CN111300318A - Aircraft tail cone frame equipment frock - Google Patents
Aircraft tail cone frame equipment frock Download PDFInfo
- Publication number
- CN111300318A CN111300318A CN202010276501.8A CN202010276501A CN111300318A CN 111300318 A CN111300318 A CN 111300318A CN 202010276501 A CN202010276501 A CN 202010276501A CN 111300318 A CN111300318 A CN 111300318A
- Authority
- CN
- China
- Prior art keywords
- frame
- fixed
- left end
- tail cone
- aircraft tail
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
- B25B11/02—Assembly jigs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Tires In General (AREA)
Abstract
The invention relates to an aircraft tail cone frame assembling tool, wherein a central shaft is arranged above a fixed frame, a hinged frame is arranged at the right end of the fixed frame, a U-shaped notch is formed in the upper end of the hinged frame, the left end of the central shaft penetrates through a supporting plate and a rotating shaft sleeve, the left end of the central shaft is fixed on a left end plate, the right end of the central shaft is arranged in the U-shaped notch, a star-shaped fixed claw is vertically arranged on the central shaft, a fixed pin is arranged on one side of the star-. The invention can be used for fixing, supporting and positioning the aircraft tail cone assembly, and has the advantages of convenient assembly, high assembly efficiency and high assembly precision.
Description
Technical Field
The invention belongs to the technical field of airplane machining tools, and particularly relates to an airplane tail cone frame assembling tool.
Background
The aircraft tail cone refers to the conical structure inside the jet nozzle as part of the overall aircraft fairing profile. The aircraft tail cone frame is formed into a conical structure by a plurality of supporting frames, the long trussed beams and the horizontal tail fixing seats, the supporting frames are used for fixing and supporting the long trussed beams in the aircraft tail cone frame, the horizontal tail fixing seats are fixed at the end portions of the long trussed beams, and the skin is riveted to the aircraft tail cone frame to be assembled into the aircraft tail cone. The shape of the aircraft tail cone is determined by the aircraft tail cone frame, the assembling accuracy and the importance of the aircraft tail cone frame are high, and auxiliary tools are needed to assist assembling and fixing.
Disclosure of Invention
The invention provides an aircraft tail cone frame assembling tool for solving the problems.
In order to solve the problems, the technical scheme adopted by the invention is as follows:
aircraft tail cone frame equipment frock, a serial communication port, which comprises a fixed frame, the center pin, the star stationary dog, the center pin sets up in the mount top, be equipped with two fixed columns on the mount left end, be equipped with the left end board on the fixed column of left side, rotatory axle sleeve, be equipped with the backup pad on the fixed column of right side, be equipped with articulated frame on the mount right-hand member, articulated frame upper end is equipped with the U-shaped notch, the center pin left end runs through the backup pad, rotatory axle sleeve, its left end is fixed in the left end board, the center pin right-hand member sets up in the U-shaped notch, the star stationary dog sets up perpendicularly on the center pin, star stationary dog one side is equipped with the fixed.
The bottom of the hinged frame is fixed with the fixed frame through a locking nut and a fixing pin, and the fixing pin is located on the upper portion of the locking nut.
The invention has the beneficial effects that:
(1) the left end of the central shaft penetrates through the supporting plate and the rotating shaft sleeve, the left end of the central shaft is fixed on the left end plate, the right end of the central shaft is arranged in the U-shaped notch, and the central shaft determines the central line of the aircraft tail cone.
(2) The star-shaped fixing claw is vertically arranged on the central shaft, a fixing pin is arranged on one side of the star-shaped fixing claw, the fixing pin is inserted into a fixing hole in the supporting frame, and the star-shaped fixing claw is used for positioning and fixing the supporting frame.
(3) The stringer is clamped into a groove on the support frame, the stringer is fixed and supported by the support frame, the right end of the stringer is clamped by the horizontal tail fixing seat positioning frame, and the horizontal tail fixing seat is aligned with the horizontal tail fixing seat positioning frame and assembled to the right end of the stringer.
(4) The right end of the fixing frame is provided with a hinged frame, and after the hinged frame is laid down, the assembled aircraft tail cone frame can be detached from the assembling tool.
The method can be used for fixing, supporting and positioning the aircraft tail cone assembly, and is convenient to assemble, high in assembling efficiency and high in assembling accuracy.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is a schematic structural view of an aircraft tail cone mount according to the present invention;
FIG. 2 is a schematic structural view of the aircraft tail cone assembly fixture of the present invention;
FIG. 3 is a schematic structural view of the hinge frame and the fixing frame;
FIG. 4 is a schematic structural view of the aircraft tail cone assembly fixture during assembly;
reference numerals: a support frame-11, a stringer-12 and a horizontal tail fixing seat-13;
the device comprises a fixed frame-21, a central shaft-22, a star-shaped fixed claw-23, a fixed pin-231, a fixed column-24, a left end plate-241, a rotating shaft sleeve-242, a supporting plate-243, a horizontal tail fixed seat positioning frame-25, a hinged frame-26, a U-shaped notch-261, a locking nut-262 and a fixed pin fixing-263.
