CN105667831A - Rivet-assembling method for helicopter transitional section - Google Patents
Rivet-assembling method for helicopter transitional section Download PDFInfo
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- CN105667831A CN105667831A CN201610130463.9A CN201610130463A CN105667831A CN 105667831 A CN105667831 A CN 105667831A CN 201610130463 A CN201610130463 A CN 201610130463A CN 105667831 A CN105667831 A CN 105667831A
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- frame
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- rivet
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- riveted joint
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Abstract
The invention belongs to helicopter rivet-assembling. According to the technical scheme of the invention, a rivet-assembling method for a helicopter transitional section comprises the following steps of manufacturing a technical 5-frame which is completely as same as a 5-frame of a middle body of a helicopter in structure and dimension; mounting the technical 5-frame on a transitional section rivet-assembling fixture, wherein the position of the technical 5-frame is as same as the position of the 5-frame of the middle body of the helicopter after the technical 5-frame is abut-jointed; laying an engine upper platform, a ladder locating bracket, a handle, a left horizontal piece, a right horizontal piece and a landing gear joint component on the upper surface of the technical 5-frame or in an interior vertical steel bar to be riveted; pressing front and back skins on the left and right sides of the technical 5-frame to be riveted; pressing the bottom of the transitional section on the lower surface of the technical 5-frame upwards to be riveted; simultaneously riveting and assembling other parts of the helicopter transitional section on the transitional section rivet-assembling fixture; and after the rivet-assembling of all parts are finished, detaching the helicopter transitional section from the transitional section rivet-assembling fixture.
Description
Technical field
The invention belongs to aircraft riveted joint assembling, it relates to aircraft transition section riveted joint assembly method
Background technology
Certain model vertiplane existing find in assembling process this vertiplane at transition section front end big uncork, there is no product 5 frame, cause manufacturability herein weak, easy deformation, when docking with middle fuselage, there is the inaccurate problem of docking.
Summary of the invention
The technical problem to be solved in the present invention: provide a kind of aircraft transition section riveted joint assembly method, it is possible to solve vertiplane transition section and dock inaccurate problem with middle fuselage.
The technical scheme of the present invention: a kind of aircraft transition section riveted joint assembly method comprises:
Manufacture 5 frame structures with fuselage in vertiplane, size completely technique 5 frame;
Being arranged on by described technique 5 frame in transition section riveted joint assembling type frame, the position of described technique 5 frame is identical with the position residing for fuselage 5 frame in vertiplane after docking;
Platform on engine, ladder locating support, handle, left and right horizontal part, landing gear adapter assembly are ridden over and rivet on the vertical muscle of upper surface or inside of described technique 5 frame, front and back covering is pressed in the described technique 5 frame left and right sides rivet, rivets being upwards pressed in described technique 5 frame lower surface bottom transition section;
Transition section riveted joint assembling type frame carries out the riveted joint assembling at other positions of vertiplane transition section simultaneously;
After all riveted joint assemblings complete, vertiplane transition section is removed transition section riveted joint assembling type frame.
The useful effect of the present invention: the present invention confines position by technique 5 and rivets the hole drilling on aircraft structure, to avoid herein due to without any support, make transition section Product Process weak, easy deformation, the coordination problem such as gap, rank difference occurs when docking to general assembly, meet the matching requirements of product, it is to increase conforming product rate.
Accompanying drawing explanation
Fig. 1 is aircraft transition section riveted joint assembling type frame structural representation in the embodiment of the present invention.
Fig. 2 is technique 5 frame structural representation in the embodiment of the present invention.
Embodiment
Below with reference to drawings and Examples, technical solution of the present invention is further described:
The technical scheme of the present invention: a kind of aircraft transition section riveted joint assembly method comprises:
Step 1, manufacture the 5 frame structure with fuselage in vertiplane, a size completely technique 5 frame.
