CN204937456U - The coupling mechanism that a kind of unmanned plane combinationally uses - Google Patents
The coupling mechanism that a kind of unmanned plane combinationally uses Download PDFInfo
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- CN204937456U CN204937456U CN201520606894.9U CN201520606894U CN204937456U CN 204937456 U CN204937456 U CN 204937456U CN 201520606894 U CN201520606894 U CN 201520606894U CN 204937456 U CN204937456 U CN 204937456U
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Abstract
The coupling mechanism that a kind of unmanned plane combinationally uses, relate to technical field of aircraft structure design, for the connection between two unmanned planes, cover cone, addendum cone are individually fixed on the wingtip of different unmanned plane wing, the nose shape of tail shape and the addendum cone of cover cone agrees with, and is bored and coordinate the parallel combination assembled and realize unmanned plane between addendum cone by the cover on different aircraft.The first lockout mechanism on cover cone comprises knock hole, the first linear plain bearing group is arranged with in parallel in knock hole, on cover cone, the bottom position of knock hole is provided with spring kayser, spring kayser is the unitized construction of rigid sleeve and spring, and Spring Card is locked and is covered with the first magnet coil, spring kayser bottom is fixed on described cover cone.The coupling mechanism that the unmanned plane that the utility model provides combinationally uses can realize meeting with the Fast Installation of aircaft configuration and dismounting unmanned plane and dock operating needs Spring Card lockset in the air and have and insert easily, locking failure-free feature.
Description
Technical field
The utility model relates to technical field of aircraft structure design, in particular to the coupling mechanism that a kind of unmanned plane combinationally uses.
Background technology
Unmanned plane is combined and spliced is a kind of unmanned plane application mode of new ideas.Unmanned plane is used can effectively be improved its pneumatic efficiency by reasonable combination, realizes aerial electric energy and information sharing.Odysseus (Odysseus) the solar power unmanned plane of U.S.'s aurora flight science company designs, by combinationally using, is adjusted to " Z " font, by day with absorption solar power as much as possible." one " font is kept, to improve flight pneumatic efficiency at night.In addition, the unmanned plane of single task module, by combinationally using, possesses system relationship, has complementary functions, the ability of information mutual communication.
Though combinationally using of unmanned plane has a lot of advantage, the design of coupling mechanism is a difficult point.First, during the aerial asymptotic docking of unmanned plane, affect comparatively large by wing tip rough air, docking difficulty is large, and coupling mechanism design simply should be suitable for and is easy to docking and is separated.Secondly, coupling mechanism belongs to force transmission mechanism, should have the ability of bending resistance, antitorque and tension.Finally, coupling mechanism should have high reliability.Not yet find the coupling mechanism meeting this kind of unmanned plane combination and require at present.The technical matters needing now solution badly how to design a kind of structure, and this structure can be used in the connection of unmanned plane, the docking being easy to unmanned plane be separated.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, provide a kind of simple and reasonable, docking of being easy to unmanned plane be separated, connect the coupling mechanism that solid and reliable unmanned plane combinationally uses.
The purpose of this utility model is achieved through the following technical solutions: the coupling mechanism that a kind of unmanned plane combinationally uses, for the parallel combination of unmanned plane, comprise cover cone, addendum cone, wherein, cover cone, addendum cone are individually fixed on the wingtip of the different wing of unmanned plane, the nose shape of tail shape and the addendum cone of cover cone agrees with, and is bored and coordinate the parallel combination assembled and realize unmanned plane between addendum cone by the cover on different aircraft.By the unmanned plane wing of docking arranges connection structure, make unmanned plane connection process more simple, convenient.
In such scheme preferably, the inner side same position of the re-entrant angle of cover terebrantia is provided with the first lockout mechanism, the both sides correspondence position of the salient angle of the head of addendum cone is provided with the second lockout mechanism, and the first lockout mechanism coordinates with the second lockout mechanism to realize overlapping bores and being fixedly connected with of described addendum cone.Connection between unmanned plane is by the cover cone on wing and having coordinated between addendum cone.
