CN205381386U - Many rotors unmanned vehicles , subassembly and rotor subassembly - Google Patents
Many rotors unmanned vehicles , subassembly and rotor subassembly Download PDFInfo
- Publication number
- CN205381386U CN205381386U CN201521088850.8U CN201521088850U CN205381386U CN 205381386 U CN205381386 U CN 205381386U CN 201521088850 U CN201521088850 U CN 201521088850U CN 205381386 U CN205381386 U CN 205381386U
- Authority
- CN
- China
- Prior art keywords
- rotor
- fuselage
- connector
- rotor assemblies
- assemblies
- 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.)
- Expired - Fee Related
Links
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 17
- 230000000712 assembly Effects 0.000 claims description 144
- 238000000429 assembly Methods 0.000 claims description 144
- 230000008878 coupling Effects 0.000 claims description 28
- 238000010168 coupling process Methods 0.000 claims description 28
- 238000005859 coupling reaction Methods 0.000 claims description 28
- 239000004020 conductor Substances 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 1
Landscapes
- Toys (AREA)
Abstract
The utility model provides a many rotors unmanned vehicles, this unmanned vehicles includes fuselage, many rotors subassembly and rapid disassembly structure. This fuselage is provided with flight control system, these a plurality of rotor subassemblies are used for providing flight power, this rapid disassembly structure is used for connecting rotor subassembly detachable in this fuselage. Wherein, this rapid disassembly structure connects this rotor subassembly when this fuselage, and this rotor subassembly forms electric connection with this flight control system through this rapid disassembly structure, a plurality of these rapid disassembly structure correspond a plurality of these rotor subassemblies of connecting and can exchange in the hookup location of this fuselage. The utility model discloses still relate to subassembly and rotor subassembly.
Description
Technical field
This utility model relates to a kind of many rotor unmanned aircrafts, assembly and rotor assemblies.
Background technology
Many rotor unmanned aircrafts include horn and the fuselage being connected with this horn, connection between horn and the fuselage of existing many rotor unmanned aircrafts mostly adopts fixing connection, and minority adopts quick-disassembly structure that the left and right horn of many rotor unmanned aircrafts is connected to fuselage.When adopting quick-disassembly structure to connect left and right horn and fuselage, left and right horn can not exchange use, causes that the left and right horn removed soon must be distinguished to avoid setup error in time storing and transport, and is not easy to field maintenance when breaking down.
Utility model content
In view of this, it is necessary to a kind of many rotor unmanned aircrafts that many rotor unmanned aircrafts can be made to be easy to maintenance and transport are provided.
There is a need to provide a kind of assembly for being assembled into many rotor unmanned aircrafts and rotor assemblies.
A kind of many rotor unmanned aircrafts include:
Fuselage, this fuselage is provided with flight control system；
Multiple rotor assemblies, the plurality of rotor assemblies is used for providing flying power；
Quick-disassembly structure, this quick-disassembly structure is for being connected to this fuselage by dismountable for rotor assemblies；
Wherein, when this rotor assemblies is connected to this fuselage by this quick-disassembly structure, this rotor assemblies and this flight control system are electrically connected by this quick-disassembly structure；These rotor assemblies multiple that these quick-disassembly structure correspondences multiple connect can be exchanged in the link position of this fuselage.
Further, this quick-disassembly structure includes joint and the auxiliary section detachably connectable with this joint, and when this rotor assemblies is connected to this fuselage, this rotor assemblies is electrically connected this fuselage by this joint and this auxiliary section.
Further, this joint and this auxiliary section one of them be arranged on this fuselage and be electrically connected with this fuselage, another is arranged in this rotor assemblies and is electrically connected with this rotor assemblies.
Further, this joint includes tube-in-tube structure, and this tube-in-tube structure offers groove, and this groove is used for housing this auxiliary section.
Further, this joint also includes the pin components being electrically connected with this fuselage or this rotor assemblies, and this pin components is fixed on the bottom surface of this groove.
Further, this pin components includes three pins, and three these pins are for being electrically connected with the triple line of three phase mains；This auxiliary section offers three connecting holes, and three these connecting holes are for being electrically connected with the triple line of three phase mains.
Further, this quick-disassembly structure also includes attachment structure, and this attachment structure is connected with this joint or this auxiliary section.
Further, this attachment structure includes fixing plate, and this quick-disassembly structure is connected to this rotor assemblies by this fixing plate, and this joint or this auxiliary section are fixed on this fixing plate；This attachment structure also includes the bolt through this fixing plate, and this quick-disassembly structure is connected to this fuselage by this bolt.