In step 2, described technique 5 frame is arranged on transition section riveted joint assembling type frame, the position of described technique 5 frame is identical with the position residing for fuselage 5 frame in docking afterwards vertiplane.
Step 3, the upper surface that platform on engine, ladder locating support, handle, left and right horizontal part, landing gear adapter assembly are ridden over described technique 5 frame or inner vertical muscle are riveted, front and back covering is pressed in the described technique 5 frame left and right sides rivet, rivets being upwards pressed in described technique 5 frame lower surface bottom transition section.
Step 4, the riveted joint assembling simultaneously carrying out other positions of vertiplane transition section in transition section riveted joint assembling type frame.
After step 5, all riveted joint assemblings complete, vertiplane transition section is removed transition section riveted joint assembling type frame.
Embodiment
Shown in FIGS 1 and 2, the present invention is a kind of aircraft transition section riveted joint assembly method, is ensured by aircraft transition section riveted joint assembling type frame. aircraft transition section riveted joint assembling type frame, comprises technique 5 frame (1), 6 frame clamps (2), 7 frame clamps (3), 8 frame clamps (4), web plate (5), type frame framework (6), auxiliary part (7). technique 5 frame (1), 6 frame clamps (2), 7 frame clamps (3), the fixing strengthening of web plate (5) of the junction of 8 frame clamps (4) and type frame framework (6), type frame framework (6) amplifies and technique 5 frame (1) according to the profile of aircraft transition section, 6 frame clamps (2), 7 frame clamps (3), size after the installation of 8 frame clamps (4), square steel is selected to be welded, in order to transition section product takes off type frame, use as during product undercarriage with auxiliary part (7) below type frame, can with go-cart, guide rail, runner, screw block fixed block etc., effect prevents in go-cart after product is opened type frame, the transition section product after riveted joint assembling is released type frame.
Ensured by aircraft transition section riveted joint assembling type frame. 5-8 frame transition section manufactures and designs the benchmark that complete technique 5 frame the same with product 5 frame M533G1501051 docks with middle fuselage as tool locating, designs, manufactures other positioning element in transition section type frame. The advantage confining this kind of method of design in position by technique 5 is the accuracy that accurately located transition section and middle fuselage docking location in PT1 triturating. Ensure that the interior shape of platform two side bars, the connection relation of left-right longeron, horizontal element, bottom covering and middle fuselage 5 frame, weak in transition section front end big uncork, manufacturability, when there is no product 5 frame, solve manufacturability herein weak and dock the many coordination problems occurred.
The technical process of this frock is used to be:
1, bottom transition section, first frame of 6 frames, first frame of 7 frames, 8 frames, upper platform by pilot hole in transition section type frame inner position in frock;
2, web member location riveted joint;
3, use cargo door that ability tool locating cargo door doorframe is installed, drill hinge, angle box connection hole; Use ladder positioning tool location boarding ladder part;
4, pilot hole is pressed in the location of each covering, its clamping snub rope.
5, cargo door doorframe, front and back covering, ladder part, handle, left and right horizontal part, high-performance landing gear adapter assembly is riveted;
6, product undercarriage;
7, payment is always examined.
The processing method more than carried out is through the Installation Validation of PT1 frame, PT3 frame, and transition section parts dock with middle fuselage, decrease the generation of coordination problem, ensure that and has met the requirement of product drawing by the overall dimensions that finished product is installed, proves that process program is effective.
