CN105923151A - Unmanned aerial vehicle with externally-arranged electronic speed controller structure - Google Patents
Unmanned aerial vehicle with externally-arranged electronic speed controller structure Download PDFInfo
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- CN105923151A CN105923151A CN201610283382.2A CN201610283382A CN105923151A CN 105923151 A CN105923151 A CN 105923151A CN 201610283382 A CN201610283382 A CN 201610283382A CN 105923151 A CN105923151 A CN 105923151A
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- 230000005611 electricity Effects 0.000 claims description 70
- 238000009432 framing Methods 0.000 claims description 21
- 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 description 18
- 238000009434 installation Methods 0.000 claims description 7
- 238000010276 construction Methods 0.000 claims description 5
- 238000012546 transfer Methods 0.000 claims description 5
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 239000004411 aluminium Substances 0.000 claims description 3
- 238000002955 isolation Methods 0.000 claims 1
- 239000007787 solid Substances 0.000 claims 1
- 230000000712 assembly Effects 0.000 abstract description 4
- 238000000429 assembly Methods 0.000 abstract description 4
- 230000007547 defect Effects 0.000 abstract 1
- 230000017525 heat dissipation Effects 0.000 abstract 1
- 230000006835 compression Effects 0.000 description 20
- 238000007906 compression Methods 0.000 description 20
- 238000010586 diagram Methods 0.000 description 12
- 230000008602 contraction Effects 0.000 description 9
- 238000000034 method Methods 0.000 description 7
- 230000007812 deficiency Effects 0.000 description 6
- 238000003466 welding Methods 0.000 description 6
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- 238000007789 sealing Methods 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000003780 insertion Methods 0.000 description 2
- 230000037431 insertion Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 208000031481 Pathologic Constriction Diseases 0.000 description 1
- 206010053615 Thermal burn Diseases 0.000 description 1
- 241000826860 Trapezium Species 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The invention discloses an unmanned aerial vehicle with an externally-arranged electronic speed controller structure and belongs to the field of unmanned aerial vehicles. The unmanned aerial vehicle comprises first rotor wings, second rotor wings, two quick detaching assemblies, rotor wing power assemblies, a first detaching assembly and a signal positioning assembly, wherein the rotor wing power assemblies are fixed to rotor wing shafts, each first rotor wing is rotationally fixed to the corresponding rotor wing power assembly through one quick detaching assembly, and each second rotor wing is rotationally fixed to the corresponding rotor wing power assembly through the other quick detaching assembly; the diameter of each first rotor wing is larger than that of each second rotor wing; the first detaching assembly is fixed to a vehicle body and connected with a cradle head in a sliding manner; and the signal positioning assembly is fixed to a vehicle shell. By the adoption of the unmanned aerial vehicle with the externally-arranged electronic speed controller structure, the technical defect that the heat dissipation performance of an electronic speed controller fixed into a vehicle body is poor in the prior art is overcome.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, particularly to a kind of, there is the unmanned of external electric tune structure
Machine.
Background technology
UAV is called for short " unmanned plane ", is to utilize radio robot and the programme-control provided for oneself
The most manned aircraft that device is handled.Without driving cabin on machine, but automatic pilot, programme-control dress are installed
Put, the equipment such as information collecting device.On ground, naval vessels or machine tool remote control station personnel are by the equipment such as radar,
It is tracked, position, remote control, remote measurement and Digital Transmission.Can be as commonly flying under wireless remotecontrol
Machine equally takes off or launches with booster rocket, it is possible to is taken to by machine tool and throws in flight in the air.
Unmanned plane of the prior art, including fuselage, rotor shaft and The Cloud Terrace, and rotor shaft is fixed rotationally
On fuselage, fuselage interior is additionally provided with flight control system simultaneously.
But, in the prior art, the electricity in unmanned plane is transferred to toward the inside being fixed on fuselage so that put
Electricity in fuselage interior is adjusted and is connected with the flight control system of fuselage interior, and fuselage is often in sealing shape
State, this electricity allowing for being fixed on fuselage interior is adjusted heat dispersion extreme difference, is generated heat the most in the course of the work
Or hot, the final electricity that damages is adjusted, and affects the normal flight of unmanned plane.
Summary of the invention
The present invention provides a kind of unmanned plane with external electric tune structure, solves or part solves existing
The electricity being fixed on fuselage interior is had in technology to adjust the technological deficiency of heat dispersion difference.
For solving above-mentioned technical problem, the invention provides a kind of unmanned plane with external electric tune structure,
Wherein, unmanned plane includes fuselage, rotor shaft, flight control system and The Cloud Terrace, described in there is external electric
The unmanned plane adjusting structure includes: the first rotor；Second rotor；Two Quick-dismantle components；Rotor power assembly,
Described rotor power assembly is fixed in described rotor shaft, and is connected with described flight control system, thinks
Described first rotor and the powered rotation of described second rotor；And described first rotor is fast by one
Tear assembly open to be rotationally fixed on described rotor power assembly so that described first rotor is relative to described rotation
Wing axle is rotatable；Described second rotor is rotationally fixed to described rotor power by another Quick-dismantle component
On assembly so that described second rotor is rotatable relative to described rotor shaft；And described first rotor is straight
Footpath is more than the diameter of described second rotor；And described rotor power assembly at least includes that an electricity is adjusted so that
Described electricity phase modulation is in the outside of described fuselage for described fuselage；First dismounting assembly, described first tears open
Unload assembly to be fixed on described fuselage, and be slidably connected with described The Cloud Terrace, so that described The Cloud Terrace is relative to institute
State the first dismounting assembly or described fuselage can slide；Signal framing assembly, described signal framing group
Part is fixed on described fuselage, and is provided with for unmanned plane is carried out signal in described signal framing assembly
The localizer of location；Wherein, by described first dismounting assembly, described The Cloud Terrace is connected on described fuselage,
Described The Cloud Terrace is dismantled between assembly and described fuselage detachable by described first, and described localizer
It is arranged on described fuselage by described signal framing assembly, outside by described localizer with described fuselage
Boundary's air-flow is isolated.
Optionally, described first dismounting assembly includes: fixed plate, described fixed plate is fixed on described fuselage
On, and be slidably connected with described The Cloud Terrace, so that described The Cloud Terrace slides relative to described fixed plate；Fixed
Position parts, described positioning element is fixed in described fixed plate, with fixing relative to described to described The Cloud Terrace
The position of plate positions, and then realizes described The Cloud Terrace relative to the installation of described fuselage or dismounting.
Optionally, described rotor power assembly includes: refrigerating seat, and described refrigerating seat includes the first stationary plane
With the second stationary plane, described first stationary plane and described second stationary plane transverse axis centered by described rotor shaft,
It is symmetrically dispersed in the both sides of described rotor shaft；First motor, described first motor is fixed on described first
On stationary plane, described first rotor is made to be fixed on described first electricity by what a described Quick-dismantle component rotated
On machine；Second motor, described second motor is fixed on described second stationary plane, makes described second rotor
It is fixed on described second motor by what Quick-dismantle component another described rotated；First electricity is adjusted, and described the
One electricity adjusts the inside being fixed on described refrigerating seat, and controls system with described first motor and described flight respectively
System connects, to be moved the first rotor described in described first driven by motor rotated by described first electricity transfer drive；
Second electricity is adjusted, and described second electricity is adjusted and is fixed on the inside of described refrigerating seat, and respectively with described first motor
Connect with the flight control system within described unmanned plane, to move described second by described second electricity transfer drive
Described in driven by motor, the second rotor rotates.