Detailed Description
The following detailed description of the preferred embodiments of the present invention is provided to enable those skilled in the art to more readily understand the advantages and features of the present invention and to clearly and unequivocally define the scope of the present invention.
Referring to the description and the attached drawing 1, the aircraft tail cone frame comprises a conical structure which is composed of a plurality of supporting frames 11, a stringer beam 12 and a horizontal tail fixing seat 13, wherein the supporting frames play a role in fixing and supporting the stringer beam inside, the horizontal tail fixing seat is fixed at the end part of the stringer beam, and finally a skin is riveted on the aircraft tail cone frame to assemble the aircraft tail cone.
Referring to the description figure 2, aircraft tail cone frame equipment frock, including mount 21, center pin 22, star stationary dog 23, center pin 22 sets up in mount 21 top, be equipped with two fixed columns 24 on the mount 21 left end, be equipped with left end board 241 on the fixed column of left side, rotatory axle sleeve 242, be equipped with backup pad 243 on the fixed column of right side, be equipped with articulated frame 26 on the mount right-hand member, the articulated frame upper end is equipped with U-shaped notch 261, the center pin left end runs through the backup pad, rotatory axle sleeve, its left end is fixed in the left end board, the center pin passes through rivet riveting with the left end board, but the center pin. The star-shaped fixing claws 23 are vertically arranged on the central shaft 22, the size and the position of each star-shaped fixing claw depend on the size and the position of the support frame, one side of each star-shaped fixing claw is provided with a fixing pin 231, the fixing pins are inserted into fixing holes on the support frame, and the star-shaped fixing claws are used for positioning and fixing the support frame. The center pin right-hand member is equipped with horizontal tail fixing base locating frame 25, is equipped with long longeron fixed recess on the horizontal tail fixing base locating frame, and in the recess of carriage was gone into to long longeron card, long longeron right-hand member card was gone into the fixed recess of long longeron on the horizontal tail fixing base locating frame, whole long longeron was fixed, was supported, was fixed a position, connects horizontal tail fixing base at long longeron right-hand member. The structure diagram of the whole aircraft tail cone frame after the aircraft tail cone and the assembly tool are assembled is shown in the attached figure 4 of the participation specification.
Referring to fig. 3, the bottom of the hinged frame 26 is fixed to the fixed frame 21 by a locking nut 262 and a fixing pin 263, and the fixing pin 263 is located at the upper part of the locking nut. The hinged rack can be laid down, when the fixing pin is detached and the locking nut is loosened, the hinged rack is laid down around the screw rod of the locking nut, and the aircraft tail cone frame can be detached from the assembling tool at the moment. When the hinge frame is assembled, the hinge frame is righted, the fixing pin is inserted into the jacks of the hinge frame and the fixing frame, and the hinge frame and the fixing frame are locked by the locking nut.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, that the preferred embodiments of the present invention are described above and the present invention is not limited to the preferred embodiments, and that various changes and modifications may be made without departing from the spirit and scope of the present invention and these changes and modifications are within the scope of the invention as claimed.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (2)
1. Aircraft tail cone frame equipment frock, a serial communication port, which comprises a fixed frame, the center pin, the star stationary dog, the center pin sets up in the mount top, be equipped with two fixed columns on the mount left end, be equipped with the left end board on the fixed column of left side, rotatory axle sleeve, be equipped with the backup pad on the fixed column of right side, be equipped with articulated frame on the mount right-hand member, articulated frame upper end is equipped with the U-shaped notch, the center pin left end runs through the backup pad, rotatory axle sleeve, its left end is fixed in the left end board, the center pin right-hand member sets up in the U-shaped notch, the star stationary dog sets up perpendicularly on the center pin, star stationary dog one side is equipped with the fixed.
2. The aircraft tail cone assembly tool according to claim 1, wherein the bottom of the hinged frame is fixed with the fixed frame through a locking nut and a fixing pin, and the fixing pin is located on the upper portion of the locking nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010276501.8A CN111300318A (en) | 2020-04-10 | 2020-04-10 | Aircraft tail cone frame equipment frock |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010276501.8A CN111300318A (en) | 2020-04-10 | 2020-04-10 | Aircraft tail cone frame equipment frock |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111300318A true CN111300318A (en) | 2020-06-19 |
Family
ID=71155771
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010276501.8A Pending CN111300318A (en) | 2020-04-10 | 2020-04-10 | Aircraft tail cone frame equipment frock |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111300318A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112719883A (en) * | 2020-12-21 | 2021-04-30 | 北京航星机器制造有限公司 | Assembly tool |
-
2020
- 2020-04-10 CN CN202010276501.8A patent/CN111300318A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112719883A (en) * | 2020-12-21 | 2021-04-30 | 北京航星机器制造有限公司 | Assembly tool |
| CN112719883B (en) * | 2020-12-21 | 2022-06-10 | 北京航星机器制造有限公司 | Assembly tool |
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