Further, this attachment structure includes fixed part and the shackle member being connected to this fixed part that can dismantle, this fixed part is connected to this fuselage, this rotor assemblies is connected to this fixed part by this shackle member, this shackle member and this fixed part offset or are separated, and make this attachment structure be in the lock state or can disassembly status.
Further, this quick-disassembly structure each includes rotor connector and the fuselage connector removably connected with this rotor connector, and this rotor connector is fixed in this rotor assemblies, and this fuselage connector is fixed on this fuselage；This rotor connector and this fuselage connector can mechanical couplings and electric coupling, when this rotor assemblies is arranged on this fuselage by this fuselage connector and this rotor connector, this fuselage connector and the electric connection of this rotor connector.
Further, this rotor connector each, after the axial rotation predetermined angle of this rotor assemblies, remains able to match with this fuselage connector so that this rotor assemblies rotates this predetermined angle and is arranged on this fuselage.
Further, this rotor assemblies each includes horn and the multiple power set being arranged on this horn.
Further, these power set each include propeller and drive the motor of this propeller rotational.
Further, the work direction of rotation of the multiple power set on this each horn is identical or contrary.
Further, the shape of this horn includes following at least one: T-shaped, and V-type is U-shaped, Y type, X-type.
Further, this rotor connector includes mechanical link and electrical connection section, and this fuselage connector includes the mechanical engagement portion for being coupled with this mechanical link and the electrically mated portion for being coupled with this electrical connection section.
Further, this rotor connector and this fuselage connector are electric-conductor so that this rotor connector and this fuselage connector while mechanical couplings, also electric coupling.
A kind of assembly for being assembled into many rotor unmanned aircrafts, comprising:
Fuselage, this fuselage is provided with fuselage connector and the flight control system being electrically connected with this fuselage connector；And
Multiple rotor assemblies, the plurality of rotor assemblies is used for providing flying power；This rotor assemblies each is provided with the rotor connector for removably connecting with this fuselage connector；This rotor connector and this fuselage connector can mechanical couplings and electric coupling；
Wherein, when this rotor assemblies assembles with this fuselage, this rotor assemblies is matched by this fuselage connector and this rotor assemblies and is arranged on this fuselage, and this fuselage connector is electrically connected with this rotor connector.
Further, the fuselage connector that the rotor connector of one of them this rotor assemblies can be corresponding with this rotor assemblies of another one matches so that the link position of two these rotor assemblies and this fuselage can exchange.
Further, the structure of two these rotor assemblies is identical or differ.
Further, this rotor connector, after the axial rotation predetermined angle of this rotor assemblies, remains able to match with this fuselage connector so that this rotor assemblies rotates this predetermined angle and is arranged on this fuselage.
Further, this rotor assemblies each includes horn and the multiple power set being arranged on this horn.
A kind of rotor assemblies of unmanned vehicle, comprising:
Horn, this horn removably connects for the fuselage with unmanned vehicle；This fuselage is provided with flight control system and the fuselage connector being electrically connected with this flight control system；
Power Component, this Power Component is for providing flying power to this unmanned vehicle, and this Power Component is arranged on this horn；And
Rotor connector, this rotor connector is fixed on the link of this horn and this fuselage；
Wherein, this rotor connector and this fuselage connector can mechanical couplings and electric coupling；When this rotor assemblies is arranged on this fuselage by this fuselage connector and this rotor connector, this fuselage connector is electrically connected with this rotor connector.
Further, this horn is hollow structure, and wire electrically connects through this horn is internal with this rotor connector.
Adopting many rotor unmanned aircrafts of the present utility model, this quick-disassembly structure can be connected to fuselage by dismountable for rotor assemblies, and when this rotor assemblies is connected to this fuselage by this quick-disassembly structure, this rotor assemblies is electrically connected by this quick-disassembly structure and this fuselage；Can exchange between these rotor assemblies multiple that these quick-disassembly structure correspondences multiple connect.This rotor assemblies this fuselage of dismountable connection, and this quick-disassembly structure correspondence multiple connect these rotor assemblies multiple between can exchange so that from these rotor assemblies multiple that this fuselage disassembles store and transport time without distinguish, it is simple to store and transport.Additionally, when this unmanned vehicle breaks down, as rotor assemblies breaks down, it is possible to quickly will appear from the rotor assemblies of fault and be replaced by standby rotor assemblies or quick-replaceable rotor assemblies the parts broken down, it is simple to field maintenance.
Accompanying drawing explanation
Fig. 1 is the decomposing schematic representation of many rotor unmanned aircrafts that this utility model one embodiment provides.