In above-mentioned either a program preferably, the first lockout mechanism on cover cone comprises knock hole, the first linear plain bearing group is arranged with in parallel in knock hole, on cover cone, the bottom position of knock hole is provided with spring kayser, spring kayser is the unitized construction of rigid sleeve and spring, and Spring Card is locked and is covered with the first magnet coil, spring kayser bottom is fixed on described cover cone.Traction during by arranging magnet coil and making unmanned plane dock with spring Carcel with clear and definite electromagnetic force realizes the connection of unmanned plane; Spring Carcel, by the cover of docking cone and addendum cone locking, prevents from coming off.
In above-mentioned either a program preferably, the salient angle face of addendum cone is provided with spacing hole, steel pin is provided with in spacing hole, steel pin is the cylindrical structural of head with cap, end has the draw-in groove of annular, steel pin is fixed in described knock hole by draw-in groove and described spring snap fit, is provided with the second linear slide bearing between the hole wall of spacing hole and steel pin.
In above-mentioned either a program preferably, near port position, spacing hole's circumference is provided with the second magnet coil in spacing hole.
In above-mentioned either a program preferably, on addendum cone, the bottom of spacing hole is provided with base, base support steel pin head.
The beneficial effect of the coupling mechanism that unmanned plane provided by the utility model combinationally uses is, adopt modular design, can realize and the Fast Installation of aircaft configuration and dismounting, the mode of conical bush tandem docking possesses the ability of bending resistance, antitorque and tension, meets unmanned plane and docks operating needs in the air; The fixing steel pin of lockout mechanism and spring kayser all adopt electromagnetic force to drive, and are realized the insertion of steel pin by the positive and negative docking of magnet coil electrode and are exited; The linear plain bearing of knock hole wall, has directional tagging, and the friction force that can reduce steel pin insertion and exit; Spring Card lockset has insertion easily, locking failure-free feature.The structure of device entirety is simple, and easily manufactured, device stability is high, safe and reliable.
Accompanying drawing explanation
Fig. 1 is the structural representation of the cover cone of a preferred embodiment of the coupling mechanism combinationally used according to unmanned plane of the present utility model;
Fig. 2 is the structural representation of first lockout mechanism embodiment illustrated in fig. 1 of the coupling mechanism combinationally used according to unmanned plane of the present utility model;
Fig. 3 is the structural representation of the addendum cone embodiment illustrated in fig. 1 of the coupling mechanism combinationally used according to unmanned plane of the present utility model;
Fig. 4 be the coupling mechanism combinationally used according to unmanned plane of the present utility model Fig. 3 shown in the structural representation of the second lockout mechanism of addendum cone;
Fig. 5 is that the addendum cone embodiment illustrated in fig. 1 of the coupling mechanism combinationally used according to unmanned plane of the present utility model bores with cover the structural representation connected;
Fig. 6 is that the addendum cone embodiment illustrated in fig. 1 of the coupling mechanism combinationally used according to unmanned plane of the present utility model bores with cover the structural representation be separated.
Reference numeral:
1-overlaps cone, 2-addendum cone, 101-steel pin, 102-spring kayser, 103-first magnet coil, 104-first linear plain bearing, 105-second magnet coil, 106-second linear slide bearing, 107-base, 108-knock hole.
Detailed description of the invention
In order to understand the coupling mechanism combinationally used according to the unmanned plane of the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to the coupling mechanism that unmanned plane of the present utility model combinationally uses.
As shown in figs 1 to 6, the coupling mechanism that the unmanned plane that the utility model provides combinationally uses, for the parallel combination of unmanned plane, comprise cover cone 1, addendum cone 2, wherein, cover cone 1, addendum cone 2 are individually fixed on the wingtip of the different wing of unmanned plane, and the cover tail shape of cone 1 agrees with the nose shape of addendum cone 2, by the cover on different aircraft bore 1 with coordinate the parallel combination assembled and realize unmanned plane between addendum cone 2.
