auxiliary sliding rocker arm 8 is/are further provided with a second fixing mechanism for locking the second auxiliary sliding rocker arm sliding block 9 on the second auxiliary sliding rocker arm 8.
The first fixing mechanism adopts a first positioning stop nail 5, the first positioning stop nail 5 is arranged on the first auxiliary sliding rocker arm slide block 7, the end head of the first positioning stop nail can penetrate through the first auxiliary sliding rocker arm slide block 7 to be abutted with the first auxiliary sliding groove, and after the position of the first auxiliary sliding rocker arm slide block 7 is adjusted, the first positioning stop nail 5 can be locked to lock the first auxiliary sliding rocker arm slide block 7 on the first auxiliary sliding groove, so that the main sliding rocker arm telescopic rod 6 is fixed relative to the first auxiliary sliding rocker arm 3.
The second fixing mechanism adopts a second positioning stop nail 11, the second positioning stop nail 11 is arranged on the second auxiliary sliding rocker arm sliding block 9, the end head of the second positioning stop nail can pass through the second auxiliary sliding rocker arm sliding block 9 to be in butt joint with the second auxiliary sliding groove, and after the position of the second auxiliary sliding rocker arm sliding block 9 is adjusted, the second positioning stop nail 11 can be locked to lock the second auxiliary sliding rocker arm sliding block 9 on the second auxiliary sliding groove, so that the auxiliary sliding rocker arm telescopic rod 10 is fixed relative to the position of the second auxiliary sliding rocker arm 8.
The using method of the aircraft semi-enclosed space symmetry point marking device comprises the following steps:
first, the scribing, positioning and pre-perforating position is carried out on an airplane according to the digital-analog size, a first auxiliary sliding rocker slider 7 is adjusted on a first auxiliary sliding rocker 3, so that the top point of the end head of a main sliding rocker telescopic rod 6 on the first auxiliary sliding rocker slider is overlapped with the scribing position point of the pre-perforating position on the airplane, and a first positioning stop nail 5 is locked to lock the overlapped position.
The removing device is used for adjusting the second main sliding guide sliding block 13 on the main sliding guide groove 1 to be close to the first auxiliary sliding rocker arm 3; on the other hand, the second auxiliary sliding rocker block 9 on the second auxiliary sliding rocker 8 is adjusted to enable two points on the ends of the telescopic rods of the main sliding rocker telescopic rod 6 and the auxiliary sliding rocker telescopic rod 10 to be overlapped. After superposition, the second positioning stop nail 11 is locked, so that the numerical values of the first auxiliary sliding rocker arm sliding block 7 and the second auxiliary sliding rocker arm sliding block 9 on the first scale line 4 and the second scale line 12 are consistent.
And (3) adjusting a second main sliding guide slide block 13 on the main sliding guide groove 1, pulling the distance between the second main sliding guide slide block and the first main sliding guide slide block 2 to enable the distance to be opened to be larger than the height of the airplane frame and the beam reinforcing rib, and clamping the device at the position to be measured of the airplane frame and the beam.
The top point of the end head on the main sliding rocker arm telescopic rod 6 is overlapped with the point of the pre-opening scribing position on the airplane, and the second main sliding guide sliding block 13 on the main sliding guide groove 1 is adjusted to be closed. The vertex positions of the ends of the main sliding rocker arm telescopic rod 6 and the auxiliary sliding rocker arm telescopic rod 10 are the starting positions of the holes.
The device can confirm the position of the asymmetric frame and the beam in the aircraft before opening the holes, can effectively promote operators to confirm the position of the opening holes correctly, prevent the damage of the aircraft caused by the error position of the opening holes, improve the structural quality of the aircraft, effectively promote the quality of the bulkhead/Liang Kaikong of the operators, prevent the error position of the opening holes, ensure the structural strength of the aircraft and the like.
The above embodiments are only preferred embodiments of the present invention, and the scope of the present invention is not limited thereto, but any insubstantial changes and substitutions made by those skilled in the art on the basis of the present invention are intended to be within the scope of the present invention as claimed.