Fig. 2 is the partial enlarged drawing of the many rotor unmanned aircrafts in Fig. 1.
Fig. 3 is the decomposing schematic representation of many rotor unmanned aircrafts that another embodiment of this utility model provides.
Main element symbol description
Following detailed description of the invention will further illustrate this utility model in conjunction with above-mentioned accompanying drawing.
Detailed description of the invention
Below in conjunction with the accompanying drawing in this utility model embodiment, the technical scheme in this utility model embodiment is clearly and completely described, it is clear that described embodiment is only a part of embodiment of this utility model, rather than whole embodiments.Based on the embodiment in this utility model, the every other embodiment that those of ordinary skill in the art obtain under not making creative work premise, broadly fall into the scope of this utility model protection.
It should be noted that be referred to as " being fixed on " another assembly when assembly, it can directly on another assembly or can also there is assembly placed in the middle.When an assembly is considered as " connection " another assembly, it can be directly to another assembly or may be simultaneously present assembly placed in the middle.When an assembly is considered as " being arranged at " another assembly, it can be set directly on another assembly or may be simultaneously present assembly placed in the middle.
Unless otherwise defined, all of technology used herein and scientific terminology are identical with belonging to the implication that those skilled in the art of the present utility model are generally understood that.The purpose describing specific embodiment it is intended merely to herein, it is not intended that in restriction this utility model at term used in the description of the present utility model.Term as used herein " and/or " include the arbitrary and all of combination of one or more relevant Listed Items.
Below in conjunction with accompanying drawing, embodiments more of the present utility model are elaborated.When not conflicting, the feature in following embodiment and embodiment can be mutually combined.
Embodiment of the present utility model provides a kind of many rotor unmanned aircrafts.These many rotor unmanned aircrafts include fuselage, multiple rotor assemblies and multiple quick-disassembly structure.
The plurality of rotor assemblies is used for providing flying power.The plurality of quick-disassembly structure is used for connecting this rotor assemblies and this fuselage.This quick-disassembly structure each includes rotor connector and the fuselage connector removably connected with this rotor connector, and this rotor connector is fixed on this rotor assemblies, and this fuselage connector is fixed on this fuselage.
Wherein in certain embodiments, this rotor connector and this fuselage connector can mechanical couplings and/or electric coupling.
Wherein in some embodiments, this rotor connector can match with this fuselage connector in multiple angle positions.Specifically, this rotor connector each, after the axial rotation predetermined angle of this rotor assemblies, remains able to match with this fuselage connector so that this rotor assemblies rotates this predetermined angle and is arranged on this fuselage.Such as, this predetermined angle is 180 degree so that this rotor assemblies is reverse mounted.
Wherein in some embodiments, the rotor connector of one of them rotor assemblies can match with at least two fuselage connector so that at least two of which rotor assemblies exchanges installation site.
Embodiment of the present utility model also provides for a kind of assembly for being assembled into many rotor unmanned aircrafts, and it includes fuselage and multiple rotor assemblies.
This fuselage is provided with fuselage connector.The plurality of rotor assemblies is used for providing flying power；This rotor assemblies each is provided with the rotor connector for removably connecting with this fuselage connector；This rotor connector and this fuselage connector can mechanical couplings and/or electric coupling.
Wherein in some embodiments, this rotor connector and this fuselage connector mechanical couplings and electric coupling simultaneously.Such as, when this rotor assemblies assembles with this fuselage, this rotor assemblies is matched by this fuselage connector and this rotor connector and is arranged on this fuselage, and this fuselage connector is electrically connected with this rotor connector.
Wherein in some embodiments, the fuselage connector that the rotor connector of one of them this rotor assemblies can be corresponding with this rotor assemblies of another one matches so that the link position of two these rotor assemblies and this fuselage can exchange.The structure of two these rotor assemblies is identical or differs.
Embodiment of the present utility model also provides for the rotor assemblies of a kind of unmanned vehicle, and it includes horn, Power Component and rotor connector.
This horn removably connects for the fuselage with unmanned vehicle.This fuselage is provided with fuselage connector and flight control system, and this flight control system is electrically connected with this fuselage connector.This Power Component is for providing flying power to this unmanned vehicle, and this Power Component is arranged on this horn.This rotor connector is fixed on the link of this horn and this fuselage.Wherein, this rotor connector and this fuselage connector can mechanical couplings and/or electric coupling.
Wherein in some embodiments, this rotor connector and this fuselage connector mechanical couplings and electric coupling simultaneously.Such as, when this rotor assemblies is arranged on this fuselage by this fuselage connector and this rotor connector, this fuselage connector is electrically connected with this rotor connector.
