CN103863549A - Body supporting assembly for four-axis unmanned aircraft - Google Patents
Body supporting assembly for four-axis unmanned aircraft Download PDFInfo
- Publication number
- CN103863549A CN103863549A CN201410115070.1A CN201410115070A CN103863549A CN 103863549 A CN103863549 A CN 103863549A CN 201410115070 A CN201410115070 A CN 201410115070A CN 103863549 A CN103863549 A CN 103863549A
- Authority
- CN
- China
- Prior art keywords
- cantilever
- equipment compartment
- anchor ear
- unmanned vehicle
- fuselage
- 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.)
- Granted
Links
Images
Abstract
The invention discloses a body supporting assembly for a four-axis unmanned aircraft. Two positioning frames (17) parallel to each other are arranged at the position, close to an equipment bin (13), inside each cantilever (14); a bottom plate (18) is inserted and fixed into the two positioning frames (17); an electronic speed regulator (19) is arranged on each bottom plate (18); a landing gear (1) comprises a left bottom tube (3) and a right bottom tube (3) which are parallel to each other; supporting tubes (4) are welded at the front and rear parts of each bottom tube (3); a supporting plate (5) is fixed at the top of each supporting tube (4) and is fixedly supported at the position, close to the root, of the bottom surface of the corresponding cantilever (14). The body supporting assembly is simple in structure, convenient and quick to assemble and disassemble, excellent in firmness and high in stability. By arranging the electronic speed regulators inside the cantilevers, the spaces of the cantilevers are fully utilized, and the electronic speed regulators are quite convenient and quick to assemble and disassemble.
Description
Technical field
The invention belongs to agricultural vehicle technology field, specifically, the particularly fuselage support assembly of four-axle aircraft.
Background technology
Along with social development, the progress of science and technology, the work such as spray insecticide on a large scale in farmland, fertilising are progressively completed by unmanned vehicle.The alighting gear of existing four axle unmanned vehicles is supported on fuselage equipment compartment bottom by four fast replacing devices, and these four fast replacing device complex structures, cost are high, and the location comparison of four fast replacing devices concentrates, and can cause supporting the less stable of fuselage.Moreover, the contact surface of four fast replacing devices and fuselage is less, and the fixing being connected with fuselage is not good enough.In addition, electronic governor is generally arranged in equipment compartment, and this kind of arrangement not only greatly takies equipment compartment space, affects the layout of other parts in equipment compartment; And very inconvenience of dismounting, in-use performance does not ensure.
Summary of the invention
Technical matters to be solved by this invention is to provide four axle unmanned vehicle fuselage support assemblies of fixing and good stability.
Technical scheme of the present invention is as follows: a kind of four axle unmanned vehicle fuselage support assemblies, there is fuselage (2) and alighting gear (1), fuselage (2) is positioned at the top of alighting gear (1), described fuselage (2) is by equipment compartment (13), cantilever (14) and motor bin (15) form, described equipment compartment (13) is positioned at midway location, be provided with four cantilevers (14) that distribute by even circumferential in the periphery of equipment compartment (13), the axial line of the axial line of this cantilever (14) and equipment compartment (13) is perpendicular, the ring wall of the inner of described cantilever (14) and equipment compartment (13) is connected as a single entity, be provided with motor bin (15) in the outer end of each cantilever (14), the axis parallel of the axial line of described motor bin (15) and equipment compartment (13), in the inner position near equipment compartment (13) of each described cantilever (14), two postings that are parallel to each other (17) are all installed, in these two postings (17), intert and be fixed with a base plate (18), electronic governor (19) is installed on this base plate (18), electronic governor (19) is positioned between two postings (17) of same cantilever (14), described alighting gear (1) comprises two bottom tubes that are parallel to each other in left and right (3), all be welded with support tube (4) in the front and rear part of every foundation pipe (3), and the top of every support tube (4) is all fixed with supporting plate (5), four blocks of supporting plates (5) are positioned in same level, and by the rectangular distribution, and four blocks of supporting plates (5) are corresponding one by one with four cantilevers (14), every block of supporting plate (5) is fixedly supported on the position of cantilever (14) bottom surface near root.