Optionally, described refrigerating seat is provided with at least one vent, so that the inside of described refrigerating seat is empty
Between communicate with free surrounding space.
Optionally, described first electricity is stealthily substituted and is included: the first electric capacity, first circuit board and the first heat sink；Its
In, described first circuit board controls system with described first electric capacity, described first motor and described flight respectively
System connects, and described first heat sink is attached on described first circuit board；With, described second electricity is stealthily substituted
Include: the second electric capacity, second circuit board and the second heat sink；Wherein, described second circuit board respectively with institute
State the second electric capacity, described second motor and described flight control system to connect, and described second heat sink patch
It is attached on described second circuit board.
Optionally, described first heat sink and/or described second heat sink are aluminium sheets.
Optionally, described first circuit board is between described first electric capacity and described first heat sink；With/
Or, described second circuit board is between described second electric capacity and described second heat sink.
Optionally, in the vertical direction, described first rotor is positioned at the top of described second rotor.
Optionally, described signal framing assembly includes: location bar, described location bar include a fixing end and
One support end, described location bar is fixed on described fuselage by described fixing end；Spiral shell dish, described spiral shell dish
It is fixed on the bar of described location by described support end, and the inside of described spiral shell dish is hollow-core construction so that
Described localizer is fixed in described spiral shell dish.
What the present invention provided has the unmanned plane of external electric tune structure, by being fixed by rotor power assembly
In rotor shaft, and this rotor power assembly at least includes that an electricity is adjusted, owing to rotor power assembly is relative
Be in the outside of fuselage in unmanned plane, this electric phase modulation allowing for being arranged on rotor power assembly is for nothing
The man-machine outside being also at fuselage, the electricity effectively solved in prior art in unmanned plane is adjusted due to often
Being fixed on the inside of fuselage, and fuselage is often in sealing state, this allows for being fixed on fuselage interior
Electricity adjusts heat dispersion extreme difference, generates heat the most in the course of the work or hot, and the final electricity that damages is adjusted, and affects
The technological deficiency of the normal flight of unmanned plane.
Accompanying drawing explanation
In order to be illustrated more clearly that the embodiment of the present invention or technical scheme of the prior art, below will be to reality
Execute the required accompanying drawing used in example to be briefly described, it should be apparent that, the accompanying drawing in describing below is only
It is only some embodiments of the present invention, for those of ordinary skill in the art, is not paying creativeness
On the premise of work, it is also possible to obtain other accompanying drawing according to these accompanying drawings.
The unmanned plane overall structure schematic diagram that Fig. 1 provides for the embodiment of the present invention；
The side view of the unmanned plane that Fig. 2 provides for Fig. 1；
In the unmanned plane that Fig. 3 provides for Fig. 1, the annexation overall structure of the first dismounting assembly and The Cloud Terrace is shown
It is intended to；
First dismounting assembly and the annexation overall structure side of The Cloud Terrace in the unmanned plane that Fig. 4 provides for Fig. 1
View；
Fig. 5 is the first dismounting assembly overall structure schematic diagram in Fig. 4；
Fig. 6 is the first dismounting assembly overall structure front view in Fig. 5；
In the unmanned plane that Fig. 7 provides for the embodiment of the present invention, the first location plunger is in cuing open under contraction state
View；
What in the unmanned plane that Fig. 8 provides for the embodiment of the present invention, the first location plunger was under contraction state is whole
Body structural representation；
In the unmanned plane that Fig. 9 provides for the embodiment of the present invention, the first location plunger is in cuing open under raised position
View；
What in the unmanned plane that Figure 10 provides for the embodiment of the present invention, the first location plunger was under raised position is whole
Body structural representation；
The overall structure schematic diagram of fuselage in the unmanned plane that Figure 11 provides for the embodiment of the present invention；
Figure 12 is the close-up schematic view of the second dismounting assembly in Figure 11；
The overall structure schematic diagram of signal framing assembly in the unmanned plane that Figure 13 provides for the embodiment of the present invention；
The sectional view of signal framing assembly in the unmanned plane that Figure 14 provides for the embodiment of the present invention；
The first motor, refrigerating seat and the annexation of rotor shaft three that Figure 15 provides for the embodiment of the present invention
Schematic diagram；
The first motor, refrigerating seat and the annexation of rotor shaft three that Figure 16 provides for the embodiment of the present invention
Sectional view；
The overall structure schematic diagram that Figure 17 adjusts for the first electricity that the embodiment of the present invention provides；
The side view that Figure 18 adjusts for the first electricity that the embodiment of the present invention provides；
The first motor that Figure 19 provides for the embodiment of the present invention, the second motor, refrigerating seat, rotor shaft
Annexation schematic diagram；
The structural front view of the Quick-dismantle component that Figure 20 provides for the embodiment of the present invention；
The overall structure schematic diagram of the Quick-dismantle component that Figure 21 provides for the embodiment of the present invention；
The overall structure schematic diagram of the another unmanned plane that Figure 22 provides for the embodiment of the present invention；
Figure 23 is the annexation schematic diagram of the first rotor and the second rotor in Figure 22.
Detailed description of the invention
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the present invention, and
It is not all, of embodiment.Based on the embodiment in the present invention, those of ordinary skill in the art are obtained
Every other embodiment, broadly falls into the scope of protection of the invention；Wherein involved in this enforcement "and/or"
Key word, represent and or two kinds of situations, in other words, A and/or B mentioned by the embodiment of the present invention,
Illustrate A and B, two kinds of situations of A or B, describe three kinds of states existing for A Yu B, such as A and
/ or B, represent: only include A and do not include B；Only include B and do not include A；Including A and B.
Meanwhile, in the embodiment of the present invention, when assembly is referred to as " being fixed on " another assembly, and it is permissible
Directly on another assembly or assembly placed in the middle can also be there is.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, and it can be to be set directly at another group
On part or may be simultaneously present assembly placed in the middle.Term " vertical " used in the embodiment of the present invention,
" level ", "left", "right" and similar statement are merely for purposes of illustration, and are not intended to limit
The present invention processed.
What the present invention provided has the unmanned plane of external electric tune structure, by being fixed by rotor power assembly
In rotor shaft, and this rotor power assembly at least includes that an electricity is adjusted, owing to rotor power assembly is relative
Be in the outside of fuselage in unmanned plane, this electric phase modulation allowing for being arranged on rotor power assembly is for nothing
The man-machine outside being also at fuselage, the electricity effectively solved in prior art in unmanned plane is adjusted due to often
Being fixed on the inside of fuselage, and fuselage is often in sealing state, this allows for being fixed on fuselage interior
Electricity adjusts heat dispersion extreme difference, generates heat the most in the course of the work or hot, and the final electricity that damages is adjusted, and affects
The technological deficiency of the normal flight of unmanned plane.Structure is adjusted in order to offer of the present invention being had external electric
Unmanned plane elaborates, to support the technical problem to be solved, below, the present invention provides
Embodiment in, first the overall structure of unmanned plane is elaborated, then narration unmanned plane mistake
Cheng Zhong, draws the unmanned plane with external electric tune structure that the present invention provides the most targetedly,
To reach purpose complete, clear, that understand.
Refer to Fig. 1-2,11,14, embodiments provide a kind of unmanned plane, including fuselage 1,
Rotor shaft 2, The Cloud Terrace 3, the first dismounting assembly 4, signal framing assembly 5 and rotor power assembly 6.
