CN113104231A - Device and method for positioning integral frame of airplane - Google Patents
Device and method for positioning integral frame of airplane Download PDFInfo
- Publication number
- CN113104231A CN113104231A CN202110331174.6A CN202110331174A CN113104231A CN 113104231 A CN113104231 A CN 113104231A CN 202110331174 A CN202110331174 A CN 202110331174A CN 113104231 A CN113104231 A CN 113104231A
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- Prior art keywords
- sliding sleeve
- sliding
- pin
- positioning
- sliding pin
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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 belongs to the technical field of airplane assembly, and particularly relates to a device and a method for positioning an integral frame of an airplane. The positioning device comprises a sliding sleeve, a refined bolt, a nut, a compression nut, a flange plate and a sliding pin; the sliding sleeve is of a lug-shaped structure, mounting holes are formed in two ends of the lug, and the sliding sleeve is fixed on the mounting base body by matching with a refined bolt and a nut; the axis of the sliding sleeve is of a sleeve type structure, a semi-arc boss is arranged at the end part of the sliding sleeve, and a clamping groove is formed in the boss; the sliding pin is a stepped shaft, and the shaft section with the smallest diameter and the next smallest diameter is provided with threads which are respectively matched with the compression nut and the flange plate; the shaft section with the largest diameter of the pin shaft is provided with an annular boss, and the annular boss is provided with a notch; the sliding pin is rotated to enable the annular boss to be matched with the clamping groove in the sliding sleeve, and locking and releasing of the sliding pin are achieved. The device can effectively position and assemble the whole frame of the airplane, and achieves the purposes of simple manufacture, convenient use and accurate positioning. Meanwhile, the occupied time in the frame is reduced, and the assembly efficiency is improved.
Description
Technical Field
The invention belongs to the technical field of airplane assembly, and particularly relates to a device and a method for positioning an integral frame of an airplane.
Background
Aircraft upper frames have long been assembled in the form of discrete parts. The method comprises the following steps: firstly, a common frame edge positioner is used for positioning a frame edge (or a web plate) in a frame, and then the frame is gradually put on the frame according to the space geometric dimension relation among other parts on the frame, the frame edge (or the web plate) and the airplane to complete assembly. The number of parts is large, the positions are scattered, so that the assembly period occupied by the parts in the frame is long, and the production efficiency is reduced; the dispersed positioning of each frame also leads to inaccurate positioning of the whole frame body, and products are not easy to get off the shelf after the assembly is finished. With the increasing demand for aircraft production batches, this approach has become increasingly unable to meet production line requirements.
In view of such situations, it is necessary to design an integral frame positioning device, which effectively avoids the above disadvantages of the conventional positioning devices, and can realize the combination of the integral frame outside the frame, thereby not only meeting the requirement of positioning accuracy, but also improving the production efficiency and meeting the assembly requirement of the production line.
Disclosure of Invention
The purpose of the invention is as follows: the invention aims to solve the technical problems that parts are combined outside a frame into an integral frame, the occupied time in the frame is reduced, and an integral frame positioning device is designed. Also machined frames and similar parts can be mounted in this way.
The technical scheme is as follows: in order to solve the technical problems, the technical scheme of the invention is as follows: designing a positioning device for an integral frame of an airplane, wherein the positioning device comprises a sliding sleeve, a refined bolt, a nut, a compression nut, a flange plate and a sliding pin; the sliding sleeve is of a lug-shaped structure, mounting holes are formed in two ends of the lug, and the sliding sleeve is fixed on the mounting base body by matching with a refined bolt and a nut; the axis of the sliding sleeve is of a sleeve type structure, a semi-arc boss is arranged at the end part of the sliding sleeve, and a clamping groove is formed in the boss; the sliding pin is a stepped shaft, and the shaft section with the smallest diameter and the next smallest diameter is provided with threads which are respectively matched with the compression nut and the flange plate; the shaft section with the largest diameter of the pin shaft is provided with an annular boss, and the annular boss is provided with a notch; the sliding pin is rotated to enable the annular boss to be matched with the clamping groove in the sliding sleeve, and locking and releasing of the sliding pin are achieved.
