CN105818997B - Multi-rotor unmanned aerial vehicle - Google Patents
Multi-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN105818997B CN105818997B CN201610283293.8A CN201610283293A CN105818997B CN 105818997 B CN105818997 B CN 105818997B CN 201610283293 A CN201610283293 A CN 201610283293A CN 105818997 B CN105818997 B CN 105818997B
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- Prior art keywords
- side plate
- positioning
- rotor
- fixed
- chute
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- 230000005611 electricity Effects 0.000 claims abstract description 52
- 238000009432 framing Methods 0.000 claims abstract description 24
- 230000006835 compression Effects 0.000 claims description 33
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- 230000007812 deficiency Effects 0.000 abstract description 6
- 239000006185 dispersion Substances 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 12
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- 238000003466 welding Methods 0.000 description 5
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- 230000004048 modification Effects 0.000 description 4
- 238000004134 energy conservation Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 230000000630 rising effect Effects 0.000 description 2
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- 206010053615 Thermal burn Diseases 0.000 description 1
- 241000826860 Trapezium Species 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
- B64D47/08—Arrangements of cameras
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/14—Direct drive between power plant and rotor hub
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B64D27/40—
Abstract
The invention discloses a kind of multi-rotor unmanned aerial vehicle, belongs to unmanned air vehicle technique field, and the multi-rotor unmanned aerial vehicle includes：First dismounting component, the first dismounting component are fixed on the body；Signal framing component, the signal framing component are fixed on the casing；Rotor power component, the rotor power component are fixed in the rotor shaft, and the rotor power component comprises at least an electricity and adjusted；Quick-dismantle component, first rotor are rotationally fixed on the rotor power component by the Quick-dismantle component.The present invention solves the technological deficiency for the electricity tune heat dispersion difference for being fixed on fuselage interior in the prior art.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, more particularly to a kind of multi-rotor unmanned aerial vehicle.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without driving cabin on machine, but the equipment such as automatic pilot, presetting apparatus, information collecting device are installed.
On ground, naval vessels or machine tool remote control station personnel are by equipment such as radars, and it is tracked, positioned, is remotely controlled, remote measurement and numeral pass
It is defeated.It can take off as conventional airplane or be launched with booster rocket under wireless remotecontrol, can also be taken to by machine tool in the air
Launch flight.
Unmanned plane of the prior art, including fuselage, rotor shaft and head, and rotor shaft is rotationally fixed 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 for being fixed on fuselage so that is placed in fuselage interior
Electricity adjust and be connected with the flight control system of fuselage interior, and fuselage is often in sealing state, and this allows for being fixed on fuselage
Internal electricity adjusts heat dispersion extreme difference, easily heating or hot in the course of the work, and final damage electricity is adjusted, and influences unmanned plane
Normal flight.
The content of the invention
The present invention provides a kind of multi-rotor unmanned aerial vehicle, solves or part solves and is fixed on fuselage interior in the prior art
Electricity adjust heat dispersion difference technological deficiency.
In order to solve the above technical problems, the invention provides a kind of multi-rotor unmanned aerial vehicle, wherein, unmanned plane include fuselage,
First rotor, rotor shaft, head and flight control system, the multi-rotor unmanned aerial vehicle include：First dismounting component, described first
Dismounting component is fixed on the fuselage；Signal framing component, the signal framing component are fixed on the fuselage, and described
The locator for carrying out signal framing to unmanned plane is provided with signal framing component；Rotor power component, the rotor move
Power component is fixed in the rotor shaft, and is connected with the flight control system, is provided with the rotation for first rotor
Power, and the rotor power component comprises at least an electricity and adjusted；Quick-dismantle component, first rotor pass through the Quick-dismantle component
It is rotationally fixed on the rotor power component；Wherein, the head is connected to by the described first dismounting component described
On fuselage so that the head is by detachable between the described first dismounting component and the fuselage, and the locator passes through
The signal framing component is arranged on the fuselage, and the external air flow of the locator and the fuselage is isolated.
Optionally, the first dismounting component includes：Fixed plate, the fixed plate are fixed on the fuselage, and with institute
State head to be slidably connected, so that the head enters line slip relative to the fixed plate；Positioning element, the positioning element are fixed
In in the fixed plate, to be positioned to the head relative to the position of the fixed plate, and then the head phase is realized
Install or dismantle for the fuselage.
Optionally, the fixed plate includes：First side plate；Second side plate, first side plate and the second side plate phase
It is parallel；Transverse slat, first side plate and second side plate and the transverse slat are perpendicular, and the transverse slat is respectively with described first
Side plate and second side plate are slidably connected, and the head is fixedly connected with the transverse slat, and then pass through the transverse slat institute
State head and enter line slip relative to first side plate and second side plate；The positioning element is individually fixed in described first
On side plate and second side plate, to determine relative to the position of first side plate and second side plate the transverse slat
Position.
Optionally, a chute is respectively arranged with first side plate and second side plate, the transverse slat is set
In the chute so that the transverse slat is slided by the chute relative to first side plate and second side plate
It is dynamic；Through first side plate, second side plate corresponding to one end of the positioning element, and in the chute internal projection or
Person shrink so that one end of the positioning element relative to the chute in the chute internal projection, the positioning element
One end stops that the transverse slat enters line slip in the chute, and one end of the positioning element is relative to the chute in the cunning
During groove contract, one end of the positioning element is separated with the transverse slat, so that the transverse slat is slided in the chute
It is dynamic.
Optionally, the positioning element includes：First positioning plunger, the first positioning plunger include the first positioning end；
Second positioning plunger, the second positioning plunger include the second positioning end；Wherein, through described corresponding to first positioning end
First side plate, and the chute internal projection in first side plate or contraction, so that first positioning end is relative to institute
When stating the chute internal projection in the first side plate, first positioning end stops that the transverse slat enters line slip in chute, described the
In the chute contract in relative to first side plate, first positioning end is separated one positioning end with the transverse slat,
So that the transverse slat enters line slip in chute；Wherein, second side plate is passed through corresponding to second positioning end, and in institute
Chute internal projection or the contraction in the second side plate are stated, so that cunning of second positioning end in relative to second side plate
During groove internal projection, second positioning end stops that the transverse slat enters line slip in chute, second positioning end relative to
During chute contract in second side plate, second positioning end is separated with the transverse slat, so that the transverse slat is in cunning
Enter line slip in groove.