The inner side same position of re-entrant angle of the afterbody of cover cone 1 is provided with the first lockout mechanism, and the both sides same position of the salient angle of the head of addendum cone 2 is provided with the second lockout mechanism, and the first lockout mechanism coordinates with the second lockout mechanism and realizes overlapping being fixedly connected with of cone 1 and addendum cone 2.The first lockout mechanism on cover cone 1 comprises knock hole 108, the first linear plain bearing group 104 is arranged with in parallel in knock hole 108, on cover cone 1, the bottom position of knock hole 108 is provided with spring kayser 102, spring kayser 102 is the unitized construction of rigid sleeve and spring, spring kayser 102 is covered with the first magnet coil 103, spring kayser 102 bottom be fixed on cover cone 1 on.
The salient angle face of addendum cone 2 is provided with spacing hole, steel pin 101 is provided with in spacing hole, steel pin 101 is the cylindrical structural of head with cap, end has the draw-in groove of annular, draw-in groove coordinates with described spring kayser 102 and is fixed in spacing hole 108 by steel pin 101, is provided with the second linear slide bearing 106 between the hole wall of spacing hole 108 and steel pin 101.Near port position, spacing hole's circumference is provided with the second magnet coil 105 in spacing hole.On addendum cone 2, the bottom of spacing hole 108 is provided with base 107, base 107 support described steel pin 101 head.
The cover of the coupling mechanism that the unmanned plane that the utility model provides combinationally uses is bored 1 head and is considered pneumatic drag reduction, adopt taper rectification, the conical suface of end cone concave surface and addendum cone 2 head agrees with, taper conjunction plane possesses the ability of bending resistance, antitorque and tension, addendum cone 2 afterbody considers pneumatic drag reduction equally, has carried out taper rectification.Complete fixing by 2 lockout mechanisms after cover cone 1 and addendum cone 2 dock, lockout mechanism is made up of steel pin 101, spring kayser 102, first magnet coil 103 and the linear plain bearing 104 of the second magnet coil 105, first and the second linear slide bearing 106, base 107 etc.Wherein, steel pin 101 is cylindrical, head with cap, prevents it from extracting out in knock hole, and end has the draw-in groove of annular, for axial restraint.The kayser that spring kayser 102 is designed by spring, steel sleeve and rounding forms.Spring kayser inserts in the draw-in groove of steel pin 101, completes the fixing of steel pin.First magnet coil 103 and the second magnet coil 105 adopt electromagnetic principle, by the generation electromagnetic force that switches on power forward or backwards, in drive coil steel pin and spring card slot insertion or exit.First linear plain bearing 104 and the second linear slide bearing 106 are made up of supportable directive slide track and the steel ball etc. that hardens, and are arranged on the hole wall of location, have directional tagging, can reduce the friction force that steel pin 101 inserts or exits.
In concrete use procedure, when unmanned plane combines in the air, as shown in Figure 5, under the guiding of Precise Position System and designating system, two unmanned planes approach gradually, and wherein, the addendum cone 2 of first unmanned plane and the cover of the second frame unmanned plane are bored 1 and aloft achieved a butt joint.The second magnet coil 105 in addendum cone 2 is now energized, and the steel pin 101 on coil axis, under the driving of electromagnetic force, is inserted in the knock hole 108 of first unmanned plane sleeve by the first linear plain bearing 104 and the second linear slide bearing 106.There are in knock hole 108 two symmetrical spring kaysers 102 installed, steel pin 101 can back down the kayser with rounding easily, inserts knock hole 108 li, once kayser springs back in the draw-in groove of steel pin 101, just realize the fixing of steel pin 101, thus the combination realizing unmanned plane connects.Knock hole 108 and steel pin 101 are arranged in power lead in first unmanned plane and the second frame unmanned plane and data line gang socket respectively, and both can realize sharing of electric energy and information between two frame unmanned planes after being communicated with.