Preferably, the flange is provided with lightening holes so as to reduce the weight of the whole device.
Preferably, the compression nut is provided with a pin hole, and the pin hole is matched with the handle to realize the adjustment of the compression nut.
Preferably, the end of the shaft section with the largest diameter of the sliding pin is a hexagonal boss, and a pin hole is formed in the hexagonal boss and matched with a handle to realize adjustment of the sliding pin.
Preferably, the sliding sleeve mounting surface is of a lug type structure, so that the contact area is increased, and the mounting precision is improved by matching dispersed refined bolts and nuts.
A method for realizing the positioning of an integral frame of an airplane based on the positioning device comprises the steps of firstly installing a sliding sleeve of the positioning device on a preset positioning hole of a base body, then inserting a sliding pin into an inner hole of the sliding sleeve, and rotating to enable an annular boss of the sliding pin to be screwed into a clamping groove of the sliding sleeve; mounting the flange plate on the secondary small-diameter shaft section of the sliding pin, and ensuring that the end face of the flange plate is fitted with the step shaft end face of the sliding pin; mounting the integral frame on the shaft section with the minimum diameter of the sliding pin, and locking the integral frame by using a compression nut; the positioning devices are multiple and form a triangular form.
Preferably, the number of the positioning devices is three, and the three positioning devices form a triangle.
The invention has the beneficial effects that: the device can effectively position and assemble the whole frame of the airplane, is convenient to adjust, use and position, is accurate, is convenient to mount, reduces the occupied time in the frame, improves the assembly efficiency and improves the assembly quality of products; the positioning structure provided by the invention is simple, good in interchangeability and convenient to install and disassemble; after the product is changed, only the individual parts need to be adaptively designed. The sliding pin and the sliding sleeve are locked by adopting a self structure without depending on other auxiliary locking mechanisms, so that the structure is more simplified, and the operation is more convenient.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a front view of the apparatus of the present invention in an assembled position;
FIG. 3 is a left side view of the apparatus of the present invention in an assembled position;
FIG. 4 is a schematic view of a sliding sleeve structure;
FIG. 5 is a schematic view of a compression nut;
FIG. 6 is a schematic view of the flange structure;
FIG. 7 is a schematic view of a slide pin construction;
wherein, 1-sliding pin; 2-a sliding sleeve; 3-refining the bolt; 4-mounting a substrate; 5-a nut; 6-integral frame; 7-a compression nut; 8-a flange plate; 9-handle.
Detailed Description
The following further describes the embodiments of the present invention with reference to the drawings.
As shown in fig. 1; the invention provides a positioning device for an integral frame of an airplane, which comprises a sliding sleeve 2, a refined bolt 3, a nut 5, a compression nut 7, a flange plate 8 and a sliding pin 1; wherein, the sliding sleeve 2 is connected on the installation base 4 through the refined bolt 3 and the nut 5, then the sliding pin 1 passes through the sliding sleeve 2, then the flange plate 8 is connected with the sliding pin 1 through the screw thread, finally the whole frame 6 is compressed by the special compression nut 7, so that the whole frame is tightly attached to the flange plate 8, in order to realize the self-locking between the sliding sleeve 2 and the sliding pin 1, the end part of the sliding sleeve 2 is provided with an arc-shaped boss, and the boss is provided with a clamping groove; meanwhile, an annular boss is arranged on the sliding pin 1, a notch is arranged on the annular boss, the shape of the notch is similar to that of the clamping groove, and the sliding pin 1 and the sliding sleeve 2 can be locked when the annular boss is screwed into the clamping groove of the sliding sleeve 1 by rotating the sliding pin 1; and the sliding pin 1 continues to rotate, and after the annular boss completely exits from the clamping groove, the sliding pin and the sliding sleeve can be separated and unlocked.