Wherein, described rotor shaft 2 is rotationally fixed on described fuselage 1 by its one end, to realize rotation
Wing axle 2 is collapsible relative to fuselage, then completes rotor shaft 2 dynamic with the expansion action of fuselage or contraction
Make.In embodiments of the present invention, the quantity of rotor shaft 2 can be 4, and 4 described rotor shaft 2
Symmetrical four corner portions being distributed in fuselage 1.The inside of described fuselage 1 is additionally provided with for controlling
The flight control system of unmanned plane during flying.On the other end of rotor shaft 2, it is fixed with described rotor power
Assembly 6, and be connected with the flight control system set by fuselage 1 inside, think that the rotation of rotor provides dynamic
An electricity tune described above is at least included in power, and described rotor power assembly 6.
Meanwhile, described first dismounting assembly 4 is fixed on described fuselage 1, and dismantles by described first
Detachable for described The Cloud Terrace 3 is connected on described fuselage 1 by assembly 4 so that described The Cloud Terrace 3 passes through
Described first dismounting assembly 4 can be with described fuselage 1 quickly, dismantle flexibly of the present invention to constitute
The double paddle structures being applied to unmanned plane.Certainly, consolidating between the first dismounting assembly 4 and described fuselage 1
It can be diversified for determining connected mode, as can be bolt connect, can be screw connect, permissible
It is welding, it is also possible to be one-body molded, do not limit in this embodiment of the present invention, as long as being capable of the
One dismounting assembly 4 is fixed on described fuselage 1.
Further, described signal framing assembly 5 is fixed on described fuselage 1, and described signal framing
A localizer 53 it is provided with in assembly 5.Certainly, localizer 53 is mainly used in embodiments of the present invention
The transmission of positional information is carried out between unmanned plane and earth station, unmanned to be monitored in real time by localizer 53
The position of machine and flight information, for the type of localizer 53, the embodiment of the present invention is not limited to,
Can be navigational route type receiver, geodetic type receiver or time service type receiver etc..However it is necessary that explanation
It is that, in the embodiment of the present invention, described localizer 53 is arranged on described machine by described signal framing assembly 6
On body 1, thus make the extraneous gas of localizer 53 with described fuselage 1 by signal framing assembly 6
Stream is isolated；Effectively avoid localizer 53 the most exposed when external fuselage, unmanned plane during flying process
Middle external air flow, extraneous dampness or extraneous shelter because of with localizer 53 Long Term Contact or friction and lead
The localizer 53 caused makes moist or damages, and has the advantages that security performance is high.
Below, the building block of each several part of unmanned plane is elaborated.
For above-mentioned first dismounting assembly 4, refer to Fig. 3-11, wherein, described first
Dismounting assembly 4 at least includes: fixed plate 41 and positioning element 42.
Wherein, described fixed plate 41 is fixed on described fuselage 1, and is slidably connected with described The Cloud Terrace 3,
So that described The Cloud Terrace 3 slides relative to described fixed plate 41, and owing to fixed plate 41 is relative to machine
Body 1 is fixed, and then realizes The Cloud Terrace 3 and slide relative to fuselage 1.Certainly, fixed plate 41 and described
Fixing connected mode between fuselage 1 can be diversified, as being bolt connection, Ke Yishi
Screw connects, can be welding, it is also possible to is one-body molded, does not limits in this embodiment of the present invention,
As long as being capable of fixed plate 41 to be fixed on described fuselage 1.Described positioning element 42 is fixed on institute
State in fixed plate 41, so that described The Cloud Terrace 3 is positioned relative to the position of described fixed plate 41, enter
And realize described The Cloud Terrace 3 and install relative to described fuselage or dismounting.
Here, positioning element 42 is equivalent to screens parts, when The Cloud Terrace 3 is installed on fuselage by needs
Time on 1, now slide into a certain position relative to fixed plate 41 between The Cloud Terrace 3 and fixed plate 41, then
By positioning element 42, the The Cloud Terrace 3 of this position is positioned, to prevent The Cloud Terrace 3 relative to fixed plate 41
Slide.And when The Cloud Terrace 3 pulled down by needs, the most only need manual toggle positioning element 42, it is allowed to The Cloud Terrace 3
Skid off relative to fixed plate 41, can realize The Cloud Terrace 3 quick, dismantle flexibly.During this, The Cloud Terrace
Installation and removal without by any extraneous utensil such as spanner etc., easy to operate, it is quick, convenient to have
Feature.
In embodiments of the present invention, as preferably, please continue to refer to Fig. 5-6, described fixed plate 42 is permissible
Being the U-shaped shape in cross section, the described fixed plate 42 under this shape at least may include that the first side plate 411；
Second side plate 412 and transverse slat 413.Wherein, described first side plate 411 is equal with described second side plate 412
OK；And described first side plate 411 and described second side plate 412 perpendicular with described transverse slat 413, and institute
State transverse slat 413 to be slidably connected with described first side plate 411 and described second side plate 412 respectively, described cloud
Platform 3 is fixing with described transverse slat 413 to be connected, and then makes described The Cloud Terrace 3 relative by described transverse slat 413
Slide in described first side plate 411 and described second side plate 412.Meanwhile, described positioning element 41
It is individually fixed on described first side plate 411 and described second side plate 412, with to described transverse slat 413 phase
Position for described first side plate 411 and described second side plate 412 positions.Certainly, described
Side plate 411, fixing connected mode between described second side plate 412 and described fuselage 1 can be multiple
Various, as being bolt connection, can be screw connection, can be welding, it is also possible to be one
Molding, does not limits in this embodiment of the present invention, if be capable of described first side plate 411, described
Two side plates 412 are fixed on described fuselage 1.
Same principle, the fixing connected mode between described The Cloud Terrace 3 and described transverse slat 413 can also be
Diversified, as being bolt connection, can be screw connection, can be welding, it is also possible to be
One-body molded, do not limit in this embodiment of the present invention, as long as being capable of described The Cloud Terrace 3 and described horizontal stroke
Plate 413 is relatively fixed, all within protection scope of the present invention.
Further, for ease of being fixed with the transverse slat 413 of The Cloud Terrace 3, it is possible to and the first side plate 411, second
Side plate 412 is flexibly, quickly slide, in order to The Cloud Terrace 3 flexibly, is quickly installed or dismounting.Make
For on a kind of embodiment of the embodiment of the present invention, described first side plate 411 and described second side plate 412
It is respectively arranged with a chute, to be arranged in described chute by described transverse slat 413 so that described transverse slat 413
Slided relative to described first side plate 411 and described second side plate 412 by described chute.
Meanwhile, one end of described positioning element 42 corresponding through described first side plate 411, described second
Side plate 412, and in described chute internal projection or contraction, so that one end of described positioning element 42 is relative
In described chute in described chute internal projection time, one end of described positioning element 42 stops described transverse slat 413
Slide in described chute, one end of described positioning element 42 relative to described chute at described chute
During contract, one end of described positioning element 42 is separated with described transverse slat 413, so that described transverse slat 413
Slide in described chute.
Need exist for explanation, in embodiments of the present invention, described " protruding " it can be understood as
Being that parts slip in some parts, " contraction " can be understood as parts and skid off some portion
Part.Such as, one end of described positioning element 42 described above relative to described chute in described chute
Time protruding, i.e. refer to that one end of described positioning element 42 is slipped in described chute, positioning element 42 described above
One end relative to described chute when described chute contract, i.e. refer to that one end of described positioning element 42 is sliding
Go out described chute.The Cloud Terrace 3 is realized relative to the dismounting of fuselage 1 or peace by positioning element 42 with this
Dress.For described positioning element 42, in embodiments of the present invention, the one as the present embodiment is real
Existing mode, described positioning element 42 can at least include: the first location plunger and described second location plunger.
