CN103192985A - Novel integrated structure pull bar for airplane - Google Patents
Novel integrated structure pull bar for airplane Download PDFInfo
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- CN103192985A CN103192985A CN2012100049540A CN201210004954A CN103192985A CN 103192985 A CN103192985 A CN 103192985A CN 2012100049540 A CN2012100049540 A CN 2012100049540A CN 201210004954 A CN201210004954 A CN 201210004954A CN 103192985 A CN103192985 A CN 103192985A
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- pull bar
- hollow
- rod
- fork
- aircraft
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Abstract
A novel integrated structure pull bar for an airplane comprises a hollow pull bar body (1), forks (2) and tapered transition portions (3), the hollow pull bar body (1) of the structure pull bar is a hollow tube, two ends of the hollow pull bar body (1) are provided with the single-prong-shaped or double-prong-shaped forks (2) respectively, prong-shaped portions are provided with mounting holes, and one of the tapered transition portions (3) is adopted between the hollow pull bar body (1) and one of the bar ends. The novel integrated structure pull bar for an airplane has the advantages of simple structure, large bearing capability, easy realization of the series and batch production, and low integrated manufacturing cost.
Description
Technical field
The present invention relates to aircraft with novel overall formula structure pull bar, belong to the aviation machine technical field.
Background technology
Pull bar is to transmit the typical primary structure member that axial load is the master, mostly is hollow structure, has a wide range of applications in aeroplane structure design, and particularly the application aspect mechanical manoeuvring system and hatch door control system is more general.The existing structure rod material is aluminum alloy, adopts one-piece construction, and the body of rod is hollow structure, and single tine shape or two fork-shaped are processed in body of rod two ends, and manufacturing process is comparatively complicated.This structure is comparatively common in American-European developed country, and China mainly relies on import, and is expensive.The present invention adopts the lower manufacturing process of material, cost still less by above-mentioned one-piece construction pull bar is redesigned, and realizes the production domesticization of this type one-piece construction pull bar smoothly.
Summary of the invention
The objective of the invention is in order to solve existing integral type pull bar manufacturing process complexity, manufacturing cost is higher, foreign technology blocks problem, patent of the present invention provides the novel overall formula structure that a kind of manufacturing process is simple, manufacturing cost is relatively low pull bar.
The present invention is achieved through the following technical solutions goal of the invention:
A kind of aircraft novel overall formula structure pull bar, comprise the hollow pull rod body of rod, fork, tapering transition, the hollow pull rod body of rod of this structure pull bar is hollow tube, hollow pull rod body of rod two ends are the fork of single tine shape or two fork-shapeds, fork portion is provided with mounting hole, adopts tapering transition between the described hollow pull rod body of rod and the rod end.
Pull bar blank of the present invention adopts hollow high strength aluminum alloy pipe.
The wall thickness of the body of rod of hollow pull rod described in the present invention is between 0.5-5mm.
The position of fork described in the present invention thickness manys 0.5-5mm than the wall thickness of the described hollow pull rod body of rod.
The centre distance of mounting hole described in the present invention is between 100-2000mm.
Fabrication scheme of the present invention, aircraft adopts hollow high strength aluminum alloy 2024 pipes through the technology manufacturing of swaging with novel overall formula structure pull bar pipe, to increase the overall mechanical properties of the body of rod.Utilize high strength aluminum alloy 2024 good ductility, the pull bar pipe end adopts both-end cold extruding formation process or precision die-forging forming processes, adopt special solution hardening treatment process to improve pull bar integrated carrying ability simultaneously, adopt anode oxidation process and Electrostatic Spray Technology raising pull bar resistance to corrosion and beautify outward appearance.
Advantage of the present invention, aircraft of the present invention is simple with novel overall formula structure Tiebar structure, and load-carrying capacity is bigger, realizes seriation, mass production easily, and whole manufacturing cost is lower.
Description of drawings
Fig. 1 aircraft of the present invention novel overall formula structure pull bar (dual forked type) structural representation;
Fig. 2 aircraft of the present invention novel overall formula structure pull bar (single tine type) structural representation.