Referring to fig. 2-3, the positioning device of the integral frame is composed of three sets of integral frame positioners, which are distributed in a triangle shape and coordinate with the process positioning holes on the integral frame 6 when the mounting substrate 4 is mounted; and (3) compressing the integral frame 6 by using a compression nut 7 to ensure that the integral frame 6 is tightly attached to the flange plate 8, thereby finishing the assembly of the integral frame 6 in the airplane.
The specific assembly process is as follows:
1) a sliding sleeve 2 is arranged on the installation base body 4, is coordinated with a process positioning hole on the integral frame 6 and is connected with a refined bolt 3 and a nut 5;
2) the sliding pin 1 penetrates through the sliding sleeve 2;
3) a flange plate 8 is arranged at the end of the sliding pin 1 to increase the positioning surface;
4) the positioning polished rod at the end of the sliding pin 1 penetrates through the technical positioning hole on the integral frame 6, so that the positioning surface on the integral frame 6 is attached to the positioning surface of the flange plate;
5) rotating the sliding pin 1 to enable the clamping groove 11 in the sliding sleeve 2 to clamp the edge opening 12 in the sliding pin 1;
6) the whole frame 6 is tightly pressed by a compression nut 7 for assembly;
7) after the assembly is finished, the compression nut 7 is screwed out;
8) rotating the sliding pin 1 to align the notch 13 on the sliding pin 1 with the clamping groove 11 in the sliding sleeve 2;
9) the sliding pin is slid to the left, so that the sliding pin is disengaged from the sliding sleeve and is put down, see fig. 2.
For the assembly process, after the whole assembly process is finished, the lower frame of the frame can be finished only by screwing out the compression nut, and other parts do not need to be disassembled, so that the workload is greatly reduced, and the time is shortened. Because the sliding sleeve can realize repeated positioning without being disassembled, the abrasion of the base body mounting hole caused by repeated disassembly is avoided, and the positioning precision of the whole structure is ensured to the maximum extent. And after the new frame is put on the shelf, the positioning can be realized by only repeating the steps 6), 7) and 8), and the whole process is simple and efficient. The positioning device and the positioning method provided by the invention can effectively position and assemble the whole frame of the airplane, and achieve the purposes of simple manufacture, convenient use and accurate positioning. Meanwhile, the occupied time in the frame is reduced, and the assembly efficiency is improved.
While specific embodiments of the present invention have been described above, it should be noted that the above embodiments are not all routine techniques in the art; the invention is not limited to the specific embodiments described above, wherein equipment and structures not described in detail are understood to be practiced in a manner common in the art; numerous other and varied variations, changes or substitutions may be made by those skilled in the art without departing from the spirit of the invention, which falls within the scope of the claims; such modifications are to be considered as falling within the scope of the present invention.
Claims (9)
1. The utility model provides an aircraft whole frame positioner which characterized in that: the device comprises a sliding sleeve, a refined bolt, a nut, a compression nut, a flange plate and a sliding pin; the sliding sleeve is of a lug-shaped structure, mounting holes are formed in two ends of the lug, and the sliding sleeve is fixed on the mounting base body by matching with a refined bolt and a nut; the axis of the sliding sleeve is of a sleeve type structure, a semi-arc boss is arranged at the end part of the sliding sleeve, and a clamping groove is formed in the boss; the sliding pin is a stepped shaft, and the shaft section with the smallest diameter and the next smallest diameter is provided with threads which are respectively matched with the compression nut and the flange plate; a round boss is arranged on the shaft section with the largest diameter of the pin shaft, and a notch is arranged on the round boss; the sliding pin is rotated to enable the annular boss to be matched with the clamping groove in the sliding sleeve, and locking and releasing of the sliding pin are achieved.