Optionally, the first positioning plunger includes：First bolt, first bolt are provided with described
One positioning end；First positioning thread insert, first positioning thread insert are set on first bolt, and first positioning
One first compression stroke is provided between swivel nut and first bolt；First retaining spring, first retaining spring
It is arranged in first compression stroke；Wherein, first positioning end sequentially passes through first retaining spring, described first
Compression stroke and first side plate, with the chute internal projection in first side plate or contraction；With second positioning
Plunger includes：Second bolt, second bolt are provided with second positioning end；Second positioning thread insert, it is described
Second positioning thread insert is set on second bolt, and between second positioning thread insert and second bolt
It is provided with one second compression stroke；Second retaining spring, second retaining spring are arranged in second compression stroke；Its
In, second positioning end sequentially passes through second retaining spring, second compression stroke and second side plate, with
Chute internal projection or contraction in second side plate.
Optionally, on first positioning end of first bolt, one first card convex is provided with, by described
One retaining spring is limited in first compression stroke, and causes first positioning end in relative to first side plate
Chute contract when, pass through first card convex and compress first retaining spring；And/or second bolt
On second positioning end, one second card convex is provided with, second retaining spring is limited to second compression stroke
It is interior, and cause second positioning end in the chute contract in relative to second side plate, to pass through second card convex
Compress second retaining spring.
Optionally, the signal framing component also includes：Locating rod, the locating rod include a fixing end and a support
End, the locating rod are fixed on the fuselage by the fixing end；Spiral shell disk, the spiral shell disk are fixed on by the support end
In the locating rod, and the inside of the spiral shell disk is in hollow-core construction so that the locator is fixed in the spiral shell disk.
Optionally, the rotor power component includes：First motor so that the first rotor rotational is fixed on described first
On motor；Refrigerating seat, the refrigerating seat are fixed in the rotor shaft, and first motor is fixed on the refrigerating seat；
First electricity is adjusted, and first electricity adjusts the inside for being fixed on the refrigerating seat, and is controlled respectively with first motor and the flight
System processed connection, rotated with the first rotor described in moving first motor driven by the described first electric transfer drive；Wherein, institute
State refrigerating seat and be provided with least one ventilating opening, the inner space of the refrigerating seat is communicated with free surrounding space.
Optionally, first electricity, which is stealthily substituted, includes：First electric capacity；First circuit board；And first heat sink；Wherein, described
One circuit board is connected with first electric capacity, first motor and the flight control system respectively, and first radiating
Plate is attached on the first circuit board.
Multi-rotor unmanned aerial vehicle provided by the invention, its head by the first dismounting component it is detachable be fixed on fuselage
Bottom, instead of it is traditional it is direct head is fixed on fuselage, caused by head dismounting it is complicated, and must in unloading process
The technological deficiency that extraneous disassembling tool could be dismantled must be relied on.Meanwhile rotor power component is fixed on rotation in the present invention
On wing axle, rotor is arranged on rotor power component, thinks the powered rotation of rotor, and the rotor power component is at least
Adjusted including an electricity.This allows for electricity tune in the present invention and is directly fixed on fuselage periphery as the building block of rotor power component
Position, and because rotor is arranged on rotor power component, therefore electricity adjusts the connection line between rotor very short, greatly
Reduce electricity adjust and rotor between because exist circuit it is long caused by power attenuation, possess efficiently, energy-conservation the characteristics of.
Brief description of the drawings
In order to illustrate more clearly about the embodiment of the present invention or technical scheme of the prior art, below will be to institute in embodiment
The accompanying drawing needed to use is briefly described, it should be apparent that, drawings in the following description are only some implementations of the present invention
Example, for those of ordinary skill in the art, on the premise of not paying creative work, can also be obtained according to these accompanying drawings
Obtain other accompanying drawings.
Fig. 1 is unmanned plane overall structure diagram provided in an embodiment of the present invention；
Fig. 2 is the side view for the unmanned plane that Fig. 1 is provided；
Fig. 3 is the annexation overall structure diagram of the first dismounting component and head in the unmanned plane that Fig. 1 is provided；
Fig. 4 is the annexation overall structure side view of the first dismounting component and head in the unmanned plane that Fig. 1 is provided；
Fig. 5 is the first dismounting component overall structure diagram in Fig. 4；
Fig. 6 is the first dismounting component overall structure front view in Fig. 5；
Fig. 7 is the sectional view that first positioning plunger is under contraction state in unmanned plane provided in an embodiment of the present invention；
Fig. 8 is that the overall structure that first positioning plunger is under contraction state in unmanned plane provided in an embodiment of the present invention is shown
It is intended to；
Fig. 9 is the sectional view that first positioning plunger is under raised position in unmanned plane provided in an embodiment of the present invention；
Figure 10 is the overall structure that first positioning plunger is under raised position in unmanned plane provided in an embodiment of the present invention
Schematic diagram；
Figure 11 is the overall structure diagram of unmanned plane middle fuselage provided in an embodiment of the present invention；
Figure 12 is the close-up schematic view of the second dismounting component in Figure 11；
Figure 13 is the overall structure diagram of signal framing component in unmanned plane provided in an embodiment of the present invention；
Figure 14 is the sectional view of signal framing component in unmanned plane provided in an embodiment of the present invention；
Figure 15 is the first motor provided in an embodiment of the present invention, refrigerating seat and the connection relationship diagram of rotor shaft three；
Figure 16 is the first motor provided in an embodiment of the present invention, refrigerating seat and the annexation sectional view of rotor shaft three；
Figure 17 is the overall structure diagram that the provided in an embodiment of the present invention first electricity is adjusted；
Figure 18 is the side view that the provided in an embodiment of the present invention first electricity is adjusted；
Figure 19 is the first motor provided in an embodiment of the present invention, the second motor, refrigerating seat, the annexation of rotor shaft
Schematic diagram；
Figure 20 is the structural front view of Quick-dismantle component provided in an embodiment of the present invention；
Figure 21 is the overall structure diagram of Quick-dismantle component provided in an embodiment of the present invention.