Fuselage of the present invention is moulded attractive in appearance, and height dimension is little, and inner space is large, the parts such as autopilot can be installed in equipment compartment, and can distinguish mounted motor in four motor bins.The present invention supports aircraft fuselage by four blocks of supporting plates on alighting gear, simple in structure, and dismounting is not only convenient but also quick; Supporting plate is supported on the position of cantilever near root in the mode of lifting, and the fixing being connected with fuselage is on the one hand good, on the other hand, can effectively improve the stability that supports fuselage.Meanwhile, the present invention saves out equipment compartment bottom space, can, by the dilatation downwards of equipment compartment bottom, with integrated medicine-chest, thereby take full advantage of space, has reduced the height dimension of whole aircraft, has reduced the volume of aircraft.In addition, electronic governor is arranged on cantilever inside by the present invention, and the supporting construction being made up of posting and base plate is accurately located, can guarantee the steadiness that electronic governor is supported, loosening to prevent that electronic governor from occurring, take full advantage of so on the one hand the space of cantilever, do not affect the layout of other parts on agricultural unmanned vehicle; On the other hand, the dismounting of electronic governor is very convenient.
In order to strengthen structural strength and the steadiness of alighting gear, be positioned at left and right directions with being connected with transverse tube (6) between two support tubes (4) on one side, be positioned between two support tubes (4) of fore-and-aft direction the same side and be connected with longitudinal tubule (L tubule) (7).
Described motor bin (15) is the tubular structure of the uncovered lower end closed in upper end.Above structure can facilitate motor assembling and power output; The upper end of motor bin is uncovered, is conducive to distribute the heat producing in machine operation process, to guarantee the in-use performance of motor.
Be symmetrically arranged with medicine bar (16) in the left and right sides of alighting gear (1), the middle part of the every longitudinal tubule (L tubule) (7) on alighting gear (1) is all welded with two hangers (8), between two hangers (8), be provided with the first anchor ear (9), between described the first anchor ear (9) and two hangers (8), be bolted, and the first anchor ear (9) is held the inner pipe shaft of respective side medicine bar (16) tightly.Medicine bar is arranged on to the left and right sides of alighting gear, and medicine bar is arranged on the pipe shaft of alighting gear respective side longitudinal tubule (L tubule) by anchor ear, this setting is not only simple in structure, and medicine bar easy accessibility, and fixing is better; Meanwhile, medicine bar does not contact with fuselage, can not cause the damage to medicine-chest, can protect preferably medicine-chest structure.
The front and back side of every described medicine bar (16) is all symmetrically arranged with hound (10), the outer end of these two hounds (10) connects with corresponding medicine bar (16) by same the second anchor ear (11), the second anchor ear (11) is held the position near outer end at medicine bar (16) tightly, the inner of described hound (10) is connected with the support tube (4) of respective side by the 3rd anchor ear (12), and the 3rd anchor ear (12) is held the position in support tube (4) lower end tightly.Hound installation is convenient, solid and reliable on the one hand for above structure; On the other hand, two hounds support the position of medicine bar near outer end jointly, can further strengthen the fixing of medicine bar, prevent that medicine bar from shaking in aircraft operation process or become flexible.
In order to reduce production costs, be convenient to processing and fabricating, described supporting plate (5) is rectangular flat structure, and supporting plate (5) fits with cantilever (14) bottom surface, and is bolted.
Described posting (17) is elliptical annular sheet body structure, and is made up of aviation laminate, and the thickness of posting (17) is 2-4mm.Posting adopts above structure, is combined closely with cantilever, and it is firm to connect; Posting is made by aviation laminate, intensity high, not yielding or damage; And angle of bend is little, aseismicity is good
Beneficial effect: the present invention supports four cantilevers of fuselage by four blocks of supporting plates on alighting gear, not only simple in structure, easy accessibility, quick, and there is good fixing and stability.Electronic governor is arranged on cantilever inside by the present invention, takes full advantage of so on the one hand the space of cantilever, do not affect the layout of other parts on agricultural unmanned vehicle; On the other hand, the dismounting of electronic governor is very convenient.
Accompanying drawing explanation
Fig. 1 is the birds-eye view of the present invention together with fuselage.
Fig. 2 is the upward view that Fig. 1 removes fuselage.
Fig. 3 is the side-looking enlarged drawing that Fig. 2 removes medicine bar and hound.
Fig. 4 is the scheme of installation of electronic governor.
The specific embodiment
Below in conjunction with drawings and Examples, the invention will be further described:
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the present invention includes fuselage 2 and alighting gear 1 two large divisions, fuselage 2 is positioned at the top of alighting gear 1.Described fuselage 2 is made up of equipment compartment 13, cantilever 14 and motor bin 15, described equipment compartment 13 is positioned at midway location, these equipment compartment 13 uncovered lower end closed in upper end, are provided with four cantilevers 14 that distribute by even circumferential in the periphery of equipment compartment 13, the outer end of each cantilever 14 is provided with motor bin 15.Described cantilever 14 is hollow structure, and its cross section reduces to the direction of motor bin 15 gradually from equipment compartment 13, and the axial line of the axial line of described cantilever 14 and equipment compartment 13 is perpendicular, and the ring wall of the inner of cantilever 14 and equipment compartment 13 is connected as a single entity.Described motor bin 15 is the tubular structure of the uncovered lower end closed in upper end, and the axis parallel of the axial line of motor bin 15 and equipment compartment 13, the outer wall of motor bin 15 is connected with cantilever 14 one, and the inside of motor bin 15 is communicated with the inner chamber of equipment compartment 13 by the endoporus of cantilever 14.