Referring to Fig. 1 and Fig. 2, many rotor unmanned aircrafts 100 that this utility model one embodiment provides, it includes fuselage 10, rotor assemblies 20 and quick-disassembly structure 200.This rotor assemblies 20 is connected to this fuselage 10 by this quick-disassembly structure 200 is dismountable.
This quick-disassembly structure 200 has multiposition mounting means or multi-angle mounting means.Specifically in the illustrated embodiment, corresponding these rotor assemblies 20 multiple connected of these quick-disassembly structures 200 multiple can be exchanged in the link position of this fuselage 10.
When this rotor assemblies 20 is mechanically connected to this fuselage 10 by this quick-disassembly structure 200, this rotor assemblies 20 is electrically connected by this quick-disassembly structure 200 with this fuselage 10 and/or is mechanically connected.Specifically in the illustrated embodiment, this rotor assemblies 20 is provided with rotor connector, this fuselage 10 is provided with fuselage connector, when this rotor assemblies 20 is connected to this fuselage 10, this rotor assemblies 20 and this fuselage 10 concurrently form electric connection by this rotor connector and this fuselage connector and are mechanically connected.Such as, when this rotor assemblies 20 is arranged on this fuselage 10 by this fuselage connector and this rotor connector, this fuselage connector is electrically connected with this rotor connector.
This rotor connector can design according to different demands from the fit system of this fuselage connector, such as, wherein in an embodiment, this rotor connector includes mechanical link and electrical connection section, and this fuselage connector includes the mechanical engagement portion for being coupled with this mechanical link and the electrically mated portion for being coupled with this electrical connection section.In other embodiments, this rotor connector and this fuselage connector can be electric-conductor so that this rotor connector and this fuselage connector while mechanical couplings, also electric coupling.
The concrete structure of this rotor connector can also design according to different demands, for instance, this rotor connector is provided with following at least one: insert, insertion groove, inserts hole, shackle member, buckling piece, slot, connecting hole, threaded connector, screwed hole, engagement piece.
The concrete structure of this fuselage connector can also design according to different demands, for instance, this fuselage connector can be provided with following at least one accordingly: insert, insertion groove, insert hole, fastener, buckling piece, slot, connecting hole, threaded connector, screwed hole, engagement piece.
Specifically in the illustrated embodiment, this fuselage connector includes the auxiliary section 11 being located at this fuselage 10, and this auxiliary section 11 offers several connecting hole 111, and the central shaft of these connecting holes 111 several is substantially parallel.These connecting holes 111 several are electrically connected with this fuselage connector.In the present embodiment, the quantity of this connecting hole 111 is six, six these connecting holes 111 are arranged along two parallel linear interval respectively, and every three these connecting holes 111 interval along these two parallel straight lines is arranged, and is connected respectively the triple line of three phase mains；Being appreciated that in other embodiments, six these connecting holes 111 can be other arrangement modes.This auxiliary section 11 is fixed on an outer surface of this fuselage 10.In the present embodiment, the quantity of this auxiliary section 11 is two, and two these auxiliary sections 11 are relative to this opposing setting of fuselage 10；Being appreciated that in other embodiments, the quantity of this auxiliary section 11 can change according to actual needs.Being additionally provided with this flight control system on this fuselage 10, this flight control system is used for controlling this many rotor unmanned aircrafts 100.This flight control system is electrically connected by this quick-disassembly structure 200 with this rotor assemblies 20.
Further, this fuselage connector also includes the screwed hole 12 of being located at this fuselage 10.In the present embodiment, the quantity of this screwed hole 12 is four, and this screwed hole 12 of each two lays respectively at the both sides of two these auxiliary sections 11；Being appreciated that in other embodiments, the quantity of this screwed hole 12 can increase according to actual needs or reduce.
This rotor assemblies 20 is connected to this fuselage 10 by what this quick-disassembly structure 200 can be dismantled.This rotor assemblies 20 includes horn 21 and is located at the power set on this horn 21.Specifically in the illustrated embodiment, this horn 21 each is provided with multiple power set, and the work direction of rotation of the plurality of power set is identical or contrary.This horn 21 is hollow structure, and wire electrically connects through this horn 21 is internal with this rotor connector.
