CN103935523A - Multi-shaft aircraft arm installing structure - Google Patents
Multi-shaft aircraft arm installing structure Download PDFInfo
- Publication number
- CN103935523A CN103935523A CN201410195030.2A CN201410195030A CN103935523A CN 103935523 A CN103935523 A CN 103935523A CN 201410195030 A CN201410195030 A CN 201410195030A CN 103935523 A CN103935523 A CN 103935523A
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- China
- Prior art keywords
- aircraft
- upper plate
- horn
- fuselage
- lower plate
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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
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Abstract
The invention relates to a multi-shaft aircraft arm installing structure. The multi-shaft aircraft arm installing structure is characterized by being provided with an aircraft body upper plate, an aircraft body lower plate, an arm connecting part arranged between the aircraft body upper plate and the aircraft body lower plate and close the peripheries of the aircraft body upper plate and the aircraft body lower plate, and an elastic clamp piece located on the periphery of the aircraft body upper plate, integrally manufactured with the aircraft body upper plate and capable of being in clamped connection with an aircraft arm so as to avoid pin shaft rotation around the aircraft arm, wherein the aircraft body upper plate and the aircraft body lower plate are arranged in parallel. A main aircraft frame structure is simplified, the weight of the main aircraft frame structure is decreased, and the production efficiency and the product quality of an aircraft can be improved. In addition, the aircraft arm in the multi-shaft aircraft arm installing structure can be bent, and storage and usage of the aircraft are facilitated.
Description
Technical field
The invention belongs to vehicle technology field, particularly relate to a kind of Multi-axis aircraft horn mounting structure.
Background technology
Multi-axis aircraft have cost low, easy to operate, have high degree of flexibility and can hedgehopping etc. feature, can utilize its photographic equipment carrying to carry out picture photographing, obtain image data, and obtained image data sent back to ground.The fields such as Multi-axis aircraft has been widely used at present and has taken photo by plane, electric power line walking, aerial reconnaissance, simulated flight, subsidy unmanned plane, in order to the observation of monitoring evidence obtaining and specific position etc., can realize the transmission of implementing live video picture, for director, carrying out decision-making and judgement, is a kind of important tool of obtaining information.In addition, the Multi-axis aircraft of easy structure is also received widely and is liked in toy field.
Horn is for the parts of aircraft motor are installed, in prior art, it is to be screwed or to process separately new parts in order to fixing horn that horn is arranged on mode on aircraft fuselage, this structure is not only complicated, increase aircraft weight cost, and aircraft volume is larger, deposit and use inconvenience.
Summary of the invention
The present invention for solve the aircraft horn mounting structure existing in known technology complicated, use the technical matterss such as inconvenience provide a kind of simple in structure, can alleviate aircraft own wt, can lead aircraft volume to dwindle so that the Multi-axis aircraft horn mounting structure that aircraft is deposited and used.
The technical scheme that the present invention takes for the technical matters existing in solution known technology is: a kind of Multi-axis aircraft horn mounting structure, is characterized in that: have the fuselage upper plate and the fuselage lower plate that are arranged in parallel; Be located at the horn attaching parts that fuselage upper plate between fuselage upper plate and fuselage lower plate, close and fuselage lower plate periphery arrange; One end is hinged on the horn of described horn attaching parts bottom by the axis bearing pin parallel with fuselage lower plate with fuselage upper plate; Be positioned at fuselage upper plate periphery, with fuselage upper plate Construction integration, can with the elastic card of described horn clamping to avoid horn to rotate around described bearing pin.
The present invention can also adopt following technical measures:
Described elastic card is formed by two that are located at described fuselage upper plate periphery symmetrical open-minded seams; Described elastic card is provided with draw-in groove, on described horn one end top corresponding with described elastic card be provided with can with the fixture block of described draw-in groove clamping.
Described fuselage upper plate and fuselage lower plate are circular carbon plate.