Wherein, the 1-hollow pull rod body of rod, 2-fork, 3-tapering transition
The specific embodiment
Below by specific embodiment the present invention is described in further detail:
A kind of aircraft novel overall formula structure pull bar, comprise the hollow pull rod body of rod 1, fork 2, tapering transition 3, the hollow pull rod body of rod 1 of this structure pull bar is hollow tube, the hollow pull rod body of rod 1 two ends are the fork 2 of single tine shape or two fork-shapeds, fork portion is provided with mounting hole, adopt tapering transition 3 between the hollow pull rod body of rod 1 and the rod end, pull bar blank among the present invention adopts hollow high strength aluminum alloy pipe, the wall thickness of the hollow pull rod body of rod 1 of the present invention is between 0.5-5mm, fork 2 position thickness many 0.5-5mm than the wall thickness of the described hollow pull rod body of rod 1, and mounting hole centre distance is between 100-2000mm.
Pull bar blank of the present invention adopts the hollow high strength aluminum alloy Guan Jing technology manufacturing of swaging, the pull bar pipe end adopts both-end fashion of extrusion moulding or precision drop forging mode forming technique to make, the present invention adopts special solution hardening treatment process to improve pull bar integrated carrying ability, adopts anode oxidation process and electrostatic painting process raising pull bar resistance to corrosion and beautifies outward appearance.
See also Fig. 1, it is aircraft of the present invention novel overall formula structure pull bar (dual forked type) structural representation.In this scheme drawing, pull bar integral body comprises the hollow pull rod body of rod 1, fork 2, tapering transition 3 three parts.Hollow draw-bar blank body adopts high strength aluminum alloy 2024 materials, is processed into thin-walled hollow type structure by the method for swaging, with low weight and the high strength that keeps the whole pull bar body of rod.The pull bar pipe end adopts the one-shot forming of both-end extrusion forming mode, by design precision die and proper heat treatment technology, avoid pipe end unstability, cracking phenomena in the forming process, and by accurate machining process and special solution hardening treatment process, finally be processed into Fig. 1 structure.This structure improves the pull bar resistance to corrosion and beautifies outward appearance through anodic oxidation treatment technology and Electrostatic Spray Technology.
See also Fig. 2, it is aircraft of the present invention novel overall formula structure pull bar (single tine type) structural representation.In this scheme drawing, pull bar integral body comprises the hollow pull rod body of rod 1, fork 2, tapering transition 3 three parts.Hollow draw-bar blank body adopts high strength aluminum alloy 2024 materials, is processed into thin-walled hollow type structure by the method for swaging, to keep the high strength of the whole pull bar body of rod.The pull bar pipe end adopts the one-shot forming of die-forging forming mode, by design precision die and proper heat treatment technology, avoid rod end unstability, cracking phenomena in the forming process, and by accurate machining process and special solution hardening treatment process, finally be processed into Fig. 2 structure.This structure improves the pull bar resistance to corrosion and beautifies outward appearance through anodic oxidation treatment technology and Electrostatic Spray Technology.Aircraft of the present invention is simple with novel overall formula structure Tiebar structure, and load-carrying capacity is bigger, and manufacturing cost is relatively low, realizes seriation, mass production easily.
Claims (5)
1. an aircraft is with novel overall formula structure pull bar, it is characterized in that, comprise the hollow pull rod body of rod (1), fork (2), tapering transition (3), the hollow pull rod body of rod (1) of this structure pull bar is hollow tube, the hollow pull rod body of rod (1) two ends are the fork (2) of single tine shape or two fork-shapeds, fork portion is provided with mounting hole, adopts tapering transition (3) between the described hollow pull rod body of rod (1) and the rod end.
2. aircraft as claimed in claim 1 is characterized in that: pull bar blank employing hollow high strength aluminum alloy pipe with novel overall formula structure pull bar.
3. aircraft as claimed in claim 1 or 2 is with novel overall formula structure pull bar, and it is characterized in that: the wall thickness of the described hollow pull rod body of rod (1) is between 0.5-5mm.
4. aircraft as claimed in claim 3 is characterized in that with novel overall formula structure pull bar: described fork (2) position thickness manys 0.5-5mm than the wall thickness of the described hollow pull rod body of rod (1).