Embodiment
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 clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, rather than whole embodiments.It is based on
Embodiment in the present invention, the every other embodiment that those of ordinary skill in the art are obtained, belong to what the present invention protected
Scope；Involved "and/or" keyword wherein in this implementation, represent and or two kinds of situations, in other words, the present invention is implemented
A and/or B mentioned by example, illustrate two kinds of A and B, A or B situations, describe three kinds of states present in A and B, such as A and/or
B, represent：Only including A does not include B；Only including B does not include A；Including A and B.
Meanwhile in the embodiment of the present invention, when component is referred to as " being fixed on " another component, it can be directly at another
On component or there may also be component placed in the middle.When a component is considered as " connection " another component, it can be direct
It is connected to another component or may be simultaneously present component placed in the middle.When a component is considered as " being arranged at " another group
Part, it can be set directly on another component or may be simultaneously present component placed in the middle.Made in the embodiment of the present invention
Term " vertically ", " horizontal ", "left", "right" and similar statement are merely for purposes of illustration, and are not intended to
The limitation present invention.
Multi-rotor unmanned aerial vehicle provided by the invention, its head by the first dismounting component it is detachable be fixed on fuselage
Bottom, instead of it is traditional it is direct head is fixed on fuselage, caused by head dismounting it is complicated, and must in unloading process
The technological deficiency that extraneous disassembling tool could be dismantled must be relied on.Meanwhile rotor power component is fixed on rotation in the present invention
On wing axle, rotor is arranged on rotor power component, thinks the powered rotation of rotor, and the rotor power component is at least
Adjusted including an electricity.This allows for electricity tune in the present invention and is directly fixed on fuselage periphery as the building block of rotor power component
Position, and because rotor is arranged on rotor power component, therefore electricity adjusts the connection line between rotor very short, greatly
Reduce electricity adjust and rotor between because exist circuit it is long caused by power attenuation, possess efficiently, energy-conservation the characteristics of.In order to right
Multi-rotor unmanned aerial vehicle provided by the invention elaborates, to support the technical problems to be solved by the invention, below, the present invention
In the embodiment of offer, the overall structure of unmanned plane is elaborated first, then during unmanned plane is described, enters one
Step targetedly draws multi-rotor unmanned aerial vehicle provided by the invention, to reach complete, clear, clear purpose.
Fig. 1-2,11,14 are referred to, the embodiments of the invention provide a kind of unmanned plane, including fuselage 1, rotor shaft 2, head
3, the first dismounting component 4, signal framing component 5 and rotor power component 6.
Wherein, the rotor shaft 2 is rotationally fixed on the fuselage 1 by its one end, with realize rotor shaft 2 relative to
Fuselage is foldable, then completes rotor shaft 2 and the expansion action or contractive action of fuselage.In embodiments of the present invention, rotor
The quantity of axle 2 can be 4, and 4 rotor shafts 2 are symmetrically distributed in four corner portions of fuselage 1.The fuselage 1
Inside be additionally provided with flight control system for controlling unmanned plane during flying.On the other end of rotor shaft 2, it is fixed with described
Rotor power component 6, and be connected with the flight control system set by the inside of fuselage 1, think the powered rotation of rotor, and
An electricity tune described above is comprised at least on the rotor power component 6.
Meanwhile the first dismounting component 4 is fixed on the fuselage 1, and by the described first dismounting component 4 by described in
Head 3 is detachable to be connected on the fuselage 1 so that the head 3 by described first dismounting component 4 can with it is described
Fuselage 1 is quick, flexibly dismounting, to form multi-rotor unmanned aerial vehicle of the present invention.Certainly, the first dismounting component 4 and the machine
The mode that is fixedly connected between body 1 can be diversified, such as can be bolt connection, can be mode connects for screw, Ke Yishi
Weld or be integrally formed, be not limited in this embodiment of the present invention, as long as can realize that the first dismounting component 4 is fixed
In the fuselage 1.
Further, the signal framing component 5 is fixed on the fuselage 1, and is set in the signal framing component 5
There is a locator 53.Certainly, locator 53 is mainly used in entering line position between unmanned plane and earth station in embodiments of the present invention
The transmission of confidence breath, to monitor position and the flight information of unmanned plane in real time by locator 53, for locator 53
Type, the embodiment of the present invention is not limited to, and can be navigational route type receiver, geodetic type receiver or time service type receiver
Deng.It should be understood that in the embodiment of the present invention, the locator 53 is arranged on institute by the signal framing component 6
State on fuselage 1, so allow for isolating the external air flow of locator 53 and the fuselage 1 by signal framing component 6；Have
Effect to avoid locator 53 directly exposed in external fuselage, external air flow during unmanned plane during flying, extraneous moisture or
Extraneous shelter locator 53 caused by either being rubbed with the Long Term Contact of locator 53 makes moist or damaged, and has security
Can be high the characteristics of.
Below, the building block of each several part of unmanned plane is elaborated.
For the above-mentioned first dismounting component 4,
Fig. 3-11 are referred to, wherein, the first dismounting component 4 comprises at least：Fixed plate 41 and positioning element 42.
Wherein, the fixed plate 41 is fixed on the fuselage 1, and is slidably connected with the head 3, so that the head
3 enter line slip relative to the fixed plate 41, and because fixed plate 41 is fixed relative to fuselage 1, so realize head 3 relative to
Fuselage 1 enters line slip.Certainly, the mode that is fixedly connected between fixed plate 41 and the fuselage 1 can be diversified, such as may be used
Be bolt connection, can be mode connects for screw, can be welding or be integrally formed, do not done in this embodiment of the present invention
Limitation, as long as can realize that fixed plate 41 is fixed on the fuselage 1.The positioning element 42 is fixed on the fixed plate 41
On, to be positioned to the head 3 relative to the position of the fixed plate 41, and then realize the head 3 relative to described
Fuselage is installed or dismounting.