Claims (1)
1. The application method of the symmetrical point marking device for the semi-enclosed space of the airplane is characterized by comprising the following steps of: the aircraft semi-enclosed space symmetry point marking device comprises
The device comprises a main sliding guide groove (1), a first main sliding guide slide block (2) and a second main sliding guide slide block (13), wherein the first main sliding guide slide block (2) and the second main sliding guide slide block (13) are arranged in the main sliding guide groove and can slide along the main sliding guide groove;
a first auxiliary sliding rocker arm (3) fixedly arranged on the first main sliding guide sliding block and a second auxiliary sliding rocker arm (8) fixedly arranged on the second main sliding guide sliding block (13);
the first auxiliary sliding rocker arm (3) is provided with a first auxiliary sliding groove, and a first auxiliary sliding rocker arm sliding block (7) is arranged in the first auxiliary sliding groove in a sliding manner; the second auxiliary sliding rocker arm (8) is provided with a second auxiliary sliding groove, and a second auxiliary sliding rocker arm sliding block (9) is arranged in the second auxiliary sliding groove in a sliding manner; a first scale line (4) is arranged on the first auxiliary sliding rocker arm (3), and a second scale line (12) is arranged on the second auxiliary sliding rocker arm (8);
a main sliding rocker telescopic rod (6) with the rod length direction perpendicular to the length direction of the first auxiliary sliding rocker is arranged on the first auxiliary sliding rocker sliding block (7); the auxiliary sliding rocker arm telescopic rod (10) with the rod length direction perpendicular to the length direction of the second auxiliary sliding rocker arm is arranged on the second auxiliary sliding rocker arm sliding block (9), wherein in the process that the first auxiliary sliding rocker arm (3) and the second auxiliary sliding rocker arm (8) slide in the main sliding guide groove, at least the end of the main sliding rocker arm telescopic rod (6) and the end of the auxiliary sliding rocker arm telescopic rod (10) can be in contact alignment in opposite directions, and the rod lengths are positioned in the same straight line and can be respectively telescopic in the straight line;
the first auxiliary sliding rocker arm sliding block (7) and/or the first auxiliary sliding rocker arm (3) are/is further provided with a first fixing mechanism for locking the first auxiliary sliding rocker arm sliding block (7) on the first auxiliary sliding rocker arm (3), the first fixing mechanism adopts a first positioning stop nail (5), the first positioning stop nail (5) is arranged on the first auxiliary sliding rocker arm sliding block (7), and the end head of the first positioning stop nail can penetrate through the first auxiliary sliding rocker arm sliding block (7) to be in butt joint with the first auxiliary sliding groove; the second auxiliary sliding rocker arm sliding block (9) or the second auxiliary sliding rocker arm (8) is further provided with a second fixing mechanism for locking the second auxiliary sliding rocker arm sliding block (9) on the second auxiliary sliding rocker arm (8), the second fixing mechanism adopts a second positioning stop nail (11), the second positioning stop nail (11) is arranged on the second auxiliary sliding rocker arm sliding block (9), and the end head of the second positioning stop nail can penetrate through the second auxiliary sliding rocker arm sliding block (9) to be abutted with the second auxiliary sliding groove;
the using method of the aircraft semi-enclosed space symmetry point marking device comprises the following steps:
firstly, marking and positioning a pre-opening position on an airplane according to a digital-analog size, adjusting a first auxiliary sliding rocker slider (7) on a first auxiliary sliding rocker (3) to enable the top point of the end of a main sliding rocker telescopic rod (6) on the first auxiliary sliding rocker to coincide with a pre-opening marking position point on the airplane, and locking a first positioning stop nail (5) to lock the coinciding position;
the removing device is used for adjusting a second main sliding guide sliding block (13) on the main sliding guide groove (1) to be close to the first auxiliary sliding rocker arm (3); on the other hand, a second auxiliary sliding rocker arm sliding block (9) on the second auxiliary sliding rocker arm (8) is adjusted to enable two points on the ends of the telescopic rods of the main sliding rocker arm telescopic rod (6) and the auxiliary sliding rocker arm telescopic rod (10) to coincide; after superposition, locking a second positioning stop nail (11) to ensure that the numerical values of the first auxiliary sliding rocker arm sliding block (7) and the second auxiliary sliding rocker arm sliding block (9) on the first scale line (4) and the second scale line (12) are consistent;
a second main sliding guide sliding block (13) on the main sliding guide groove (1) is adjusted, the distance between the second main sliding guide sliding block and the first main sliding guide sliding block (2) is pulled away, the distance between the second main sliding guide sliding block and the first main sliding guide sliding block is larger than the height of the airplane frame and the beam reinforcing rib, and the device is clamped at the position to be measured of the airplane frame and the beam;
the top point of the end head on the main sliding rocker arm telescopic rod (6) is overlapped with the point of the pre-opening scribing position on the airplane, and the second main sliding guide sliding block (13) on the main sliding guide groove (1) is adjusted to be closed; the vertex positions of the ends of the telescopic rods of the main sliding rocker arm telescopic rod (6) and the auxiliary sliding rocker arm telescopic rod (10) are the starting positions of the holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111237952.1A CN114012688B (en) | 2021-10-25 | 2021-10-25 | Symmetrical point marking device for semi-enclosed space of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111237952.1A CN114012688B (en) | 2021-10-25 | 2021-10-25 | Symmetrical point marking device for semi-enclosed space of airplane |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114012688A CN114012688A (en) | 2022-02-08 |
| CN114012688B true CN114012688B (en) | 2023-07-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111237952.1A Active CN114012688B (en) | 2021-10-25 | 2021-10-25 | Symmetrical point marking device for semi-enclosed space of airplane |
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|---|---|
| CN (1) | CN114012688B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5598760A (en) * | 1994-07-15 | 1997-02-04 | Sucic; Steve | EOP scribe device |
| CN205325658U (en) * | 2015-10-23 | 2016-06-22 | 成都飞机工业（集团）有限责任公司 | Projection marking tool |
| CN110509248A (en) * | 2019-07-26 | 2019-11-29 | 中国航空工业集团公司济南特种结构研究所 | A kind of lineation device for outer mold surface groove in radome |
-
2021
- 2021-10-25 CN CN202111237952.1A patent/CN114012688B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5598760A (en) * | 1994-07-15 | 1997-02-04 | Sucic; Steve | EOP scribe device |
| CN205325658U (en) * | 2015-10-23 | 2016-06-22 | 成都飞机工业（集团）有限责任公司 | Projection marking tool |
| CN110509248A (en) * | 2019-07-26 | 2019-11-29 | 中国航空工业集团公司济南特种结构研究所 | A kind of lineation device for outer mold surface groove in radome |
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| Publication number | Publication date |
|---|---|
| CN114012688A (en) | 2022-02-08 |
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