5. aircraft as claimed in claim 1 is with novel overall formula structure pull bar, and it is characterized in that: described mounting hole centre distance is between 100-2000mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210004954.0A CN103192985B (en) | 2012-01-10 | 2012-01-10 | Aircraft Novel integral structure pull bar |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210004954.0A CN103192985B (en) | 2012-01-10 | 2012-01-10 | Aircraft Novel integral structure pull bar |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103192985A true CN103192985A (en) | 2013-07-10 |
| CN103192985B CN103192985B (en) | 2016-01-06 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210004954.0A Active CN103192985B (en) | 2012-01-10 | 2012-01-10 | Aircraft Novel integral structure pull bar |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103192985B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112170773A (en) * | 2020-08-25 | 2021-01-05 | 福建龙溪轴承(集团)股份有限公司 | Light alloy non-revolving body special-shaped integral pull rod precision forging near-net forming technology |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4248062A (en) * | 1979-10-05 | 1981-02-03 | Shakespeare Company | Drive shaft assembly and method for making same |
| US4275122A (en) * | 1978-07-17 | 1981-06-23 | Gkn Transmissions Limited | Shaft and universal joint member assembly |
| US4469730A (en) * | 1982-12-30 | 1984-09-04 | The Boeing Company | Composite base structure and end fitting joint and method |
| US6350204B1 (en) * | 1999-05-11 | 2002-02-26 | Kabushiki Kaisha Toyoda Jidoshokki Seisakusho | Fiber-reinforced plastic pipe |
| CN1672827A (en) * | 2004-03-22 | 2005-09-28 | 乔治·A·米切尔公司 | Method for producing metal ball bar |
| CN101733935A (en) * | 2008-11-18 | 2010-06-16 | 马尼托沃克起重机集团（法国）公司 | Force transmitting assembly for fiber composite tie rod |
| WO2011116967A1 (en) * | 2010-03-26 | 2011-09-29 | Messier-Bugatti-Dowty | Method for producing a mechanical member from composite material, having an improved mechanical performance under traction-compression and bending |
| CN102581211A (en) * | 2012-02-02 | 2012-07-18 | 哈尔滨飞机工业集团有限责任公司 | Cold forming method for integral aluminum alloy pull rod of aircraft |
-
2012
- 2012-01-10 CN CN201210004954.0A patent/CN103192985B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4275122A (en) * | 1978-07-17 | 1981-06-23 | Gkn Transmissions Limited | Shaft and universal joint member assembly |
| US4248062A (en) * | 1979-10-05 | 1981-02-03 | Shakespeare Company | Drive shaft assembly and method for making same |
| US4469730A (en) * | 1982-12-30 | 1984-09-04 | The Boeing Company | Composite base structure and end fitting joint and method |
| US6350204B1 (en) * | 1999-05-11 | 2002-02-26 | Kabushiki Kaisha Toyoda Jidoshokki Seisakusho | Fiber-reinforced plastic pipe |
| CN1672827A (en) * | 2004-03-22 | 2005-09-28 | 乔治·A·米切尔公司 | Method for producing metal ball bar |
| CN101733935A (en) * | 2008-11-18 | 2010-06-16 | 马尼托沃克起重机集团（法国）公司 | Force transmitting assembly for fiber composite tie rod |
| WO2011116967A1 (en) * | 2010-03-26 | 2011-09-29 | Messier-Bugatti-Dowty | Method for producing a mechanical member from composite material, having an improved mechanical performance under traction-compression and bending |
| CN102581211A (en) * | 2012-02-02 | 2012-07-18 | 哈尔滨飞机工业集团有限责任公司 | Cold forming method for integral aluminum alloy pull rod of aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 史超礼: "《航空概论》", 31 July 1978, 国防工业出版社 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112170773A (en) * | 2020-08-25 | 2021-01-05 | 福建龙溪轴承(集团)股份有限公司 | Light alloy non-revolving body special-shaped integral pull rod precision forging near-net forming technology |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103192985B (en) | 2016-01-06 |
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| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Sun Jingwen Inventor after: Zhu Wei Inventor after: Chen Yalin Inventor before: Zhu Wei Inventor before: Chen Yalin |
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Free format text: CORRECT: INVENTOR; FROM: ZHU WEI CHEN YALIN TO: SUN JINGWEN ZHU WEI CHEN YALIN |
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