Herein, equivalent to one screens part of positioning element 42, when needing head 3 being installed on fuselage 1, now
A certain position is slid into relative to fixed plate 41 between head 3 and fixed plate 41, then by positioning element 42 to the position
Head 3 is positioned, to prevent head 3 from being slided relative to fixed plate 41.And when needing to pull down head 3, now only need manually
Stir positioning element 42, it is allowed to which head 3 skids off relative to fixed plate 41, you can realize quick, the flexible dismounting of head 3.This mistake
Cheng Zhong, the installation and removal of head are easy to operate without any extraneous utensil such as spanner etc., have quick, easily special
Point.
In embodiments of the present invention, preferably, please continue to refer to Fig. 5-6, the fixed plate 42 can be that section is U-shaped
Shape, the fixed plate 42 under the shape can at least include：First side plate 411；Second side plate 412 and transverse slat 413.
Wherein, first side plate 411 and second side plate 412 are parallel；And first side plate 411 and described
Two side plates 412 and the transverse slat 413 are perpendicular, and the transverse slat 413 respectively with first side plate 411 and second side plate
412 are slidably connected, and the head 3 is fixedly connected with the transverse slat 413, and then pass through the transverse slat 413 phase of head 3
Enter line slip for first side plate 411 and second side plate 412.Meanwhile the positioning element 41 is individually fixed in institute
State on the first side plate 411 and second side plate 412, with to the transverse slat 413 relative to first side plate 411 and described
The position of two side plates 412 is positioned.Certainly, between first side plate 411, second side plate 412 and the fuselage 1
The mode of being fixedly connected can be diversified, such as can be bolt connection, can be mode connects for screw, can be welding, also may be used
To be to be integrally formed, it is not limited in this embodiment of the present invention, as long as first side plate 411, second side can be realized
Plate 412 is fixed on the fuselage 1.
Same principle, the mode that is fixedly connected between the head 3 and the transverse slat 413 can also be varied
, it such as can be bolt connection, can be mode connects for screw, can be welding or be integrally formed, the present invention is implemented herein
Example be not limited, as long as can realize that the head 3 is relatively fixed with the transverse slat 413, protection scope of the present invention it
It is interior.
Further, can be with the first side plate 411, the spirit of the second side plate 412 for ease of being fixed with the transverse slat 413 of head 3
Living, quickly slip, in order to which head 3 is flexible, quickly installation or dismounting.A kind of embodiment party as the embodiment of the present invention
A chute is respectively arranged with formula, first side plate 411 and second side plate 412, the transverse slat 413 is arranged on institute
State in chute so that the transverse slat 413 is entered by the chute relative to first side plate 411 and second side plate 412
Line slip.
Meanwhile through first side plate 411, second side plate 412 corresponding to one end of the positioning element 42, and
In the chute internal projection or contraction so that one end of the positioning element 42 relative to the chute in the chute convex
When rising, one end of the positioning element 42 stops that the transverse slat 413 enters line slip in the chute, the positioning element 42
Relative to the chute in the chute contract, one end of the positioning element 42 is separated with the transverse slat 413 for one end,
So that the transverse slat 413 enters line slip in the chute.
Need exist for explanation, in embodiments of the present invention, described " projection ", it can be understood as be a part
Slip into some part, " contraction " can be understood as a part and skid off some part.For example, described above is described
Relative to the chute in the chute internal projection, that is, the one end for referring to the positioning element 42 is slipped into for one end of positioning element 42
In the chute, one end of positioning element 42 described above relative to the chute in the chute contract, that is, refer to described in
One end of positioning element 42 skids off the chute.With this by positioning element 42 come realize head 3 relative to the dismounting of fuselage 1 or
Person installs.
For the positioning element 42, in embodiments of the present invention, as a kind of implementation of the present embodiment, institute
Stating positioning element 42 can comprise at least：First positioning plunger and the second positioning plunger.And the first positioning plunger bag
Include the first positioning end；The second positioning plunger includes the second positioning end.
Wherein, first side plate, and the chute in first side plate 411 are passed through corresponding to first positioning end
Internal projection or contraction, so that first positioning end is in the chute internal projection in relative to first side plate 411, it is described
First positioning end stops that the transverse slat 413 enters line slip in chute, and first positioning end is relative to first side plate
During chute contract in 411, first positioning end is separated with the transverse slat 413, so that the transverse slat 413 is in chute
Enter line slip.Wherein, second side plate 412 is passed through corresponding to second positioning end, and in second side plate 412
Chute internal projection or contraction, so that second positioning end is in the chute internal projection in relative to second side plate 412,
Second positioning end stops that the transverse slat 413 enters line slip in chute, and second positioning end is relative to described second
During chute contract in side plate 412, second positioning end is separated with the transverse slat, so that the transverse slat 413 is in chute
Inside enter line slip.
Herein, can be as shown in Fig. 5 or Fig. 6, it can be understood as the first side plate 411 and the second side plate 412 are symmetrical
The both sides of the transverse slat 413 are distributed in, so allow for inserting first side plate while both sides of the transverse slat 413 correspond to
411 and second side plate 412 chute that is opened up in, realize the transverse slat 413 for being fixed with head 3 relative to the first side with this
The side plate 412 of plate 411 and second enters line slip.Meanwhile in order to preferably be positioned to the transverse slat 413 in sliding process.This hair
Bright embodiment by the first positioning plunger and the second positioning plunger, symmetrically set in the both sides of transverse slat 413, namely first fixed
Position plunger is corresponding with the first side plate 411, and the second positioning plunger is corresponding with the second side plate 412.It should be noted that in this hair
In bright embodiment, the structure of the first side plate 411 and the second side plate 412 can with it is identical can also be different, the first positioning plunger
With the second positioning plunger can with it is identical can also be different.And in embodiments of the present invention, for convenience of description, selected
Side plate 411 is identical with the structure of the second side plate 412, and the structure of the first positioning plunger and the second positioning 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 positioning plunger and the
Two positioning plungers can also be mutually different various structures, and such as the first side plate 411 can be 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, if be that by the first side plate 411 and the second side plate 412 with
Fuselage 1 is relatively fixed, and transverse slat 413 can with the first side plate 411 and relative the first side plate 411 slided of the second side plate 412 and
The structure of second side plate 412, within protection scope of the present invention.Likewise, the first positioning plunger and the second positioning plunger
Can be a variety of different structures, as long as disclosure satisfy that the first positioning plunger corresponding can pass through the first side plate 411, second is fixed
Position plunger corresponding can pass through the second side plate 412, and progress is raised or flexible in its each comfortable corresponding chute, with to horizontal stroke
Plate 413 spacing to the greatest extent may be used.Whether identical it is placed in the planform of the first positioning plunger and the second positioning plunger, the present invention
Embodiment does not do further restriction.