As Figure 1 and Figure 4, in the inner position near equipment compartment 13 of each described cantilever 14, two postings that are parallel to each other 17 are all installed, described posting 17 is elliptical annular sheet body structure, and the inwall of the external annulus of posting 17 and cantilever 14 fits, and by being adhesively fixed.Described posting 17 is made up of aviation laminate, and the thickness of posting 17 is 2-4mm.Interior interting of two postings 17 in same cantilever 14 is fixed with a base plate 18, and base plate 18 is positioned on horizontal surface, and has gap between base plate 18 and the interior diapire of cantilever 14.Described base plate 18 is made up of aviation laminate, and on this base plate 18, electronic governor 19 is installed, between two postings 17 of electronic governor 19 in same cantilever 14.
As shown in Figure 1, Figure 2, Figure 3 shows, alighting gear 1 is made up of bottom tube 3, support tube 4, supporting plate 5, transverse tube 6 and longitudinal tubule (L tubule) 7 etc.Wherein, bottom tube 3 has two, these two foundation pipe, 3 left and right are arranged in parallel, be provided with support tube 4 in the front and rear part of every foundation pipe 3, the lower end of each support tube 4 is welded on corresponding bottom tube 3, the top of four support tubes 4 is all welded with supporting plate 5, this supporting plate 5 is rectangular flat structure, four blocks of supporting plates 5 are positioned in same level, and by the rectangular distribution, and four blocks of supporting plates 5 are corresponding one by one with four cantilevers 14, every supporting plate 5 laminatings are supported on the position of cantilever 14 bottom surfaces near root, and be bolted with cantilever, described alighting gear 1 is connected with fuselage 2 by these four blocks of supporting plates 5.
As shown in Figure 1, Figure 2, Figure 3 shows, between left and right directions is with two support tubes 4 on one side, be welded with transverse tube 6, between two support tubes 4 of fore-and-aft direction the same side, be welded with longitudinal tubule (L tubule) 7, longitudinal tubule (L tubule) 7 and transverse tube 6 are positioned in same level, and this horizontal surface is at the upper position of alighting gear 1.All be welded with between 8, two hangers 8 of two hangers and be provided with the first anchor ear 9 at the middle part of longitudinal tubule (L tubule) every described 7, between described the first anchor ear 9 and two hangers 8, be bolted.Be symmetrical arranged medicine bar 16 in the left and right sides of described alighting gear 1, medicine bar 16 is a little less than longitudinal tubule (L tubule) 7, and medicine bar 16 is perpendicular with longitudinal tubule (L tubule) 7, and the pipe shaft of medicine bar 16 the inners is held tightly by the first anchor ear 9 of respective side.
As shown in Figure 1 and Figure 2, the front and back side of every described medicine bar 16 is all symmetrically arranged with hound 10, hound 10 is high outside and low outside is in tilted layout for this, and the outer end of these two hounds 10 connects with corresponding medicine bar 16 by same the second anchor ear 11, and the second anchor ear 11 is held the position near outer end at medicine bar 16 tightly.The inner of described hound 10 is connected with the support tube 4 of respective side by the 3rd anchor ear 12, and the 3rd anchor ear 12 is held the position in support tube 4 lower ends tightly.
Claims (7)
1. an axle unmanned vehicle fuselage support assembly, there is fuselage (2) and alighting gear (1), fuselage (2) is positioned at the top of alighting gear (1), described fuselage (2) is by equipment compartment (13), cantilever (14) and motor bin (15) form, described equipment compartment (13) is positioned at midway location, be provided with four cantilevers (14) that distribute by even circumferential in the periphery of equipment compartment (13), the axial line of the axial line of this cantilever (14) and equipment compartment (13) is perpendicular, the ring wall of the inner of described cantilever (14) and equipment compartment (13) is connected as a single entity, be provided with motor bin (15) in the outer end of each cantilever (14), the axis parallel of the axial line of described motor bin (15) and equipment compartment (13), it is characterized in that: in the inner position near equipment compartment (13) of each described cantilever (14), two postings that are parallel to each other (17) are all installed, in these two postings (17), intert and be fixed with a base plate (18), electronic governor (19) is installed on this base plate (18), electronic governor (19) is positioned between two postings (17) of same cantilever (14), described alighting gear (1) comprises two bottom tubes that are parallel to each other in left and right (3), all be welded with support tube (4) in the front and rear part of every foundation pipe (3), and the top of every support tube (4) is all fixed with supporting plate (5), four blocks of supporting plates (5) are positioned in same level, and by the rectangular distribution, and four blocks of supporting plates (5) are corresponding one by one with four cantilevers (14), every block of supporting plate (5) is fixedly supported on the position of cantilever (14) bottom surface near root.