Claims (1)
1. an aircraft transition section riveted joint assembly method, it is characterised in that, comprising:
Manufacture 5 frame structures with fuselage in vertiplane, size completely technique 5 frame;
Being arranged on by described technique 5 frame in transition section riveted joint assembling type frame, the position of described technique 5 frame is identical with the position residing for fuselage 5 frame in vertiplane after docking;
Platform on engine, ladder locating support, handle, left and right horizontal part, landing gear adapter assembly are ridden over and rivet on the vertical muscle of upper surface or inside of described technique 5 frame, front and back covering is pressed in the described technique 5 frame left and right sides rivet, rivets being upwards pressed in described technique 5 frame lower surface bottom transition section;
Transition section riveted joint assembling type frame carries out the riveted joint assembling at other positions of vertiplane transition section simultaneously;
After all riveted joint assemblings complete, vertiplane transition section is removed transition section riveted joint assembling type frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610130463.9A CN105667831A (en) | 2016-03-08 | 2016-03-08 | Rivet-assembling method for helicopter transitional section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610130463.9A CN105667831A (en) | 2016-03-08 | 2016-03-08 | Rivet-assembling method for helicopter transitional section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105667831A true CN105667831A (en) | 2016-06-15 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610130463.9A Pending CN105667831A (en) | 2016-03-08 | 2016-03-08 | Rivet-assembling method for helicopter transitional section |
Country Status (1)
| Country | Link |
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| CN (1) | CN105667831A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106346657A (en) * | 2016-12-07 | 2017-01-25 | 沈阳橡胶研究设计院有限公司 | Technical method for vulcanizing butt joint connector of sealing ring of airplane engine transition section assembly |
| CN112719883A (en) * | 2020-12-21 | 2021-04-30 | 北京航星机器制造有限公司 | Assembly tool |
Citations (5)
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| CN103303491A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Abutting technological equipment of airplane large components and abutting method thereof |
| DE102012005642A1 (en) * | 2012-03-22 | 2013-09-26 | Brötje-Automation GmbH | Method for producing an aircraft-fuselage section, involves reverting outer membrane segment, double-segment reinforcing edge of exit opening and frame segment with each other |
| CN104118575A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Aircraft main landing gear hatch door assembling coordinate platform |
| EP2883797A1 (en) * | 2013-12-16 | 2015-06-17 | Airbus Operations GmbH | Method and apparatus for manufacturing a structural component for an aircraft or spacecraft |
| CN105253325A (en) * | 2015-11-11 | 2016-01-20 | 北京特种机械研究所 | Aircraft main landing gear assembling and disassembling equipment |
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2016
- 2016-03-08 CN CN201610130463.9A patent/CN105667831A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103303491A (en) * | 2012-03-09 | 2013-09-18 | 陕西飞机工业（集团）有限公司 | Abutting technological equipment of airplane large components and abutting method thereof |
| DE102012005642A1 (en) * | 2012-03-22 | 2013-09-26 | Brötje-Automation GmbH | Method for producing an aircraft-fuselage section, involves reverting outer membrane segment, double-segment reinforcing edge of exit opening and frame segment with each other |
| CN104118575A (en) * | 2013-04-24 | 2014-10-29 | 哈尔滨飞机工业集团有限责任公司 | Aircraft main landing gear hatch door assembling coordinate platform |
| EP2883797A1 (en) * | 2013-12-16 | 2015-06-17 | Airbus Operations GmbH | Method and apparatus for manufacturing a structural component for an aircraft or spacecraft |
| CN105253325A (en) * | 2015-11-11 | 2016-01-20 | 北京特种机械研究所 | Aircraft main landing gear assembling and disassembling equipment |
Non-Patent Citations (1)
| Title |
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| 刘巍: "《某型机过渡段铆接工艺性研究》", 《中国高新技术企业》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106346657A (en) * | 2016-12-07 | 2017-01-25 | 沈阳橡胶研究设计院有限公司 | Technical method for vulcanizing butt joint connector of sealing ring of airplane engine transition section assembly |
| CN106346657B (en) * | 2016-12-07 | 2018-10-12 | 沈阳橡胶研究设计院有限公司 | Aircraft engine changeover portion assembly sealing ring banjo fixing butt jointing vulcanization process |
| CN112719883A (en) * | 2020-12-21 | 2021-04-30 | 北京航星机器制造有限公司 | Assembly tool |
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Application publication date: 20160615 |