And described first location plunger include the first positioning end；Described second location plunger includes the second positioning end.
Wherein, described first positioning end corresponding through described first side plate, and at described first side plate 411
In chute internal projection or contraction so that described first positioning end is relative to described first side plate 411
In chute internal projection time, described first positioning end stop described transverse slat 413 slide in chute,
Described first positioning end is when relative to chute contract in described first side plate 411, and described first is fixed
Position end is separated, so that described transverse slat 413 slides in chute with described transverse slat 413.Wherein,
Described second positioning end corresponding through described second side plate 412, and the cunning in described second side plate 412
Groove internal projection or contraction, so that described second positioning end is relative to the cunning in described second side plate 412
During groove internal projection, described second positioning end stops that described transverse slat 413 slides in chute, described the
Two positioning ends when relative to chute contract in described second side plate 412, described second positioning end with
Described transverse slat is separated, so that described transverse slat 413 slides in chute.
Here, can be it can be understood as the first side plate 411 and the second side as shown in Fig. 5 or Fig. 6
The both sides being distributed in described transverse slat 413 of plate 412 symmetry, thus make the both sides of described transverse slat 413
Described first side plate 411 is inserted and in chute that described second side plate 412 is offered while correspondence, with
This realizes the transverse slat 413 being fixed with The Cloud Terrace 3 and carries out relative to the first side plate 411 and the second side plate 412
Slide.Meanwhile, in order to preferably the transverse slat 413 in sliding process be positioned.The embodiment of the present invention
By the first location plunger and the second location plunger, the both sides at transverse slat 413 of symmetrical setting, namely
First location plunger and the first side plate 411 are corresponding, and the second location plunger and the second side plate 412 are corresponding.
It should be noted that in embodiments of the present invention, the structure of the first side plate 411 and the second side plate 412 can
With identical can also be different, the first location plunger and the second location plunger can identical can also
Different.And in embodiments of the present invention, for convenience of description, the first selected side plate 411 and the second side
Plate 412 structure is identical, and the structure of the first location plunger and the second location plunger is identical.
Certainly, it will be understood by those skilled in the art that the first side plate 411 and the second side plate 412, first are fixed
Position plunger and the second location plunger can also be mutually different various structures, as permissible in the first side plate 411
Being square structure, the second side plate 412 can be rectangle structure, or the first side plate 411 can be
Trapezium structure, the second side plate 412 can be square or the polygonized structure such as rectangle or rhombus.
In other words, as long as be capable of the first side plate 411 and the second side plate 412 is relatively fixed with fuselage 1,
And transverse slat 413 can first side plate 411 that slide relative with the first side plate 411 and the second side plate 412 and
Second side plate 412 structure, all within protection scope of the present invention.Same, the first location plunger and
Second location plunger can also be multiple different structure, as long as disclosure satisfy that the first location plunger can be right
Answer through the first side plate 411, the second location plunger can be corresponding through the second side plate 412, and each
Projection or flexible is carried out, to carry out transverse slat 413 spacing to the greatest extent may be used in the chute of its correspondence.It is placed in
One location plunger and second location plunger planform the most identical, the embodiment of the present invention do not do into
One step limits.
Please continue to refer to Fig. 7-10, as stated above, as a kind of embodiment of the embodiment of the present invention,
Assuming that the first selected in embodiments of the present invention location plunger and the second location plunger are the complete phases of structure
With, as a example by the first location plunger 421 shown in Fig. 7-10, the internal structure of location plunger is made
Further describe.
Such as Fig. 7-10, described first location plunger 421 includes: the first bolt 4211, first positions
Swivel nut 4212, first positions spring 4213.Wherein, described first bolt 4211 is provided with described
First positioning end 4211a；Described first positioning thread insert 4212 is set on described first bolt 4211,
And between described first positioning thread insert 4212 and described first bolt 4211, it is provided with one first compression
Space 4214.The internal diameter that can be understood as the most described first positioning thread insert 4212 is more than
The external diameter of described first bolt 4211, thus makes the first positioning thread insert 4212 be set in described
Time on first bolt 4211, there is therebetween neutral region, this neutral region is above-mentioned
One compression stroke 4214.Described first location spring is arranged in described first compression stroke 4214；Wherein,
Described first positioning end 4211a sequentially passes through described first location spring 4213, described first compression stroke
4214 and described first side plate 411, with the chute internal projection in described first side plate 411 or contraction.
It is noted that be that the first positioning end 4211a is in described first side plate 411 shown in Fig. 7-8
Chute contract state time schematic diagram.Shown in Fig. 9-10 is that the first positioning end 4211a is described
Schematic diagram during chute internal projection state in side plate 411.And in order to preferably position first
Spring 4213 is the most now in the first compression stroke 4214, and described in the embodiment of the present invention, first positions
On the described first positioning end 4211a of bolt 4211, it is provided with one first card convex 4215, with by described
One location spring 4213 is fully defined in described first compression stroke 4214, and makes described first to determine
Position end 4211a is when relative to chute contract in described first side plate 411, by described first card convex
The described first location spring 4213 of 4215 compressions.
Specifically, the embodiment of the present invention is during actual job, and the first location spring 4213 is first
In compression stroke 4214, whole process is in compression or its pre-compressed state, thus makes in its natural state,
First location spring 4213 the first compression stroke 4214 in by the elasticity tension promotion described the of self
One positioning end 4211a is entered in the chute of described first side plate 411 by the first side plate 411, and then to being in
Transverse slat 413 in chute positions.And when needs transverse slat 413 skids off from chute, Ye Jixu
When The Cloud Terrace 3 being dismantled from fuselage 1, now have only to manual toggle the first bolt 4211, make
The first positioning end 4211a compresses the first location spring 4213 by the first card convex 4215, then make the
One positioning end 4211a skids off in the chute of the first side plate 411, so realize transverse slat 413 relative to
Side plate 411 skids off.And when without External Force Acting after the first bolt 4211, first position spring
Under the elasticity tension effect of 4213, continue to press on the first positioning end 4211a and carry out return, namely Fig. 9 or
The duty of the first location plunger 421 shown in person Figure 10.Effectively achieve the peace installation and dismantling of The Cloud Terrace
Unload without by any extraneous utensil such as spanner etc., easy to operate, have quickly, feature easily.
In embodiments of the present invention, described second location plunger includes: the second bolt, described second
Bolt is provided with described second positioning end；Second positioning thread insert, described second positioning thread insert is set in
On described second bolt, and it is provided with between described second positioning thread insert and described second bolt
One second compression stroke；Second location spring, described second location spring is arranged at described second compression sky
In；Wherein, described second positioning end sequentially passes through described second location spring, described second compression sky
Between and described second side plate, with the chute internal projection in described second side plate or contraction.Described second
On described second positioning end of bolt, it is provided with one second card convex, with by described second location spring
It is limited in described second compression stroke, and makes described second positioning end relative to described second side plate
In chute contract time, by described second card convex compression described second location spring.
As it has been described above, the second location plunger in the embodiment of the present invention and the first locating dowel shown in Fig. 7-10
The structure of plug 421 is identical, the most no longer repeats the internal structure of the second location plunger, right
In the non-detailed portion of internal structure of the second location plunger, see the first locating dowel in the embodiment of the present invention
The detailed portion of plug 421.