2. The positioning device for an aircraft monoblock frame according to claim 1, wherein: the sliding sleeve mounting surface is of a lug type structure and is matched with dispersed refined bolts and nuts.
3. The positioning device for an aircraft monoblock frame according to claim 1, wherein: the compression nut is provided with a pin hole, and the pin hole is matched with the handle to realize the adjustment of the compression nut.
4. The positioning device for an aircraft monoblock frame according to claim 1, wherein: the end part of the shaft section with the maximum diameter of the sliding pin is provided with a hexagonal boss.
5. An aircraft monoblock positioning device according to claim 4, characterized in that: the hexagonal boss is provided with a pin hole which is matched with the handle to realize the adjustment of the sliding pin.
6. A method for realizing positioning of an integral frame of an airplane based on the positioning device of any one of claims 1 to 5, wherein the method comprises the following steps: firstly, installing a sliding sleeve of a positioning device on a preset positioning hole of a base body, then inserting a sliding pin into an inner hole of the sliding sleeve, and rotating to enable an annular boss of the sliding pin to be screwed into a clamping groove of the sliding sleeve; mounting the flange plate on the secondary small-diameter shaft section of the sliding pin, and ensuring that the end face of the flange plate is fitted with the step shaft end face of the sliding pin; and mounting the integral frame on the shaft section with the minimum diameter of the sliding pin, and locking the integral frame by using a compression nut.
7. The method of positioning an aircraft monoblock as recited in claim 6, wherein: the number of the positioning devices is three, and the three positioning devices form three vertexes of a triangle.
8. The method of positioning an aircraft monoblock as recited in claim 6, wherein: the area of the end face of the flange plate attached to the end face of the step shaft of the sliding pin is increased.
9. The method of claim 8, wherein: and the end face of the flange plate is subjected to fairing treatment to ensure the surface flatness.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110331174.6A CN113104231A (en) | 2021-03-26 | 2021-03-26 | Device and method for positioning integral frame of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110331174.6A CN113104231A (en) | 2021-03-26 | 2021-03-26 | Device and method for positioning integral frame of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113104231A true CN113104231A (en) | 2021-07-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110331174.6A Pending CN113104231A (en) | 2021-03-26 | 2021-03-26 | Device and method for positioning integral frame of airplane |
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| CN (1) | CN113104231A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113500551A (en) * | 2021-08-19 | 2021-10-15 | 沈阳飞机工业（集团）有限公司 | Multi-support-arm sheet metal frame assembling and positioning device and using method thereof |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201597759U (en) * | 2009-11-23 | 2010-10-06 | 西安飞机工业（集团）有限责任公司 | Airplane flange locator |
| CN203111529U (en) * | 2013-02-27 | 2013-08-07 | 中航飞机股份有限公司西安飞机分公司 | Airplane frame-edge locating mechanism |
| KR20160003485U (en) * | 2016-01-08 | 2016-10-10 | 대한민국(국방부 공군참모총장) | A Tool for Disjointing Metering Pin |
-
2021
- 2021-03-26 CN CN202110331174.6A patent/CN113104231A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201597759U (en) * | 2009-11-23 | 2010-10-06 | 西安飞机工业（集团）有限责任公司 | Airplane flange locator |
| CN203111529U (en) * | 2013-02-27 | 2013-08-07 | 中航飞机股份有限公司西安飞机分公司 | Airplane frame-edge locating mechanism |
| KR20160003485U (en) * | 2016-01-08 | 2016-10-10 | 대한민국(국방부 공군참모총장) | A Tool for Disjointing Metering Pin |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113500551A (en) * | 2021-08-19 | 2021-10-15 | 沈阳飞机工业（集团）有限公司 | Multi-support-arm sheet metal frame assembling and positioning device and using method thereof |
| CN113500551B (en) * | 2021-08-19 | 2024-03-08 | 沈阳飞机工业（集团）有限公司 | Multi-support arm sheet metal frame assembly positioning device and use method thereof |
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Application publication date: 20210713 |