When unmanned plane Airborne pollen, as shown in Figure 6, the spring kayser 102 of cover cone 1 exits the draw-in groove of steel pin 101 under the effect of the first magnet coil 103, then the second magnet coil 105 of addendum cone 2 is oppositely energized, steel pin 101 is driven to extract out from butt muff, now unmanned plane constraint relief, realizes automatically being separated with the acceleration and deceleration of the second frame unmanned plane by first unmanned plane.
The coupling mechanism that the unmanned plane that the utility model provides combinationally uses adopts modular design, can realize and the Fast Installation of aircaft configuration and dismounting; Cover cone 1 and the mode of addendum cone 2 tandem docking possess the ability of bending resistance, antitorque and tension, meet unmanned plane and dock operating needs in the air; The fixing steel pin of lockout mechanism and spring kayser all adopt electromagnetic force to drive, and are realized the insertion of steel pin 101 by the positive and negative docking of the electrode of the first magnet coil 103 and the second magnet coil 105 and are exited; Knock hole wall has the first linear plain bearing 104 and the second linear slide bearing 106, has directional tagging, and can reduce the friction force that steel pin 101 inserts and exit; Spring kayser 102 has insertion easily, locking failure-free feature.
The coupling mechanism specific embodiment more than combinationally used in conjunction with unmanned plane of the present utility model is described in detail, but be not to restriction of the present utility model, everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, the category of the coupling mechanism technical scheme combinationally used according to unmanned plane of the present utility model comprises the combination in any between each part mentioned above.
Claims (6)
1. the coupling mechanism that combinationally uses of a unmanned plane, for the parallel combination of unmanned plane, it is characterized in that: comprise cover cone (1), addendum cone (2), wherein, cover cone (1), addendum cone (2) are individually fixed on the wingtip of the different wing of unmanned plane, cover the cone tail shape of (1) and the nose shape of addendum cone (2) agree with, and bore (1) and coordinate the parallel combination assembled and realize unmanned plane between addendum cone (2) by the cover on different aircraft.
2. the coupling mechanism that combinationally uses of unmanned plane as claimed in claim 1, it is characterized in that: the inner side same position of the re-entrant angle of the afterbody of described cover cone (1) is provided with the first lockout mechanism, the both sides same position of the salient angle of the head of described addendum cone (2) is provided with the second lockout mechanism, and the first lockout mechanism coordinates with the second lockout mechanism and realizes described overlapping and bore being fixedly connected with of (1) and described addendum cone (2).
3. the coupling mechanism that combinationally uses of unmanned plane as claimed in claim 2, it is characterized in that: the first lockout mechanism on described cover cone (1) comprises knock hole (108), the first linear plain bearing group (104) is arranged with in parallel in knock hole (108), on described cover cone (1), the bottom position of knock hole (108) is provided with spring kayser (102), the unitized construction that spring kayser (102) is rigid sleeve and spring, spring kayser (102) is covered with the first magnet coil (103), spring kayser (102) bottom is fixed on described cover cone (1).
4. the coupling mechanism that combinationally uses of unmanned plane as claimed in claim 2, it is characterized in that: the salient angle face of described addendum cone (2) is provided with spacing hole, steel pin (101) is provided with in spacing hole, the cylindrical structural that steel pin (101) is head with cap, end has the draw-in groove of annular, draw-in groove coordinates with described spring kayser (102) and is fixed in described spacing hole (108) by steel pin (101), is provided with the second linear slide bearing (106) between the hole wall of described spacing hole (108) and steel pin (101).
5. the coupling mechanism that combinationally uses of unmanned plane as claimed in claim 4, is characterized in that: spacing hole in, close port position is provided with the second magnet coil (105) along spacing hole's circumference.