Secondly, for the fuselage 1 that the embodiment of the present invention provides, see Fig. 1-2 and 11-12, this
The fuselage 1 that inventive embodiments provides has removable feature.Thus make again to the inside of fuselage 1
During installing device, convenient, fast.Specifically, described fuselage 1 at least may include that body 12,
Casing 11 and the second dismounting assembly 13.Wherein, the inside of described body 12 is hollow-core construction；Described machine
At least one installing port 121 it is provided with on body 12；Described second dismounting assembly 13 can by described casing 11
Being connected on described body 12 of dismountable.Meanwhile, described first dismounting assembly 4 is fixed on described body
Bottom, and described signal framing assembly 5 is fixed on described body 12；So that at described body 12
In parts to be installed be placed into by described installing port relative to described body 12 or be removed.As
Preferably, the quantity of the described second dismounting assembly 13 in the embodiment of the present invention is at least 2, and 2 institutes
State two dismounting assemblies and be symmetrically dispersed in the both sides of described casing 11, in order between casing 11 and body 12
Connection more firm.
Further, see Figure 12, described second dismounting assembly 13 includes: socket 131 and the 3rd is fixed
Position plunger 132.Wherein, described socket 131 is fixed on described body 12；Described 3rd location plunger
132 are fixed in described casing 11, and described 3rd location plunger 132 includes the 3rd positioning end.So
Allow in the described socket of insertion 131 that described 3rd positioning end is corresponding, with by described casing 11 and described
Body 12 clamping.
Here it should be noted that socket 131 is for inserting in described second dismounting assembly 13
Parts carry out the effect of screens, are similar to keeper principle.3rd locating dowel in described second dismounting assembly 13
Plug 132 is for insertion in socket 131, and then casing 11 and body 12 play the work that bridge connects
With.Certainly, in the embodiment of the present invention, the structure of the 3rd location plunger 132 can be diversified.
Such as, can as shown in figure 12, described 3rd location plunger 132 may include that locating dowel 1321
With the 3rd caging bolt 1322, described locating dowel 1321 is fixed in described casing 11, and the described 3rd
Caging bolt 1322 is fixed in described locating dowel 1321；Described 3rd caging bolt 1322 is arranged
State the 3rd positioning end.And then insert in socket 131 casing 11 is entered with body 12 by the 3rd positioning end
Row removably connects.As the quantity of above-mentioned second dismounting assembly 13 is at least 2, and 2 described two
Dismounting assembly is symmetrically dispersed in the both sides of described casing 11.In specific implementation process, can first mate slotting
Enter the 3rd caging bolt 1322 and the socket 131 of side, then in the 3rd limit of corresponding coupling opposite side
Position bolt 1322 and socket 131.Certainly, in this kind of embodiment, casing 11 can also be by flexibility
Material is constituted so that casing 11 presents flexible characteristic, and so pinching the both sides of casing 11 by hands can make
Casing 11 is prolonged the center portion thereof position and is curved, the corresponding body 12 of placing of the casing 11 after bending is fixed with
On the position of two sockets 131, loosening the casing 11 being pinched, such casing 11 is in the elasticity of self
Automatically restoring to original state under tension force effect, the casing 11 in recovery process is owing to being precisely placed on
Two the 3rd caging bolts 1322 and the position of two socket 131 correspondences, after thus making to recover
The most corresponding each being inserted in two sockets 131 by two the 3rd caging bolts 1322 of casing 11, complete
Become and be connected with the quick of body 12.There is feature easily and efficiently.
For another example, the 3rd location plunger 132 in the embodiment of the present invention can also is that such as above-mentioned first dismounting group
The structure of the first location plunger in part 4.That is: the described 3rd positions plunger 132 may include that location
Post 1321, described locating dowel 1321 is fixed in described casing 11；3rd bolt, the described 3rd
Bolt is fixed in described locating dowel, and described 3rd bolt is provided with described 3rd positioning end；
3rd positioning thread insert, described 3rd positioning thread insert is set on described 3rd bolt, and the described 3rd
It is provided with one the 3rd compression stroke between positioning thread insert and described 3rd bolt；3rd location spring,
Described 3rd location spring is arranged in described 3rd compression stroke；Wherein, described 3rd positioning end is successively
Insert in described socket through described 3rd location spring, described 3rd compression stroke.Further, institute
State on described 3rd positioning end of the 3rd bolt, be provided with one the 3rd card convex, with fixed by the described 3rd
Position spring is limited in described 3rd compression stroke, and described 3rd positioning end is divided mutually with described socket
From time, by described 3rd card convex compression described 3rd location spring.
In embodiments of the present invention, as the presently preferred embodiments, described 3rd caging bolt and/or the described 3rd
Bolt is mutually perpendicular to described locating dowel.Fixing connection between described locating dowel and described casing is
Welding；And/or, described locating dowel and described casing are one-body molded.Described locating dowel is 3rd spacing with described
Fixing connection between bolt and/or described 3rd bolt is welding；And/or, described locating dowel and institute
State the 3rd caging bolt one-body molded.
Again, for described signal framing assembly 5, refer to Figure 13-14, described signal framing group
Part 5 also includes: location bar 51 and spiral shell dish 52.Wherein, described location bar 51 includes fixing end 511
With a support end 512, described location bar 51 is fixed in described casing 11 by described fixing end 511.
Described spiral shell dish 52 is fixed on described location bar 51 by described support end 512, and described spiral shell dish 52
Internal in hollow-core construction so that described localizer 53 is fixed in described spiral shell dish 52.Described localizer 53
Being arranged on described fuselage 1 by location bar 51 and spiral shell dish 52, thus making will be fixed by spiral shell dish 52
Position device 53 is isolated with the external air flow of described fuselage 1；Effectively avoid localizer 53 the most exposed
When external fuselage, external air flow during unmanned plane during flying, extraneous dampness or extraneous shelter because of with
Localizer 53 Long Term Contact or friction and the localizer 53 that causes make moist or damage, and have safety
The feature that energy is high.
As preferably, described location bar 51 and described casing 11 are one-body molded；And/or, described location bar
5151 and described spiral shell dish 52 one-body molded.Certainly, for spiral shell dish 52, it is the equal of localizer
One protective cover of 53, for localizer 53 is protected, in embodiments of the present invention, described spiral shell dish
52 can at least include: the first blind nut 521, and described first blind nut 521 is provided with female thread；Second spiral shell
Lid 522, described second blind nut 522 is provided with external screw thread, described first blind nut 521 and described second blind nut
522 threaded composition described spiral shell dish 52；Wherein, described first blind nut 521 and described second blind nut 522
Can be with rounded shape, it is also possible to be square shape, or diamond shaped, the embodiment of the present invention does not limits.Value
Obtaining one to be mentioned that, the angle constituted between described location bar 51 and described casing 11 is an acute angle.
That is, the center vertical pivot of location bar 51 is not mutually perpendicular to the plane at casing 11 place, and location bar 51
Inclined plane, with towards tail orientation, the most further reduces location bar 51 in unmanned plane during flying process
In with the contact resistance of external air flow.