Advantage and good effect that the present invention has are: because the present invention adopts as above technical scheme, design a kind of new horn mounting structure, this structure middle machine body consists of fuselage upper plate and fuselage lower plate, simplify the main framed structure of aircraft, alleviate aircraft body framework weight, can improve production efficiency and the product design of aircraft.In addition, the horn in the present invention can bend, and has facilitated depositing and using of aircraft.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention;
In figure: 1, fuselage upper plate; 1-1, elastic card; 1-2, draw-in groove; 2, fuselage lower plate; 3, horn attaching parts; 4, horn; 5, bearing pin.
The specific embodiment
For further understanding summary of the invention of the present invention, Characteristic, hereby exemplify following examples, and coordinate accompanying drawing to be described in detail as follows:
Refer to Fig. 1, a kind of Multi-axis aircraft horn mounting structure, is characterized in that: have fuselage upper plate 1 and fuselage lower plate 2, fuselage upper plate 1 and fuselage lower plate 2 are carbon plate lightweight, good toughness, and fuselage upper plate 1 and fuselage lower plate 2 are muscle shape grillage structure.Fuselage upper plate 1 and fuselage lower plate 2 are arranged in parallel.Between fuselage upper plate 1 and fuselage lower plate 2, be provided with horn attaching parts 3, horn attaching parts 3 is near fuselage upper plate 1 and the 2 periphery settings of fuselage lower plate.Horn attaching parts 3 connects horn 4, and one end of horn 4 is hinged on described horn attaching parts 3 bottoms by the axis bearing pin 5 parallel with fuselage lower plate 2 with fuselage upper plate 1, and horn 4, around bearing pin 5 rotations, can be realized the downward bending of horn 4.The periphery that is positioned at fuselage upper plate 1 is provided with the elastic card 1-1 with fuselage upper plate 1 Construction integration, and elastic card 1-1 can be with described horn 4 clampings to avoid horn 4 to rotate around described bearing pin 5.The effect that is elastic card 1-1 is to prevent horn 4 bendings.In the present embodiment, elastic card 1-1 is formed by two that are located at described fuselage upper plate 1 periphery symmetrical open-minded seams.Elastic card 1-1 is provided with draw-in groove 1-2, the top, end that described horn 4 is corresponding with described elastic card 1-1 be provided with can with the fixture block of described draw-in groove 1-2 clamping, when fixture block and draw-in groove 1-2 clamping, horn 4 is fixed cannot bending.
Except said structure, elastic card 1-1 can be also the part of being located at fuselage upper plate 1 periphery and protruding fuselage upper plate 1 periphery.
Structure of the present invention takes full advantage of the performance of material itself, method by machine up reaches horn and clamps fixing effect, use and installing/dismounting in saved the time, saved the step of redundancy, alleviate weight, improved accordingly work efficiency.And aggregated(particle) structure makes horn fold, easy to use.
Claims (3)
1. a Multi-axis aircraft horn mounting structure, is characterized in that: have
The fuselage upper plate (1) being arranged in parallel and fuselage lower plate (2);
Be located at horn attaching parts (3) between fuselage upper plate (1) and fuselage lower plate (2), that arrange near fuselage upper plate (1) and fuselage lower plate (2) periphery;
One end is hinged on the horn (4) of described horn attaching parts (3) bottom by the axis bearing pin (5) parallel with fuselage lower plate (2) with fuselage upper plate (1);
Be positioned at fuselage upper plate (1) periphery, with fuselage upper plate (1) Construction integration, can with the elastic card (1-1) of described horn (4) clamping to avoid horn (4) to rotate around described bearing pin (1).
2. Multi-axis aircraft horn mounting structure according to claim 1, is characterized in that: described elastic card (1-1) is formed by two symmetrical open-minded seams being located at described fuselage upper plate (1) periphery; Described elastic card (1-1) is provided with draw-in groove (1-2), the upper one end top corresponding with described elastic card (1-1) of described horn (4) be provided with can with the fixture block of described draw-in groove (1-2) clamping.