2. four axle unmanned vehicle fuselage support assemblies according to claim 1, it is characterized in that: be positioned at left and right directions with being connected with transverse tube (6) between two support tubes (4) on one side, be positioned between two support tubes (4) of fore-and-aft direction the same side and be connected with longitudinal tubule (L tubule) (7).
3. four axle unmanned vehicle fuselage support assemblies according to claim 1, is characterized in that: the tubular structure that described motor bin (15) is the uncovered lower end closed in upper end.
4. four axle unmanned vehicle fuselage support assemblies according to claim 2, it is characterized in that: be symmetrically arranged with medicine bar (16) in the left and right sides of alighting gear (1), the middle part of the every longitudinal tubule (L tubule) (7) on alighting gear (1) is all welded with two hangers (8), between two hangers (8), be provided with the first anchor ear (9), between described the first anchor ear (9) and two hangers (8), be bolted, and the first anchor ear (9) is held the inner pipe shaft of respective side medicine bar (16) tightly.
5. four axle unmanned vehicle fuselage support assemblies according to claim 4, it is characterized in that: the front and back side of every described medicine bar (16) is all symmetrically arranged with hound (10), the outer end of these two hounds (10) connects with corresponding medicine bar (16) by same the second anchor ear (11), the second anchor ear (11) is held the position near outer end at medicine bar (16) tightly, the inner of described hound (10) is connected with the support tube (4) of respective side by the 3rd anchor ear (12), and the 3rd anchor ear (12) is held the position in support tube (4) lower end tightly.
6. according to the arbitrary four described axle unmanned vehicle fuselage support assemblies of claim 1 to 5, it is characterized in that: described supporting plate (5) is rectangular flat structure, and supporting plate (5) and cantilever (14) bottom surface fit, and are bolted.
7. four axle unmanned vehicle fuselage support assemblies according to claim 1, is characterized in that: described posting (17) is elliptical annular sheet body structure, and is made up of aviation laminate, and the thickness of posting (17) is 2-4mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410115070.1A CN103863549B (en) | 2014-03-26 | 2014-03-26 | A kind of four axle unmanned vehicle supporting fuselage assemblies |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410115070.1A CN103863549B (en) | 2014-03-26 | 2014-03-26 | A kind of four axle unmanned vehicle supporting fuselage assemblies |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103863549A true CN103863549A (en) | 2014-06-18 |
| CN103863549B CN103863549B (en) | 2016-08-24 |
Family
ID=50902690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410115070.1A Expired - Fee Related CN103863549B (en) | 2014-03-26 | 2014-03-26 | A kind of four axle unmanned vehicle supporting fuselage assemblies |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103863549B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104663099A (en) * | 2015-01-22 | 2015-06-03 | 湖南金骏农业科技有限公司 | Fertilizer apparatus and plant protection airplane including same |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009269493A (en) * | 2008-05-08 | 2009-11-19 | Yamaha Motor Co Ltd | Unmanned helicopter |
| CN101973393A (en) * | 2010-09-30 | 2011-02-16 | 清华大学 | High-strength cage-type undercarriage of unmanned helicopter |
| CN202554937U (en) * | 2012-05-20 | 2012-11-28 | 浙江海洋学院 | Small-sized aerial photography flying vehicle |
| CN202807093U (en) * | 2012-09-14 | 2013-03-20 | 马永政 | Sledge-wheel-combined-type middle-and-small-sized unmanned aerial vehicle undercarriage system |
| CN202966662U (en) * | 2012-10-09 | 2013-06-05 | 长沙秀丰农业科技有限公司 | Unmanned helicopter for spraying pesticides |
| CN203222114U (en) * | 2013-04-03 | 2013-10-02 | 无锡汉和航空技术有限公司 | Electric small-sized unmanned helicopter for spraying pesticide |
| CN203461102U (en) * | 2013-09-13 | 2014-03-05 | 重庆金泰航空工业有限公司 | Undercarriage installation structure of agricultural unmanned aerial vehicle |