Again, for rotor power assembly 6, refer to Figure 15-16, described rotor power assembly 6
At least include: the first motor 61, refrigerating seat 63 and the first electricity are adjusted 64 (the first electricity is adjusted 64 and following the
Two electricity are adjusted and all be can be understood as heat radiating type electricity tune).First rotation of power is provided owing to rotating to be unmanned plane during flying
What the wing rotated is fixed on described first motor 61；Described refrigerating seat 63 is fixed in described rotor shaft 2,
And described first motor 61 is fixed on described refrigerating seat 63.In embodiments of the present invention, refrigerating seat 63
Inside be hollow-core construction, and described first electricity adjusts 64 inside being fixed on described refrigerating seat 63, and point
It is not connected with the described flight control system within described first motor 61 and fuselage 1, flies described in passing through
Row control system controls described first electricity and adjusts 64, it is achieved drive described first motor 61 to drive described first rotation
The wing rotates.
It should be strongly noted that described refrigerating seat 63 is provided with at least one vent 631, with by institute
The inner space stating refrigerating seat 63 communicates with free surrounding space.Thus make when adjusting 64 to fix the first electricity
When the inside of refrigerating seat 63, real-time and refrigerating seat 63 periphery cold air forms convection current, with to first
Electricity adjusts 64 to cool down in real time, effectively avoids and causes the first electricity because the first electricity adjusts 64 overheated mistakes to scald
Adjust 64 cannot be properly functioning technological deficiency.Meanwhile, 64 are adjusted to be directly fixed on fuselage 1 first electricity
Peripheral position, and owing to the first rotor is arranged on refrigerating seat 63, therefore the first electricity adjusts 64 and first to revolve
Connection line between the wing is the shortest, significantly reduces the first electricity and adjusts between the first rotor because there is line
Pass by power attenuation that is long and that cause, possess efficient, energy-conservation feature.
Certainly, in embodiments of the present invention, referring to Figure 19, rotor power assembly 6 can also include
Two motors 62 and the second electricity are adjusted, and described second electricity adjust respectively with described second motor 62 and described flight
Control system connects.At this point it is possible to be interpreted as that described refrigerating seat 63 includes that the first stationary plane and second is fixed
Face, described first motor 61 is fixed on described first stationary plane, and described second motor 62 is fixed on institute
State on the second stationary plane, to move described second motor 63 drive the second rotor to enter by described second electricity transfer drive
Row rotates.Same with the first electricity phase modulation, described second electricity adjusts the inside also being secured to described refrigerating seat 63.This
Sample by shown in Figure 19 2 motors are set and 2 electricity are adjusted, and then realize the unmanned plane knot of coaxial double-oar
Structure.
In embodiments of the present invention, it can be identical structure that the first electricity is in harmonious proportion that the second electricity adjusts, with the
As a example by one electricity adjusts 64, referring to Figure 17-18, it at least may include that first electric capacity the 641, first circuit
Plate 642 and the first heat sink 643.Wherein, described first circuit board 642 respectively with described first electric capacity
641, described first motor 61 and described flight control system connect, and described first heat sink 643 pastes
It is attached on described first circuit board 642.As preferably, described first heat sink 643 can be aluminium sheet.
So on the one hand, the first electricity is adjusted 64 to carry out by convection by the vent 631 offered at refrigerating seat
Cooling, adjusts 64 to dispel the heat the first electricity simultaneously also by the first heat sink 643 further.To reach to protect
Card the first electricity adjusts the technique effect of 64 safe operations.
For the second electricity is adjusted, identical with the first electricity tune 64, it is also possible to include: the second electric capacity；Second
Circuit board；And second heat sink；Wherein, described second circuit board respectively with described second electric capacity, described
Second motor and described flight control system connect, and described second heat sink is attached to described second circuit
On plate.Due in embodiments of the present invention, the internal structure that the internal structure that the second electricity is adjusted is adjusted with the first electricity
Identical, here is omitted, the non-detailed portion of internal structure that the second electricity is adjusted, and refers to the first electricity
Adjust.
As preferably, described first circuit board is between described first electric capacity and described first heat sink；
And/or, described second circuit board is between described second electric capacity and described second heat sink.
Further, continuing with seeing Figure 20-23, between the first motor 61 and the first rotor 8
Annexation, for annexation between the second motor 62 and the second rotor 9, the embodiment of the present invention
Additionally provide a kind of Quick-dismantle component, between the first motor 61 and the first rotor, the second motor 62 and
Quick Release between second rotor 9 connects.Realize carry out first rotor the 8, second rotor 9 installation or
During dismantlement work, it is only necessary to by rotating described first rotor 8 or described second rotor 9, the can be realized
Fastening between one rotor 8 and the first motor 61, between the second motor 62 and the second rotor 9 or point
From, namely without can complete by external operation instrument (such as handle) the first rotor 8 installation or
Dismantlement work, has quick, portable and that working performance is high feature.
Specifically, in the present embodiment, the first motor 61 includes first surface 611 and second surface 612.
In an embodiment, first surface 611 can be understood as the upper surface of the first motor 61, second surface 612
Can be understood as the lower surface of the first motor 61, and described first motor 61 is by described first surface
611 are fixed on the first stationary plane of refrigerating seat 63, and described second motor 62 is by described second surface
612 are fixed on the second stationary plane of refrigerating seat 63.
It is significant to note that, in prior art for many rotor wing unmanned aerial vehicles of coaxial double-oar, its
Coaxial two rotor often diameters, shape are identical, and are positioned at the both sides up and down of rotor shaft, and position
Rotor above rotor shaft, rotating when, needs the air-flow relying on its lower surface to produce this rotor
Thrust upwards, realizes lift upwards overall to unmanned plane then.Obviously, the air-flow stream of its lower surface
Dynamic area is the biggest, then this rotor is produced thrust upwards the biggest, then realize to unmanned plane overall to
On lift the biggest.And exactly identical due to two coaxial rotor sizes, this allows for
The rotor of side and the rotor of lower section are during rotating, and the rotor of lower section is due to himself occupied sky
Between area and block top rotor lower surface most of air current flow area, entirety reduces nothing then
Man-machine lift upwards, causes flight efficiency low.
And in the present embodiment, by transverse axis centered by described rotor shaft, by the first rotor 8 and second
Rotor 9 is symmetrically dispersed in the both sides of rotor shaft 2, and the diameter of the first rotor 8 is more than the second rotor 9
Diameter, it is achieved the overall size of the first rotor 8 is more than the overall size of the second rotor 9, and this allows for
During first rotor 8 and the second rotor 9 rotate at the same time, the second rotor 9 greatly reduce by
In himself exist spatial area, the obstruction to the air current flow area of first its lower surface of rotor 8,
Ensure that the air-flow of first its lower surface of rotor 8 to thrust size upwards produced by this rotor, then
It also avoid the overall upwards lift of unmanned plane to reduce and affect the technological deficiency of its flight efficiency.There is flight
The feature that efficiency is high.
For Quick-dismantle component 7, two Quick-dismantle components 7 can be selected so that described first rotor 8 leads to
Crossing a Quick-dismantle component correspondence to be rotationally fixed on described first motor, described second rotor 9 is by another
One Quick-dismantle component correspondence is rotationally fixed on described second motor.Owing to the first rotor 8 passes through Quick Release
Assembly 7 and the annexation of the first motor, action principle, with the second rotor 9 by Quick-dismantle component 7 with
The annexation of the second motor, action principle are identical, and therefore, following the present embodiment is only by with the
One rotor 8 is described in detail as a example by being connected by a Quick-dismantle component and the first motor 61, the second rotor
9 are repeated no more by the annexation action principle between a Quick-dismantle component and the second motor 61, can one
And describe refering to the connection between following first rotor 8 and the first motor 61.