Please continue to refer to Fig. 7-10, as stated above, a kind of embodiment as the embodiment of the present invention, it is assumed that at this
The first selected positioning plunger and the second positioning plunger are completely identical in structure in inventive embodiments, with shown in Fig. 7-10
Exemplified by first positioning plunger 421, to be described in further detail to the internal structure for positioning plunger.
Such as Fig. 7-10, the first positioning plunger 421 includes：First bolt 4211, the first positioning thread insert 4212,
One retaining spring 4213.
Wherein, first bolt 4211 is provided with the first positioning end 4211a；First positioning thread insert
4212 are set on first bolt 4211, and first positioning thread insert 4212 and first bolt 4211
Between be provided with one first compression stroke 4214.It can be understood as first positioning thread insert 4212 in embodiments of the present invention
Internal diameter is more than the external diameter of first bolt 4211, and so allowing for the first positioning thread insert 4212, to be set in described first fixed
When on the bolt 4211 of position, neutral region therebetween be present, this neutral region is above-mentioned first compression stroke 4214.It is described
First retaining spring is arranged in first compression stroke 4214；Wherein, the first positioning end 4211a sequentially passes through described
First retaining spring 4213, first compression stroke 4214 and first side plate 411, with first side plate 411
Chute internal projection or contraction.
It is noted that shown in Fig. 7-8 being the first positioning end 4211a in the chute in first side plate 411
Schematic diagram during contraction state.Shown in Fig. 9-10 is chute convexes of the first positioning end 4211a in first side plate 411
The schematic diagram during state of rising.And in order to preferably by the first retaining spring 4213 completely now in the first compression stroke 4214
It is interior, on the first positioning end 4211a of the first bolt 4211 described in the embodiment of the present invention, it is provided with one first card convex
4215, first retaining spring 4213 is fully defined in first compression stroke 4214, and cause described first
Positioning end 4211a compresses institute in the chute contract in relative to first side plate 411, by first card convex 4215
State the first retaining spring 4213.
Specifically, the embodiment of the present invention is during actual job, and the first retaining spring 4213 is in the first compression stroke
In 4214, whole process so allows in its natural state, the first retaining spring 4213 is the in compression or its pre-compressed state
The first positioning end 4211a is promoted to enter institute by the first side plate 411 by the elasticity tension of itself in one compression stroke 4214
In the chute for stating the first side plate 411, and then the transverse slat 413 in chute is positioned.And working as needs transverse slat 413 from cunning
When being skidded off in groove, namely when needing to dismantle head 3 from fuselage 1, the first bolt of manual toggle 4211 is now only needed,
So that the first positioning end 4211a compresses the first retaining spring 4213 by the first card convex 4215, then cause the first positioning end
4211a skids off out of the first side plate 411 chute, and then realizes being skidded off relative to the first side plate 411 for transverse slat 413.And work as nothing
After external force acts on the first bolt 4211, under the elasticity tension effect of the first retaining spring 4213, first is continued to press on
Positioning end 4211a carries out return, namely the working condition of the first positioning plunger 421 shown in Fig. 9 or Figure 10.It is effective to realize
The installation and removal of head are easy to operate without any extraneous utensil such as spanner etc., have the characteristics of quick, convenient.
In embodiments of the present invention, the second positioning plunger includes：Second bolt, second bolt are set
It is equipped with second positioning end；Second positioning thread insert, second positioning thread insert is set on second bolt, and institute
State and one second compression stroke is provided between the second positioning thread insert and second bolt；Second retaining spring, described
Two retaining springs are arranged in second compression stroke；Wherein, second positioning end sequentially passes through the second positioning bullet
Spring, second compression stroke and second side plate, with the chute internal projection in second side plate or contraction.It is described
On second positioning end of second bolt, one second card convex is provided with, second retaining spring is limited to institute
State in the second compression stroke, and second positioning end in the chute contract in relative to second side plate, is led to
Cross second card convex and compress second retaining spring.
As described above, the second positioning plunger in the embodiment of the present invention and the first positioning plunger 421 shown in Fig. 7-10
Structure is identical, and no longer the internal structure of the second positioning plunger is repeated herein, for the inside of the second positioning plunger
The non-detailed portion of structure, it see the detailed portion of the first positioning plunger 421 in the embodiment of the present invention.
Secondly, for fuselage 1 provided in an embodiment of the present invention,
Fig. 1-2 and 11-12 are see, fuselage 1 provided in an embodiment of the present invention has the characteristics of removable.So allow for
It is convenient, fast when again to the inside installing device of fuselage 1.Specifically, the fuselage 1 can at least include：Body 12, machine
Shell 11 and second dismantles component 13.
Wherein, the inside of the body 12 is in hollow-core construction；At least one installing port 121 is provided with the body 12；
The second dismounting component 13 is connected to the casing 11 is detachable on the body 12.Meanwhile first dismounting
Component 4 is fixed on the bottom of the body, and the signal framing component 5 is fixed on the body 12；So that in the machine
Part to be installed is placed into or is removed relative to the body 12 by the installing port in body 12.Preferably, this
The quantity of the second dismounting component 13 in inventive embodiments is at least 2, and 2 two dismountings components are symmetrically distributed
In the both sides of the casing 11, so that the connection between casing 11 and body 12 is more firm.
Further, Figure 12 is see, the second dismounting component 13 includes：Socket 131 and the 3rd positions plunger 132.
Wherein, the socket 131 is fixed on the body 12；The 3rd positioning plunger 132 is fixed on the casing 11, and institute
Stating the 3rd positioning plunger 132 includes the 3rd positioning end.So allow for the insertion socket 131 corresponding to the 3rd positioning end
In, by the casing 11 and the clamping of the body 12.