The shape of this horn 21 can design according to actual needs, for instance, the shape of this horn 21 includes following at least one: T-shaped, and V-type is U-shaped, Y type, X-type.This horn 21 includes multiple link, and one of them link is used for connecting this rotor connector, and all the other links are used for installing this power set.Specifically in the illustrated embodiment, this horn 21 is T-shaped；Specifically, this horn 21 includes linking arm 211 and is fixedly connected on the support arm 212 of this linking arm 211.One end of this linking arm 211 connects this support arm 212, and the other end connects this rotor connector.The two ends of this support arm 212 are respectively fixedly connected with this motor 22.In the present embodiment, the length direction of this linking arm 211 is perpendicular with the length direction of this support arm 212.This rotor connector is arranged on this horn 21, and this rotor connector is electrically connected by wire and this motor 22.In the present embodiment, the quantity of this rotor assemblies 20 is two, two these opposing settings of rotor assemblies 20.
These power set can include motor, electromotor etc..Specifically in the illustrated embodiment, these power set include motor 22 and propeller 23, and this motor 22 drives propeller 23 to rotate.This motor 22 is fixed on this horn 21, and this propeller 23 is connected to this motor 22, and this motor 22 is used for driving this propeller 23 to rotate, thus providing flying power for these many rotor unmanned aircrafts 100.
These many rotor unmanned aircrafts 100 can be four rotor unmanned aircrafts, six rotor unmanned aircrafts, eight rotor unmanned aircrafts or ten rotor unmanned aircrafts etc..Specifically in the embodiment shown in fig. 3, these many rotor unmanned aircrafts 100 are four rotor unmanned aircrafts.The horn 21 of this rotor assemblies 20 each includes two linking arms 211, being connected on support arm 212 of these two linking arm 211 intervals.This rotor connector includes joint 30 and attachment structure 301, and this joint 30 is connected with this attachment structure 301.One end of this linking arm 211 each connects this attachment structure 301 and this joint 30；Fixing a pin components 36 on the bottom surface of the groove 35 of this joint 30 each, three pins of this pin components 36 are connected respectively the triple line of this motor 22.Being provided with four auxiliary sections 11 on this corresponding fuselage 10, matches with corresponding this joint 30 in this auxiliary section 11 each.The quantity of the connecting hole 111 that this auxiliary section 11 each is offered is three.
This rotor connector also includes the fixing plate 31 being located at this joint 30, and this fixing plate 31 includes the stationary plane 311 towards this fuselage 10, and this joint 30 is fixed on this stationary plane 311.Offering screw 32 on this fixing plate 31, this screw 32 runs through this fixing plate 31.In the present embodiment, the quantity of this screw 32 is two, and two these screws 32 are positioned at the both sides of this joint 30；Being appreciated that in other embodiments, the quantity of this screw 32 can change according to actual needs.
This joint 30 matches with this auxiliary section 11, makes this rotor assemblies 20 be electrically connected with this fuselage 10.This joint 30 includes the tube-in-tube structure 34 being fixed on this stationary plane 311, and this tube-in-tube structure 34 offers groove 35, and shape and the size of the shape of this groove 35 and size and this auxiliary section 11 are suitable.Being fixed with pin components 36 on the bottom surface of this groove 35, this pin components 36 is electrically connected with this rotor connector.This pin components 36 includes three pins that are that be made of an electrically conducting material and that be not turned on mutually, and these three pins connect the triple line of this motor 22 of correspondence respectively.Specifically in the embodiment shown in Fig. 1 and 2, the quantity of the pin components 36 of this joint 30 is two, six pins of two these pin components 36 connect the triple line of two these motors 22 of correspondence respectively, and the pin of this pin components 36 of two these motor 22 correspondences is distributed axisymmetricly；The position of six these pins is corresponding with the position of the six of this auxiliary section 11 connecting holes 111.
Being appreciated that in other embodiments, this joint 30 and this auxiliary section 11 can exchange, and namely this auxiliary section 11 is fixed on this stationary plane 311, and this joint 30 is fixed on this fuselage 10.
Specifically in the embodiment shown in Fig. 1 and 2, the quantity of this quick-disassembly structure 200 is two, and two these rotor assemblies 20 are connected to this fuselage 10 respectively through two these quick-disassembly structures 200.Two these joints 30 are separately fixed on the stationary plane 311 of two these fixing plates 31, and two these fixing plates 31 are respectively fixedly connected with one end of the linking arm 211 of the horn 21 of two these rotor assemblies 20.Two these auxiliary sections 11 are separately positioned on two opposing outer surfaces of this fuselage 10.Four bolts 33 are each passed through four these screws 32 and screw in four these screwed holes 12, and two these tube-in-tube structures 34 are respectively fitted on this auxiliary section 11, and this auxiliary section 11 is contained in this groove 35.The pin of four groups of these pin components 36 respectively penetrates in the connecting hole 111 of two these auxiliary sections 11, making this rotor assemblies 20 be connected to this fuselage 10, this motor 22 of correspondence, this rotor connector, this pin components 36, this connecting hole 111 and this fuselage connector are electrically connected.