Specifically, during actual job, Quick-dismantle component 7 is by the first rotor 8 and the first motor 61 2
Person is threaded.Make the first rotor of unmanned plane to be installed when needing during actual job or
When person dismantles, the most only need to rotate described first rotor 8, such as first rotor 8 or the inverse time that turned clockwise
Pin rotates the first rotor 8, can realize the installation between described first rotor 8 and described first motor 61
Or dismounting.Compared to traditional bolt that directly uses, the first rotor 8 is fixed on the first motor 61, when
Need from the first motor 61, dismantle the first rotor 8, or when installing, be both needed to come by extraneous handle
Turn bolt, dismounting and the installment work of the first rotor 8 can be completed.And due to for connecting the first rotation
The wing 8 and the individual component that fixing bolt is individualism of the first motor 61, when turning bolt by handle
When being unloaded, often due to the complexity of execute-in-place environment, easily cause the loss of fixing bolt,
And once fix bolt loss, the most just cannot complete the first rotor 8 and installment work of the first motor 61,
I.e. cause the serious consequence that flight equipment cannot fly.And the present embodiment, it is exactly based on employing Quick-dismantle component 7
By threaded to both the first rotor 8 and the first motor 61 so that the two is when installing or dismantle, nothing
Need to be quick and convenient by external operation instrument (such as handle), have the advantages that working performance is high.
For Quick-dismantle component 7, continuing with seeing Figure 21, described Quick-dismantle component 7 at least includes: the first spiral shell
Nail 71, second screw the 72, first screw buckle 73 and the first dismounting nut 74.Wherein, described first spiral shell
The inwall of stricture of vagina button 73 is provided with the first female thread 76, and the bottom of described first screw buckle 73 offers
One screw 77 so that described first screw 432 passes described first screw 77 by described first screw buckle
On 73 first surfaces 611 being fixed on described first motor 61.The outer wall of described first dismounting nut 74
It is provided with first external screw thread 78 suitable with described first female thread 76, and described first dismounting nut
The top of 74 offers the second screw 79 so that described second screw 72 sequentially pass through described first rotor 8,
Described first dismounting nut 74 is fixed on described first rotor 8 by described second screw 79.
Wherein, the first screw buckle 73 is fixed on the first surface 611 of the first motor 61 by the first screw 71
On, the first dismounting nut 74 is fixed on the first rotor 8 by the second screw 72.And first screw buckle
The first female thread 76 that the inwall of 73 is offered, and first dismounting nut 74 outer wall offered first
External screw thread 78 mates completely, namely can realize occlusion between the first female thread 76 and the first external screw thread 78
Locking.Thus make, when the first rotor 8 is arranged in rotor shaft 3 by needs, due to the first electricity
Machine 61 is fixed on the end of rotor shaft 3, also will be arranged on the first motor 61 by the first rotor 8.This
Time, it is only necessary to manual rotation the first rotor 8 so that the first external screw thread 78 is engaged mutually with the first female thread 76,
Continue to rotate, then realize the first dismounting nut 74 and locking of the first screw buckle 73, owing to first tears open
Removing nut 74 is fixed on the first rotor 8, and the first screw buckle 73 is fixed on the first motor 61, namely
The locking achieving the first rotor 8 and the first motor 61 (rotor shaft 3) is installed.And when disassembly is desired,
The most only need to reversely rotate the first rotor 8, it is achieved the separation of the first external screw thread 78 and the first female thread 76 is i.e.
Can.There is feature swift to operate, convenient.
It should be noted that unmanned plane is during practical flight, the direction of rotation of the first rotor 8 is inverse
Hour hands direction of rotation, now, owing in flight course, the first rotor 8 itself is in rotating shape
State, and itself be also to use to rotate to realize fastening in an embodiment between the first rotor 8 and the first motor 61
Connected mode.Such as, it is by the realization that turns clockwise when the first rotor 8 relative to the first motor 61
When fastening therebetween, due in flight course the first rotor 8 normally rotate to be counterclockwise, now with
The the most normal of the first rotor 8 to rotate, namely the first rotor 8 is equivalent to the first motor 61 and has the inverse time
The driving that pin rotates.And owing to the first rotor 8 is by the ability that turns clockwise relative to the first motor 61
Realization fastens therebetween, then otherwise when occurring that the first rotor 8 is the inverse time relative to the first motor 61
When pin rotates, the fastening relationships between the first rotor 8 and the first motor 61 i.e. can be caused to occur loosening, very
Occur to the phenomenon causing the first rotor 8 to fly away from the first motor 61 and to cause unmanned plane to crash.
Therefore, rotate counterclockwise due to the normal of the first rotor 8 in flight course in order to avoid unmanned plane
And causing the fastening relationships between the first rotor 8 and the first motor 61 to occur loosening, the embodiment of the present invention will
Rotate, between first rotor 8 and the first motor 61, the direction that the direction tightened is also configured to rotate counterclockwise.
That is, first dismantles first external screw thread 78 set by outer wall of nut 74 and the interior of the first screw buckle 73
The occlusion locking direction of the first female thread 76 set by wall is also counterclockwise.Thus make when the
When one rotor 8 is to realize fastening therebetween by rotation counterclockwise relative to the first motor 61, owing to flying
During row the first rotor 8 normally rotate to be counterclockwise, now along with the first rotor 8 the most just
Often rotate, namely the first rotor 8 is equivalent to the first motor 61 and also has the trend of rotation counterclockwise.
And owing to the first rotor 8 could realize two by rotation counterclockwise exactly relative to the first motor 61
Fastening between person, so on the one hand, is effectively prevented when the first rotor 8 is relative to the first motor 61
When being to be locked by the realization occlusion that turns clockwise, due to normally rotating to be counterclockwise of the first rotor 8
Cause the fastening relationships between the first rotor 8 and the first motor 61 to occur loosening, even result in the first rotor
8 fly away from the first motor 61 and the technological deficiency that causes unmanned plane to crash.On the other hand, due to the first rotor
8 itself is also by rotating counterclockwise the fastening that could realize therebetween relative to the first motor 4, when with
The the most normal of the first rotor 8 to rotate, and make the first rotor 8 be equivalent to the first motor 61 and also have
The trend rotated counterclockwise, the most also increases the first rotor 8 and the first motor 61 is the tightest
Gu relation, it is ensured that the normal safe flight of flight equipment, have the advantages that security performance is high.
Further, continuing with seeing Figure 20-21, as described above, when by the second screw 72 successively
Through described first rotor 8, described second screw 79, described first dismounting nut 74 is fixed on described the
Time on one rotor 8, owing to unmanned plane is in flight course, the external resistance suffered by the first rotor 8 because of
Element is more, such as air-flow, wind direction etc..This allows in flight course the first rotor 8 relative to the first motor
61 and/or the vibrations of rotor shaft 3 bigger, but, long vibrations can make the second screw 72,
Annexation extremely unstable between one rotor 8 and the first dismounting nut 74 three, even causes the second spiral shell
Nail 72 loosens, and then causes security incident.Therefore, the present embodiment by setting up the first vibration damping sheet 75, and
Described first vibration damping sheet 75 offers the first through hole, so that described second screw 72 sequentially passes through described
Described first dismounting nut 437 is fixed on institute by the first through hole, described first rotor 8 and the second screw 79
State on the first rotor 8.As preferably, the first vibration damping sheet 75 can be in disc-shaped, to increase the first vibration damping sheet
75 and first contact area of rotor 8 upper surface, by the second screw 72 by the first vibration damping sheet 75 and
One rotor 8 upper surface is relative to fastening, to reduce the vibrations relative to the first motor 61 of first rotor 8,
Improve the safety and stability performance in flight course.