Herein it should be noted that socket 131 is for the part progress to insertion in the second dismounting component 13
The effect of screens, similar to keeper principle.The 3rd positioning plunger 132 is for insertion into socket in the second dismounting component 13
In 131, and then bridge is played a part of with body 12 to casing 11 and connected.Certainly, the 3rd positioning plunger in the embodiment of the present invention
132 structure can be diversified.
For example, can be as shown in figure 12, the 3rd positioning plunger 132 can include：1321 and the 3rd spacing spiral shell of locating dowel
Bolt 1322, the locating dowel 1321 are fixed on the casing 11, and the 3rd caging bolt 1322 is fixed on the positioning
On post 1321；3rd caging bolt 1322 is provided with the 3rd positioning end.And then socket is inserted by the 3rd positioning end
Casing 11 and body 12 are detachably connected in 131.As the quantity of the above-mentioned second dismounting component 13 is at least 2, and 2
The individual two dismountings component is symmetrically dispersed in the both sides of the casing 11.In specific implementation process, insertion one can be first matched
The 3rd caging bolt 1322 and socket 131 of side, then in the 3rd caging bolt 1322 and socket of corresponding matching opposite side
131.Certainly, in such a embodiment, casing 11 can also be made up of flexible material so that flexible spy is presented in casing 11
Sign, the both sides that casing 11 is so pinched by hand may be such that casing 11 prolongs the center portion thereof position and bent, casing 11 after bending
Corresponding body 12 of placing is fixed with the position of two sockets 131, loosens the casing 11 being pinched, such casing 11 is at itself
Elasticity tension effect under automatically restore to original state, the casing 11 in recovery process is due to being precisely to be placed on two the
Opening position corresponding to three caging bolts 1322 and two sockets 131, so allows for that the casing 11 after recovering is i.e. corresponding to be passed through
Two the 3rd caging bolts 1322 each in two sockets 131 of insertion, complete the quick connection with body 12.With convenient, fast
The characteristics of prompt.
For another example, the 3rd positioning plunger 132 in the embodiment of the present invention can also be the in the first dismounting component 4 as described above
The structure of one positioning plunger.I.e.：The 3rd positioning plunger 132 can include：Locating dowel 1321, the locating dowel 1321 are fixed
In on the casing 11；3rd bolt, the 3rd bolt are fixed in the locating dowel, the 3rd positioning spiral shell
Bolt is provided with the 3rd positioning end；3rd positioning thread insert, the 3rd positioning thread insert are set on the 3rd bolt,
And it is provided with one the 3rd compression stroke between the 3rd positioning thread insert and the 3rd bolt；3rd retaining spring, institute
The 3rd retaining spring is stated to be arranged in the 3rd compression stroke；Wherein, it is fixed to sequentially pass through the described 3rd for the 3rd positioning end
Position spring, the 3rd compression stroke are inserted in the socket.Further, the 3rd positioning of the 3rd bolt
On end, one the 3rd card convex is provided with, the 3rd retaining spring is limited in the 3rd compression stroke, and is caused described
When 3rd positioning end is separated with the socket, the 3rd retaining spring is compressed by the 3rd card convex.
In embodiments of the present invention, as the presently preferred embodiments, the 3rd caging bolt and/or the 3rd bolt
It is mutually perpendicular to the locating dowel.Being fixedly connected between the locating dowel and the casing is welding；And/or the positioning
Post and the casing are integrally formed.Between the locating dowel and the 3rd caging bolt and/or the 3rd bolt
It is welding to be fixedly connected；And/or the locating dowel and the 3rd caging bolt are integrally formed.
Again, for the signal framing component 5,
Figure 13-14 are referred to, the signal framing component 5 also includes：Locating rod 51 and spiral shell disk 52.
Wherein, the locating rod 51 includes a fixing end 511 and a support end 512, and the locating rod 51 passes through described solid
Fixed end 511 is fixed on the casing 11.The spiral shell disk 52 is fixed in the locating rod 51 by the support end 512, and
The inside of the spiral shell disk 52 is in hollow-core construction so that the locator 53 is fixed in the spiral shell disk 52.The locator 53 is logical
Cross locating rod 51 and spiral shell disk 52 is arranged on the fuselage 1, so allow for locator 53 and the fuselage 1 by spiral shell disk 52
External air flow be isolated；The effective locator 53 that avoids is directly exposed in external fuselage, outer during unmanned plane during flying
Either extraneous shelter locator 53 caused by with the Long Term Contact of locator 53 or friction makes moist for boundary's air-flow, extraneous moisture
Or damage, there is the characteristics of security performance is high.
Preferably, the locating rod 51 and the casing 11 are integrally formed；And/or the locating rod 5151 and described
Spiral shell disk 52 is integrally formed.
Certainly, for spiral shell disk 52, it is the equal of a protective cover of locator 53, for being carried out to locator 53
Protection, in embodiments of the present invention, the spiral shell disk 52 can comprise at least：First blind nut 521, first blind nut 521 are set
There is internal thread；Second blind nut 522, second blind nut 522 are provided with external screw thread, first blind nut 521 and second spiral shell
The threaded connection of lid 522 forms the spiral shell disk 52；Wherein, first blind nut 521 and second blind nut 522 can be with rounded
Shape or square shape, or diamond shaped, the embodiment of the present invention are not limited.It is noted that the He of locating rod 51
The angle formed between the casing 11 is an acute angle.That is, plane of the center vertical pivot of locating rod 51 where with casing 11
It is not mutually perpendicular to, and the inclined plane of locating rod 51 is with towards tail orientation, so also further reducing locating rod 51 in nothing
In man-machine flight course with the contact resistance of external air flow.
Again, for rotor power component 6, Figure 15-16 are referred to, the rotor power component 6 comprises at least：The
(it is electric that the first electric electricity tune of tune 64 and following second can be understood as heat radiating type to the electric tune 64 of one motor 61, refrigerating seat 63 and first
Adjust).The first rotor rotational that power is provided due to rotating to be unmanned plane during flying is fixed on first motor 61；It is described cold
But seat 63 is fixed in the rotor shaft 2, and first motor 61 is fixed on the refrigerating seat 63.In the embodiment of the present invention
In, the inside of refrigerating seat 63 is in hollow-core construction, and first electricity adjusts 64 inside for being fixed on the refrigerating seat 63, and respectively with
First motor 61 connects with the flight control system inside fuselage 1, to control institute by the flight control system
State the first electricity and adjust 64, realize and drive first motor 61 to drive first rotor to be rotated.