Two of these many rotor unmanned aircrafts 100 these rotor assemblies 20 can be exchanged, and namely when this quick-disassembly structure 200 departs from this fuselage 10, this rotor assemblies 20 disassembles from this fuselage 10；When re-assemblying, two these rotor assemblies 20 are without distinguishing, the joint 30 of the quick-disassembly structure 200 that two these rotor assemblies 20 all can be connected through and attachment structure 301 matches with any one in two these auxiliary sections 11 so that this rotor assemblies 20 is connected on this fuselage 10, this rotor assemblies 20 is electrically connected with fuselage 10.Two of these many rotor unmanned aircrafts 100 these rotor assemblies 20 can be exchanged so that from two these rotor assemblies 20 that this fuselage 10 disassembles store and transport time without distinguish.Additionally, when these many rotor unmanned aircrafts 100 break down, as rotor assemblies breaks down, it is possible to quickly will appear from the rotor assemblies of fault and be replaced by standby rotor assemblies or quick-replaceable rotor assemblies the parts broken down, it is simple to field maintenance.
It is appreciated that, in other embodiments, this attachment structure 301 can adopt other structures to substitute, such as demountable structure, this demountable structure includes fixed part and the shackle member being connected to this fixed part that can dismantle, and this fixed part is connected to this fuselage 10, and this rotor assemblies 20 is connected to this fixed part by this shackle member, this shackle member and this fixed part offset or are separated, and make this demountable structure be in the lock state or can disassembly status.Wherein, this joint 30 can be arranged in this fixed part, this fuselage 10 or this shackle member, and this corresponding auxiliary section 11 is arranged on this shackle member or this fixed part, this fuselage.
Above-mentioned quick-disassembly structure can be connected to fuselage by what rotor assemblies can be dismantled, and when this rotor assemblies is connected to this fuselage by this quick-disassembly structure, this rotor assemblies is electrically connected by this quick-disassembly structure and this fuselage；Can exchange between these rotor assemblies multiple that these quick-disassembly structure correspondences multiple connect.This rotor assemblies this fuselage of dismountable connection, and this quick-disassembly structure correspondence multiple connect these rotor assemblies multiple between can exchange so that from these rotor assemblies multiple that this fuselage disassembles store and transport time without distinguish, it is simple to store and transport.Additionally, when these many rotor unmanned aircrafts break down, as rotor assemblies breaks down, it is possible to quickly will appear from the rotor assemblies of fault and be replaced by standby rotor assemblies or quick-replaceable rotor assemblies the parts broken down, it is simple to field maintenance.
Additionally; those skilled in the art will be appreciated that; above embodiments is intended merely to explanation this utility model and is not used as this utility model is limited; as long as within this utility model spirit, above example is made suitably change and change all drops within the scope that this utility model claims.
Claims (24)
1. rotor unmanned aircraft more than a kind, it is characterised in that including:
Fuselage, this fuselage is provided with flight control system；
Multiple rotor assemblies, the plurality of rotor assemblies is used for providing flying power；
Quick-disassembly structure, this quick-disassembly structure is for being connected to this fuselage by dismountable for rotor assemblies；
Wherein, when this rotor assemblies is connected to this fuselage by this quick-disassembly structure, this rotor assemblies and this flight control system are electrically connected by this quick-disassembly structure；These rotor assemblies multiple that these quick-disassembly structure correspondences multiple connect can be exchanged in the link position of this fuselage.
2. many rotor unmanned aircrafts as claimed in claim 1, it is characterized in that: this quick-disassembly structure includes joint and the auxiliary section detachably connectable with this joint, when this rotor assemblies is connected to this fuselage, this rotor assemblies is electrically connected this fuselage by this joint and this auxiliary section.
3. many rotor unmanned aircrafts as claimed in claim 2, it is characterised in that: this joint and this auxiliary section one of them be arranged on this fuselage and be electrically connected with this fuselage, another is arranged in this rotor assemblies and is electrically connected with this rotor assemblies.
4. many rotor unmanned aircrafts as claimed in claim 2, it is characterised in that: this joint includes tube-in-tube structure, and this tube-in-tube structure offers groove, and this groove is used for housing this auxiliary section.
5. many rotor unmanned aircrafts as claimed in claim 4, it is characterised in that: this joint also includes the pin components being electrically connected with this fuselage or this rotor assemblies, and this pin components is fixed on the bottom surface of this groove.