As preferably, the quantity of described first screw 71 is 2；The quantity of described second screw 72 is 2
Individual；The quantity of described first screw 77 is 2；The quantity of described second screw 79 is 2.Wherein,
Each corresponding described first screw 77 of described first screw 71 so that each described first screw
Described first screw buckle 73 is fixed on described first electricity through corresponding described first screw 77 by 71
On machine 61；Each corresponding described second screw 79 of described second screw 72 so that each institute
State the second screw 72 to be fixed on by described first screw buckle 73 through corresponding described second screw 79
On described first motor 61.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know
Basic creative concept, then can make other change and amendment to these embodiments.So, appended power
Profit requires to be intended to be construed to include preferred embodiment and fall into all changes and the amendment of the scope of the invention.
Obviously, those skilled in the art can carry out various change and modification without deviating from this to the present invention
The spirit and scope of invention.So, if these amendments of the present invention and modification belong to right of the present invention and want
Ask and within the scope of equivalent technologies, then the present invention is also intended to comprise these change and modification.
Claims (9)
1. have external electric adjust structure a unmanned plane, wherein, unmanned plane include fuselage, rotor shaft,
Flight control system and The Cloud Terrace, it is characterised in that described in have external electric adjust structure unmanned plane include:
First rotor；
Second rotor；
Two Quick-dismantle components；
Rotor power assembly, described rotor power assembly is fixed in described rotor shaft, and with described flight
Control system connects, and thinks described first rotor and the powered rotation of described second rotor；And it is described
First rotor is rotationally fixed on described rotor power assembly by a Quick-dismantle component so that described
One rotor is rotatable relative to described rotor shaft；Described second rotor is by another Quick-dismantle component rotationally
It is fixed on described rotor power assembly so that described second rotor is rotatable relative to described rotor shaft；
And the diameter of described first rotor is more than the diameter of described second rotor；And described rotor power assembly is at least
Adjust including an electricity so that described electricity phase modulation is in the outside of described fuselage for described fuselage；
First dismounting assembly, described first dismounting assembly is fixed on described fuselage, and sliding with described The Cloud Terrace
It is dynamically connected, so that described The Cloud Terrace can slide relative to described first dismounting assembly or described fuselage；
Signal framing assembly, described signal framing assembly is fixed on described fuselage, and described signal framing
The localizer for unmanned plane being carried out signal framing it is provided with in assembly；
Wherein, by described first dismounting assembly, described The Cloud Terrace is connected on described fuselage so that described
The Cloud Terrace is by detachable between described first dismounting assembly and described fuselage, and described localizer is by described
Signal framing assembly is arranged on described fuselage, with the external air flow phase by described localizer with described fuselage
Isolation.
There is external electric the most as claimed in claim 1 and adjust the unmanned plane of structure, it is characterised in that institute
State the first dismounting assembly to include:
Fixed plate, described fixed plate is fixed on described fuselage, and is slidably connected with described The Cloud Terrace, so that
Described The Cloud Terrace slides relative to described fixed plate；
Positioning element, described positioning element is fixed in described fixed plate, with to described The Cloud Terrace relative to institute
The position stating fixed plate positions, and then realizes described The Cloud Terrace relative to the installation of described fuselage or dismounting.
There is external electric the most as claimed in claim 2 and adjust the unmanned plane of structure, it is characterised in that institute
State rotor power assembly to include:
Refrigerating seat, described refrigerating seat includes the first stationary plane and the second stationary plane, described first stationary plane and
Described second stationary plane transverse axis centered by described rotor shaft, is symmetrically dispersed in the both sides of described rotor shaft；
First motor, described first motor is fixed on described first stationary plane, makes described first rotor lead to
That crosses that described Quick-dismantle component rotates is fixed on described first motor；
Second motor, described second motor is fixed on described second stationary plane, makes described second rotor lead to
Cross another described Quick-dismantle component rotate be fixed on described second motor；
First electricity is adjusted, and described first electricity adjusts the inside being fixed on described refrigerating seat, and respectively with described first
Motor and described flight control system connect, to move described first driven by motor by described first electricity transfer drive
Described first rotor rotates；
Second electricity is adjusted, and described second electricity adjusts the inside being fixed on described refrigerating seat, and respectively with described second
Flight control system within motor and described unmanned plane connects, with dynamic described by described second electricity transfer drive
Described in second driven by motor, the second rotor rotates.
There is external electric the most as claimed in claim 3 and adjust the unmanned plane of structure, it is characterised in that
Described refrigerating seat is provided with at least one vent, with by the inner space of described refrigerating seat and the external world
Space communicates.
There is external electric the most as claimed in claim 4 and adjust the unmanned plane of structure, it is characterised in that
Described first electricity is stealthily substituted and is included: the first electric capacity, first circuit board and the first heat sink；Wherein, described
First circuit board is connected with described first electric capacity, described first motor and described flight control system respectively,
And described first heat sink is attached on described first circuit board；
With,
Described second electricity is stealthily substituted and is included: the second electric capacity, second circuit board and the second heat sink；Wherein, described
Second circuit board is connected with described second electric capacity, described second motor and described flight control system respectively,
And described second heat sink is attached on described second circuit board.
There is external electric the most as claimed in claim 5 and adjust the unmanned plane of structure, it is characterised in that
Described first heat sink and/or described second heat sink are aluminium sheets.
7. the external electric that has as described in claim 5 or 6 adjusts the unmanned plane of structure, it is characterised in that
Described first circuit board is between described first electric capacity and described first heat sink；
And/or,
Described second circuit board is between described second electric capacity and described second heat sink.
There is external electric the most as claimed in claim 1 and adjust the unmanned plane of structure, it is characterised in that
In the vertical direction, described first rotor is positioned at the top of described second rotor.
There is external electric the most as claimed in claim 1 and adjust the unmanned plane of structure, it is characterised in that institute
State signal framing assembly to include:
Location bar, described location bar includes fixing end and a support end, and described location bar is by described solid
Fixed end is fixed on described fuselage；
Spiral shell dish, described spiral shell dish is fixed on the bar of described location by described support end, and described spiral shell dish is interior
Portion is hollow-core construction so that described localizer is fixed in described spiral shell dish.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610283382.2A CN105923151B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with external electric tune structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610283382.2A CN105923151B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with external electric tune structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105923151A true CN105923151A (en) | 2016-09-07 |
| CN105923151B CN105923151B (en) | 2018-09-07 |
Family
ID=56837747
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610283382.2A Expired - Fee Related CN105923151B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with external electric tune structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105923151B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109720558A (en) * | 2019-02-19 | 2019-05-07 | 深圳市翔农创新科技有限公司 | The unmanned plane of layout is adjusted based on electricity |
| CN113460295A (en) * | 2017-08-31 | 2021-10-01 | 深圳市大疆创新科技有限公司 | Radiator assembly for electric regulation, electric regulation assembly, power system and unmanned aerial vehicle |
-
2016
- 2016-04-29 CN CN201610283382.2A patent/CN105923151B/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113460295A (en) * | 2017-08-31 | 2021-10-01 | 深圳市大疆创新科技有限公司 | Radiator assembly for electric regulation, electric regulation assembly, power system and unmanned aerial vehicle |
| CN109720558A (en) * | 2019-02-19 | 2019-05-07 | 深圳市翔农创新科技有限公司 | The unmanned plane of layout is adjusted based on electricity |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105923151B (en) | 2018-09-07 |
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