It should be strongly noted that the refrigerating seat 63 is provided with least one ventilating opening 631, by the refrigerating seat 63
Inner space communicated with free surrounding space.So allow for when the first electricity tune 64 is fixed on into the inside of refrigerating seat 63, in real time
Convection current is formed with the cold air of the periphery of refrigerating seat 63, to adjust 64 to be cooled down in real time the first electricity, is effectively avoided because of first
Electricity adjust 64 overheated scald and cause first electricity adjust 64 can not normal operation technological deficiency.Meanwhile the first electricity is adjusted 64 directly admittedly
Due to the peripheral position of fuselage 1, and due to the first rotor be arranged on refrigerating seat 63 on, therefore first electricity adjust 64 and first rotor it
Between connection line it is very short, significantly reduce first electricity adjust and the first rotor between because exist circuit it is long caused by work(
Rate is lost, and possesses the characteristics of efficient, energy-conservation.
Certainly, in embodiments of the present invention, Figure 19 is referred to, rotor power component 6 can also include the He of the second motor 62
Second electricity is adjusted, and second electricity is adjusted and is connected respectively with second motor 62 and the flight control system.At this point it is possible to manage
Solve includes the first stationary plane and the second stationary plane for the refrigerating seat 63, and first motor 61 is fixed on first stationary plane
On, second motor 62 is fixed on second stationary plane, to move second motor 63 by the described second electric transfer drive
The second rotor is driven to be rotated.Same with the first electric phase modulation, second electricity adjusts the inside for also being secured to the refrigerating seat 63.This
Sample is adjusted by 2 motors of setting shown in Figure 19 and 2 electricity, and then realizes the unmanned plane structure of coaxial double-oar.
In embodiments of the present invention, it can be identical structure that first the second electricity of electricity mediation, which is adjusted, and 64 are adjusted with the first electricity
Exemplified by, Figure 17-18 are referred to, it can at least include：First electric capacity 641, the heat sink 643 of first circuit board 642 and first.Its
In, the first circuit board 642 connects with first electric capacity 641, first motor 61 and the flight control system respectively
Connect, and first heat sink 643 is attached on the first circuit board 642.Preferably, first heat sink 643 can
To be aluminium sheet.So on the one hand, the first electricity tune 64 is carried out by convection in the ventilating opening 631 that refrigerating seat is opened up cold
But, further 64 are adjusted to radiate the first electricity simultaneously also by the first heat sink 643.Ensure that the first electricity adjusts 64 safety to reach
The technique effect of operation.
It is identical with the first electricity tune 64 for the second electricity is adjusted, it can also include：Second electric capacity；Second circuit board；And the
Two heat sinks；Wherein, the second circuit board respectively with second electric capacity, second motor and the flight control system
Connection, and second heat sink is attached on the second circuit board.Because in embodiments of the present invention, the second electricity is adjusted interior
Portion's structure is identical with the internal structure that the first electricity is adjusted, and here is omitted, the non-detailed portion of internal structure that the second electricity is adjusted,
The first electricity is referred to adjust.
Preferably, the first circuit board is between first electric capacity and first heat sink；And/or institute
Second circuit board is stated between second electric capacity and second heat sink.
Further, continuing with referring to Figure 20-21, for the annexation between the first motor 61 and the first rotor 8
For, the embodiment of the present invention additionally provides a kind of Quick-dismantle component, for the Quick Release connection between the first motor 61 and the first rotor.
Realize and carrying out the installation of the first rotor 8 or during dismantlement work, it is only necessary to by rotating first rotor 8, you can realize the
Fastening or separation between one rotor 8 and the first motor 61, namely can be complete without external operation instrument (such as handle)
Installation or dismantlement work into the first rotor 8, there is the characteristics of quick, portable and operating efficiency is high.
Specifically, Figure 20-21 are referred to, the first motor 61 includes first surface 611 and second surface in the present embodiment
612.In embodiment, first surface 611 can be understood as the upper surface of the first motor 61, and second surface 612 is appreciated that
To be the lower surface of the first motor 61, and first motor 61 is fixed on the refrigerating seat 63 by the first surface 611
On.Meanwhile first rotor 8 passes through the 611 detachable company of first surface of the Quick-dismantle component 7 and first motor 61
Connect.
During actual job, both the first rotor 8 and the first motor 61 are threadedly coupled by Quick-dismantle component 7.So that in reality
In the operation process of border when needing the first rotor to unmanned plane to be installed or dismantled, only need to rotate first rotation
The wing 8, such as turn clockwise the first rotor 8 or the first rotor of rotate counterclockwise 8, you can realizes first rotor 8 and described
Installation or removal between first motor 61.The first rotor 8 is directly fixed on by the first motor using bolt compared to traditional
On 61, when needing to dismantle the first rotor 8 from the first motor 61, or installing, it is both needed to turn spiral shell by extraneous handle
Bolt, the disassembly and installation work of the first rotor 8 can be completed.And due to for connecting consolidating for the first rotor 8 and the first motor 61
The individual component that bolt is individualism is determined, when turning bolt by handle and being unloaded, often due to execute-in-place environment
Complexity, easily cause the loss of fixing bolt, once and fixing bolt lose, then can not just complete the first rotor 8 and the
The installment work of one motor 61, that is, the serious consequence for causing flight equipment not fly.And the present embodiment, it is exactly based on using fast
Tear open component 7 by both the first rotor 8 and the first motor 61 be threadedly coupled so that the two in installation or dismounting, without
External operation instrument (such as handle), fast and conveniently, there is the characteristics of operating efficiency is high.