6. many rotor unmanned aircrafts as claimed in claim 5, it is characterised in that: this pin components includes three pins, and three these pins are for being electrically connected with the triple line of three phase mains；This auxiliary section offers three connecting holes, and three these connecting holes are for being electrically connected with the triple line of three phase mains.
7. many rotor unmanned aircrafts as claimed in claim 2, it is characterised in that: this quick-disassembly structure also includes attachment structure, and this attachment structure is connected with this joint or this auxiliary section.
8. many rotor unmanned aircrafts as claimed in claim 7, it is characterised in that: this attachment structure includes fixing plate, and this quick-disassembly structure is connected to this rotor assemblies by this fixing plate, and this joint or this auxiliary section are fixed on this fixing plate；This attachment structure also includes the bolt through this fixing plate, and this quick-disassembly structure is connected to this fuselage by this bolt.
9. many rotor unmanned aircrafts as claimed in claim 7, it is characterized in that: this attachment structure includes fixed part and the shackle member being connected to this fixed part that can dismantle, this fixed part is connected to this fuselage, this rotor assemblies is connected to this fixed part by this shackle member, this shackle member and this fixed part offset or are separated, and make this attachment structure be in the lock state or can disassembly status.
10. many rotor unmanned aircrafts as claimed in claim 1, it is characterized in that: this quick-disassembly structure each includes rotor connector and the fuselage connector removably connected with this rotor connector, this rotor connector is fixed in this rotor assemblies, and this fuselage connector is fixed on this fuselage；This rotor connector and this fuselage connector can mechanical couplings and electric coupling, when this rotor assemblies is arranged on this fuselage by this fuselage connector and this rotor connector, this fuselage connector and the electric connection of this rotor connector.
11. many rotor unmanned aircrafts as claimed in claim 10, it is characterized in that: this rotor connector each is after the axial rotation predetermined angle of this rotor assemblies, remain able to match with this fuselage connector so that this rotor assemblies rotates this predetermined angle and is arranged on this fuselage.
12. many rotor unmanned aircrafts as claimed in claim 10, it is characterised in that: this rotor assemblies each includes horn and the multiple power set being arranged on this horn.
13. many rotor unmanned aircrafts as claimed in claim 12, it is characterised in that: these power set each include propeller and drive the motor of this propeller rotational.
14. many rotor unmanned aircrafts as claimed in claim 12, it is characterised in that: the work direction of rotation of the multiple power set on this each horn is identical or contrary.
15. many rotor unmanned aircrafts as claimed in claim 12, it is characterised in that: the shape of this horn includes following at least one: T-shaped, and V-type is U-shaped, Y type, X-type.
16. many rotor unmanned aircrafts as claimed in claim 10, it is characterized in that: this rotor connector includes mechanical link and electrical connection section, this fuselage connector includes the mechanical engagement portion for being coupled with this mechanical link and the electrically mated portion for being coupled with this electrical connection section.
17. many rotor unmanned aircrafts as claimed in claim 10, it is characterised in that: this rotor connector and this fuselage connector are electric-conductor so that this rotor connector and this fuselage connector while mechanical couplings, also electric coupling.
18. for the assembly being assembled into many rotor unmanned aircrafts, comprising:
Fuselage, this fuselage is provided with fuselage connector and the flight control system being electrically connected with this fuselage connector；And
Multiple rotor assemblies, the plurality of rotor assemblies is used for providing flying power；This rotor assemblies each is provided with the rotor connector for removably connecting with this fuselage connector；This rotor connector and this fuselage connector can mechanical couplings and electric coupling；
Wherein, when this rotor assemblies assembles with this fuselage, this rotor assemblies is matched by this fuselage connector and this rotor assemblies and is arranged on this fuselage, and this fuselage connector is electrically connected with this rotor connector.
19. assembly as claimed in claim 18, it is characterised in that: the fuselage connector that the rotor connector of one of them this rotor assemblies can be corresponding with this rotor assemblies of another one matches so that the link position of two these rotor assemblies and this fuselage can exchange.
20. assembly as claimed in claim 19, it is characterised in that: the structure of two these rotor assemblies is identical or differs.
21. assembly as claimed in claim 18, it is characterised in that: this rotor connector, after the axial rotation predetermined angle of this rotor assemblies, remains able to match with this fuselage connector so that this rotor assemblies rotates this predetermined angle and is arranged on this fuselage.
22. assembly as claimed in claim 18, it is characterised in that: this rotor assemblies each includes horn and the multiple power set being arranged on this horn.