6. the coupling mechanism that combinationally uses of unmanned plane as claimed in claim 4, it is characterized in that: described addendum cone (2) is upper, the bottom of spacing hole is provided with base (107), base (107) support described steel pin (101) head.
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| CN201520606894.9U CN204937456U (en) | 2015-08-13 | 2015-08-13 | The coupling mechanism that a kind of unmanned plane combinationally uses |
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| CN201520606894.9U CN204937456U (en) | 2015-08-13 | 2015-08-13 | The coupling mechanism that a kind of unmanned plane combinationally uses |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106716273A (en) * | 2016-07-28 | 2017-05-24 | 深圳市大疆创新科技有限公司 | A multirotor unmanned aerial vehicle and a controlling method thereof |
| CN106809394A (en) * | 2017-03-10 | 2017-06-09 | 佛山市神风航空科技有限公司 | A kind of landing system and method for aircraft |
| CN106882384A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106892118A (en) * | 2017-03-10 | 2017-06-27 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106904285A (en) * | 2017-03-10 | 2017-06-30 | 佛山市神风航空科技有限公司 | Take off mode and the device of a kind of aircraft |
| CN109720607A (en) * | 2018-12-29 | 2019-05-07 | 西北工业大学 | More redundancy bolt-types bindiny mechanism for space truss connection |
| CN111452948A (en) * | 2020-03-17 | 2020-07-28 | 哈尔滨工业大学 | Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force |
| CN112124607A (en) * | 2020-10-14 | 2020-12-25 | 王小方 | Unmanned aerial vehicle's suction tube is around pipe mechanism |
| CN112193415A (en) * | 2020-11-12 | 2021-01-08 | 重庆凯创荣智能科技有限公司 | Combined rescue unmanned aerial vehicle and using method thereof |
| CN112623282A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Quick butt joint locking device |
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- 2015-08-13 CN CN201520606894.9U patent/CN204937456U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106716273A (en) * | 2016-07-28 | 2017-05-24 | 深圳市大疆创新科技有限公司 | A multirotor unmanned aerial vehicle and a controlling method thereof |
| CN106809394A (en) * | 2017-03-10 | 2017-06-09 | 佛山市神风航空科技有限公司 | A kind of landing system and method for aircraft |
| CN106882384A (en) * | 2017-03-10 | 2017-06-23 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106892118A (en) * | 2017-03-10 | 2017-06-27 | 佛山市神风航空科技有限公司 | The landing mode and its device of a kind of aircraft |
| CN106904285A (en) * | 2017-03-10 | 2017-06-30 | 佛山市神风航空科技有限公司 | Take off mode and the device of a kind of aircraft |
| CN109720607A (en) * | 2018-12-29 | 2019-05-07 | 西北工业大学 | More redundancy bolt-types bindiny mechanism for space truss connection |
| CN111452948A (en) * | 2020-03-17 | 2020-07-28 | 哈尔滨工业大学 | Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force |
| CN111452948B (en) * | 2020-03-17 | 2023-02-17 | 哈尔滨工业大学 | Self-destructible fixed wing unmanned aerial vehicle based on electromagnetic force |
| CN112124607A (en) * | 2020-10-14 | 2020-12-25 | 王小方 | Unmanned aerial vehicle's suction tube is around pipe mechanism |
| CN112193415A (en) * | 2020-11-12 | 2021-01-08 | 重庆凯创荣智能科技有限公司 | Combined rescue unmanned aerial vehicle and using method thereof |
| CN112193415B (en) * | 2020-11-12 | 2021-12-17 | 江苏润翔软件技术有限公司 | Combined rescue unmanned aerial vehicle and using method thereof |
| CN112623282A (en) * | 2020-12-29 | 2021-04-09 | 中国航空工业集团公司西安飞机设计研究所 | Quick butt joint locking device |
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