3. Multi-axis aircraft horn mounting structure according to claim 1, is characterized in that: described fuselage upper plate (1) and fuselage lower plate (1-2) are circular carbon plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410195030.2A CN103935523A (en) | 2014-05-09 | 2014-05-09 | Multi-shaft aircraft arm installing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410195030.2A CN103935523A (en) | 2014-05-09 | 2014-05-09 | Multi-shaft aircraft arm installing structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103935523A true CN103935523A (en) | 2014-07-23 |
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ID=51183468
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410195030.2A Pending CN103935523A (en) | 2014-05-09 | 2014-05-09 | Multi-shaft aircraft arm installing structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN103935523A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105857601A (en) * | 2016-03-30 | 2016-08-17 | 三翼航空科技南通有限公司 | Arm connecting device for unmanned aerial vehicle |
| CN106314784A (en) * | 2015-11-05 | 2017-01-11 | 曹萍 | Non-planar four-arm eight-rotor aircraft |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202666406U (en) * | 2012-06-06 | 2013-01-16 | 张锦海 | Six-arm model airplane spiral rack |
| CN202666405U (en) * | 2012-06-06 | 2013-01-16 | 张锦海 | Four-arm model airplane spiral rack |
| CN202666408U (en) * | 2012-07-20 | 2013-01-16 | 张锦海 | Six-arm model aerial propeller |
| CN202896870U (en) * | 2012-11-08 | 2013-04-24 | 广州金海航空技术有限公司 | High-strength machine body framework of aircraft |
| CN203043551U (en) * | 2013-01-14 | 2013-07-10 | 张锦海 | Central spiral frame of model airplane |
| CN203043552U (en) * | 2013-01-14 | 2013-07-10 | 张锦海 | Mechanical arm of model airplane central spiral frame |
| CN203461110U (en) * | 2013-09-10 | 2014-03-05 | 姜学海 | Irregularly-folded three-point landing type multi-axis unmanned aerial vehicle |
| CN203921204U (en) * | 2014-05-09 | 2014-11-05 | 天津天恒智远科技有限公司 | Multi-axis aircraft horn mounting structure |
-
2014
- 2014-05-09 CN CN201410195030.2A patent/CN103935523A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN202666406U (en) * | 2012-06-06 | 2013-01-16 | 张锦海 | Six-arm model airplane spiral rack |
| CN202666405U (en) * | 2012-06-06 | 2013-01-16 | 张锦海 | Four-arm model airplane spiral rack |
| CN202666408U (en) * | 2012-07-20 | 2013-01-16 | 张锦海 | Six-arm model aerial propeller |
| CN202896870U (en) * | 2012-11-08 | 2013-04-24 | 广州金海航空技术有限公司 | High-strength machine body framework of aircraft |
| CN203043551U (en) * | 2013-01-14 | 2013-07-10 | 张锦海 | Central spiral frame of model airplane |
| CN203043552U (en) * | 2013-01-14 | 2013-07-10 | 张锦海 | Mechanical arm of model airplane central spiral frame |
| CN203461110U (en) * | 2013-09-10 | 2014-03-05 | 姜学海 | Irregularly-folded three-point landing type multi-axis unmanned aerial vehicle |
| CN203921204U (en) * | 2014-05-09 | 2014-11-05 | 天津天恒智远科技有限公司 | Multi-axis aircraft horn mounting structure |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106314784A (en) * | 2015-11-05 | 2017-01-11 | 曹萍 | Non-planar four-arm eight-rotor aircraft |
| CN105857601A (en) * | 2016-03-30 | 2016-08-17 | 三翼航空科技南通有限公司 | Arm connecting device for unmanned aerial vehicle |
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Owner name: TIANJIN TIANHENG ZHIYUAN TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: TIANJIN CLOUDY FRIENDS TECHNOLOGY CO., LTD. Effective date: 20140903 |
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Free format text: CORRECT: ADDRESS; FROM: 300381 XIQING, TIANJIN TO: 300350 JINNAN, TIANJIN |
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Effective date of registration: 20140903 Address after: 300350 Tianjin City East Shuanggang Development Zone Jinnan U 2-2-1102 headquarters in Grand Valley Applicant after: TIANJIN TIANHENG ZHIYUAN TECHNOLOGY CO., LTD. Address before: 300381 Tianjin city Xiqing District Ling Bin Road extension line of Lingao Creative Industry Park 5-3-310-7 Applicant before: TIANJIN YUNYOU TECHNOLOGY CO., LTD. |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140723 |