23. a rotor assemblies for unmanned vehicle, comprising:
Horn, this horn removably connects for the fuselage with unmanned vehicle；This fuselage is provided with flight control system and the fuselage connector being electrically connected with this flight control system；
Power Component, this Power Component is for providing flying power to this unmanned vehicle, and this Power Component is arranged on this horn；And
Rotor connector, this rotor connector is fixed on the link of this horn and this fuselage；
Wherein, this rotor connector and this fuselage connector can mechanical couplings and electric coupling；When this rotor assemblies is arranged on this fuselage by this fuselage connector and this rotor connector, this fuselage connector is electrically connected with this rotor connector.
24. rotor assemblies as claimed in claim 23, it is characterised in that: this horn is hollow structure, and wire electrically connects through this horn is internal with this rotor connector.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521088850.8U CN205381386U (en) | 2015-12-24 | 2015-12-24 | Many rotors unmanned vehicles , subassembly and rotor subassembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201521088850.8U CN205381386U (en) | 2015-12-24 | 2015-12-24 | Many rotors unmanned vehicles , subassembly and rotor subassembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205381386U true CN205381386U (en) | 2016-07-13 |
Family
ID=56337907
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201521088850.8U Expired - Fee Related CN205381386U (en) | 2015-12-24 | 2015-12-24 | Many rotors unmanned vehicles , subassembly and rotor subassembly |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205381386U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177784A (en) * | 2017-12-14 | 2018-06-19 | 顺丰科技有限公司 | Attachment device and ducted fan and unmanned plane on power-equipment |
| WO2018113480A1 (en) * | 2016-12-21 | 2018-06-28 | 深圳市道通智能航空技术有限公司 | Detachable arm assembly and aircraft |
| CN108317353A (en) * | 2017-01-17 | 2018-07-24 | 深圳市越疆科技有限公司 | A kind of tripod head connection structure and holder |
| CN113978710A (en) * | 2021-10-27 | 2022-01-28 | 广西电网有限责任公司电力科学研究院 | Many rotor unmanned aerial vehicle of power moduleization |
-
2015
- 2015-12-24 CN CN201521088850.8U patent/CN205381386U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018113480A1 (en) * | 2016-12-21 | 2018-06-28 | 深圳市道通智能航空技术有限公司 | Detachable arm assembly and aircraft |
| CN108317353A (en) * | 2017-01-17 | 2018-07-24 | 深圳市越疆科技有限公司 | A kind of tripod head connection structure and holder |
| CN108177784A (en) * | 2017-12-14 | 2018-06-19 | 顺丰科技有限公司 | Attachment device and ducted fan and unmanned plane on power-equipment |
| CN113978710A (en) * | 2021-10-27 | 2022-01-28 | 广西电网有限责任公司电力科学研究院 | Many rotor unmanned aerial vehicle of power moduleization |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105939927B (en) | Multi-rotor unmanned aerial vehicle, assembly and rotor assembly | |
| CN205381386U (en) | Many rotors unmanned vehicles , subassembly and rotor subassembly | |
| US20130160464A1 (en) | Anti-vibration mount | |
| EP2789830B1 (en) | Mounting arrangement | |
| US8120228B2 (en) | Slip ring assembly | |
| US9494082B2 (en) | Electrical connectors | |
| US20150336660A1 (en) | Electric power connector for aircraft drive wheel drive system | |
| EP2799477B1 (en) | Composite structure | |
| EP3035352A1 (en) | Integrated contactor mounting and power distribution system and method | |
| CN105366032A (en) | Unmanned aerial vehicle with folding assemblies | |
| CN205385382U (en) | Connector, driving system and unmanned vehicles of electronic governor and motor | |
| CN205273839U (en) | Unmanned aerial vehicle with folding assembly | |
| EP2800210A2 (en) | Electrical unit with electrical connector | |
| CN107416179B (en) | Four-axis plant protection unmanned aerial vehicle convenient to transportation and loading and unloading | |
| CN204998763U (en) | Rotor craft and mounting that is used for rotor craft | |
| CN102509955A (en) | Misplug-proof structure for connector | |
| CN202333321U (en) | Anti-misinsertion structure for connectors | |
| CN111572752A (en) | Can dismantle many rotor unmanned aerial vehicle of rotor | |
| CN107284654B (en) | Four-axis plant protection unmanned aerial vehicle convenient to transport | |
| CN206640446U (en) | Motor and electric machine fixation structure | |
| CN110606202A (en) | Spliced aircraft | |
| US20240227171A9 (en) | Parallel link robot | |
| CN219154760U (en) | Quick-dismantling connecting assembly of modularized composite wing unmanned aerial vehicle | |
| EP3043075B1 (en) | Conveying device and aircraft system with a conveying device of such a type | |
| CN220733349U (en) | Electric control steering engine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| 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: 20160713 |