| CN203486144U (en) * | 2013-09-25 | 2014-03-19 | 重庆金泰航空工业有限公司 | Farm-oriented unmanned aerial vehicle |
| CN203793611U (en) * | 2014-03-26 | 2014-08-27 | 重庆金泰航空工业有限公司 | Fuselage support assembly for four-axis unmanned aerial vehicle |
-
2014
- 2014-03-26 CN CN201410115070.1A patent/CN103863549B/en not_active Expired - Fee Related
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2009269493A (en) * | 2008-05-08 | 2009-11-19 | Yamaha Motor Co Ltd | Unmanned helicopter |
| CN101973393A (en) * | 2010-09-30 | 2011-02-16 | 清华大学 | High-strength cage-type undercarriage of unmanned helicopter |
| CN202554937U (en) * | 2012-05-20 | 2012-11-28 | 浙江海洋学院 | Small-sized aerial photography flying vehicle |
| CN202807093U (en) * | 2012-09-14 | 2013-03-20 | 马永政 | Sledge-wheel-combined-type middle-and-small-sized unmanned aerial vehicle undercarriage system |
| CN202966662U (en) * | 2012-10-09 | 2013-06-05 | 长沙秀丰农业科技有限公司 | Unmanned helicopter for spraying pesticides |
| CN203222114U (en) * | 2013-04-03 | 2013-10-02 | 无锡汉和航空技术有限公司 | Electric small-sized unmanned helicopter for spraying pesticide |
| CN203461102U (en) * | 2013-09-13 | 2014-03-05 | 重庆金泰航空工业有限公司 | Undercarriage installation structure of agricultural unmanned aerial vehicle |
| CN203486144U (en) * | 2013-09-25 | 2014-03-19 | 重庆金泰航空工业有限公司 | Farm-oriented unmanned aerial vehicle |
| CN203793611U (en) * | 2014-03-26 | 2014-08-27 | 重庆金泰航空工业有限公司 | Fuselage support assembly for four-axis unmanned aerial vehicle |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104663099A (en) * | 2015-01-22 | 2015-06-03 | 湖南金骏农业科技有限公司 | Fertilizer apparatus and plant protection airplane including same |
| CN104663099B (en) * | 2015-01-22 | 2017-01-18 | 湖南金骏农业科技有限公司 | Fertilizer apparatus and plant protection airplane including same |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103863549B (en) | 2016-08-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203793588U (en) | Agricultural aircraft machine body assembly | |
| CN103482068A (en) | Liquid pesticide spraying system and machine body combination of four-shaft agricultural unmanned aerial vehicle | |
| CN202657241U (en) | Unmanned helicopter fuselage frame | |
| CN203793611U (en) | Fuselage support assembly for four-axis unmanned aerial vehicle | |
| CN103863549A (en) | Body supporting assembly for four-axis unmanned aircraft | |
| CN203793645U (en) | Body supporting structure of four-axis aircraft | |
| CN201525399U (en) | Vehicle frame chassis capable of being widened | |
| CN103863552A (en) | Four-shaft type flight device body assembly | |
| CN103863548A (en) | Assembly of top cover and body of four-shaft type flight device | |
| CN203793607U (en) | Arrangement structure of electronic speed regulator of agricultural unmanned aerial vehicle | |
| CN103143972A (en) | Large-span framework-type turnover clamp | |
| CN103863551B (en) | A kind of agricultural aircraft body assembly | |
| CN203583665U (en) | Novel hinged support | |
| CN206841733U (en) | A kind of three axial six degree of freedom docking facilities | |
| CN203793608U (en) | Supporting device for electronic speed regulators of agricultural unmanned aerial vehicle | |
| CN203793647U (en) | Arrangement structure for electronic speed regulators of agricultural aircraft | |
| CN203461088U (en) | Four-shaft farm-oriented unmanned aircraft fuselage positioning structure | |
| CN203793652U (en) | Electronic governor positioning frame of agricultural unmanned aircraft | |
| CN204603632U (en) | Electro-tricycle frame welding tooling | |
| CN203793598U (en) | Agricultural unmanned aircraft body assembly | |
| CN203793616U (en) | Body assembly on four-axis aerial vehicle | |
| CN203793590U (en) | Integrated body of four-axis aircraft | |
| CN203793591U (en) | Integrated type fuselage of four-axle type flying device | |
| CN205168188U (en) | Transmission shaft installing support structure | |
| CN204047067U (en) | The horizontal mounting structure of Miniature cultivator used on higher screw drive case |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160824 Termination date: 20180326 |