For Quick-dismantle component 7, comprised at least continuing with referring to Figure 21, the Quick-dismantle component 7：First screw 71, the second spiral shell
The dismounting nut 74 of the 72, first screw buckle of nail 73 and first.Wherein, the inwall of first screw buckle 73 is provided with the first internal thread
76, and the bottom of first screw buckle 73 offers the first screw 77 so that first screw 432 passes through first spiral shell
First screw buckle 73 is fixed on the first surface 611 of first motor 61 by hole 77.The first dismounting nut 74
Outer wall be provided with the first external screw thread 78 being adapted with first internal thread 76, and the top of the first dismounting nut 74
Offer the second screw 79 so that second screw 72 sequentially passes through first rotor 8, second screw 79 by described in
First dismounting nut 74 is fixed on first rotor 8.
Wherein, the first screw buckle 73 is fixed on by the first screw 71 on the first surface 611 of first motor 61, and first tears open
Removing nut 74 is fixed on the first rotor 8 by the second screw 72.And first screw buckle 73 inwall opened up first in spiral shell
Line 76, and the first external screw thread 78 for being opened up of outer wall of the first dismounting nut 74 match completely, namely the first internal thread 76 and the
Occlusion locking can be realized between one external screw thread 78.So allow for, when needing the first rotor 8 being arranged in rotor shaft 3,
Because the first motor 61 is fixed on the end of rotor shaft 3, also the first rotor 8 is arranged on the first motor 61.Now, it is only necessary to
It can be manually rotated the first rotor 8 so that the first external screw thread 78 is mutually engaged with the first internal thread 76, is continued to rotate, is then realized first
The locking of the screw buckle 73 of nut 74 and first is dismantled, because the first dismounting nut 74 is fixed on the first rotor 8, the first screw buckle
73 are fixed on the first motor 61, namely realize the locking installation of the first rotor 8 and the first motor 61 (rotor shaft 3).And work as
When needing dismounting, now only need to reversely rotate the first rotor 8, realize the separation of the first external screw thread 78 and the first internal thread 76 i.e.
Can.With it is swift to operate, facilitate the characteristics of.
It should be noted that unmanned plane, during practical flight, the direction of rotation of the first rotor 8 is rotate counterclockwise side
To, now, because the first rotor 8 is the rotating state that is in itself in flight course, and the first rotor 8 and the first motor
The connected mode fastened in itself and using rotation realization in embodiment between 61.For example, when the first rotor 8 is relative to first
Motor 61 is when being fastened therebetween by the realization that turns clockwise, because the normal of the first rotor 8 rotates to be in flight course
Counterclockwise, now as the normal rotation counterclockwise of the first rotor 8, namely the first rotor 8 have the inverse time equivalent to the first motor 61
The driving of pin rotation.And because the first rotor 8 relative to the first motor 61 could be realized therebetween by turning clockwise
Fastening, then otherwise when it is rotate counterclockwise the first rotor 8 occur relative to the first motor 61, i.e., it can cause the first rotor
8 and the first fastening relationships between motor 61 loosen, even result in the first rotor 8 and fly away from the first motor 61 and cause nobody
The phenomenon that machine crashes occurs.
Therefore, in order to avoid unmanned plane causes in flight course due to the normal rotate counterclockwise of the first rotor 8
Fastening relationships between one rotor 8 and the first motor 61 loosen, and the embodiment of the present invention is by the first rotor 8 and the first motor 61
Between rotate the direction that the direction tightened is also configured to rotate counterclockwise.That is, set by the outer wall of the first dismounting nut 74
The occlusion locking direction of the first internal thread 76 set by the inwall of first external screw thread 78 and the first screw buckle 73 is also counterclockwise
Direction.So allow for when the first rotor 8 is to realize to fasten therebetween by rotate counterclockwise relative to the first motor 61,
Because the normal of the first rotor 8 rotates to be counterclockwise in flight course, now as the counterclockwise of the first rotor 8 normally rotates,
Namely first rotor 8 also have the trend of rotate counterclockwise equivalent to the first motor 61.
And because the first rotor 8 could exactly be realized therebetween relative to the first motor 61 by rotate counterclockwise
Fastening, so on the one hand, be effectively prevented ought the first rotor 8 relative to the first motor 61 stung by the realization that turns clockwise
When closing locking, the fastening between the first rotor 8 and the first motor 61 is caused due to normal rotate to be counterclockwise of the first rotor 8
Relation loosens, and even results in the technological deficiency that the first rotor 8 flies away from the first motor 61 and causes unmanned plane to crash.The opposing party
Face, fastening therebetween could be realized relative to the first motor 4 itself and by rotate counterclockwise due to the first rotor 8,
Normally rotated when with the counterclockwise of the first rotor 8, and cause the first rotor 8 also to have rotate counterclockwise equivalent to the first motor 61
Trend, now just also increase the first rotor 8 and the first motor 61 fastening relationships therebetween, ensure that flight equipment
Normal safe flight, there is the characteristics of security performance is high.
Further, it is as described above continuing with referring to Figure 20-21, when sequentially passing through described by the second screw 72
When described first dismounting nut 74 is fixed on first rotor 8 by one rotor 8, second screw 79, due to unmanned plane
In flight course, the external resistance factor suffered by the first rotor 8 is more, such as air-flow, wind direction.This allows for flight course
In the first rotor 8 it is bigger relative to the vibrations of the first motor 61 and/or rotor shaft 3, however, prolonged vibrations can cause the
Annexation between two screws 72, the first rotor 8 and the first dismounting three of nut 74 is extremely unstable, or even causes the second screw
72 loosen, and then trigger security incident.Therefore, the present embodiment is by setting up the first vibration damping sheet 75, and in first vibration damping sheet
First through hole is opened up on 75, so that second screw 72 sequentially passes through the first through hole, the spiral shell of first rotor 8 and second
Described first dismounting nut 437 is fixed on first rotor 8 by hole 79.Preferably, the first vibration damping sheet 75 can be in disk
Shape, to increase the contact area of the first vibration damping sheet 75 and the upper surface of the first rotor 8, by the second screw 72 by the first vibration damping sheet 75
With the upper surface of the first rotor 8 relative to fastening, to reduce vibrations of first rotor 8 relative to the first motor 61, raising was flown
Safety and stability performance in journey.
Preferably, the quantity of first screw 71 is 2；The quantity of second screw 72 is 2；Described first
The quantity of screw 77 is 2；The quantity of second screw 79 is 2.Wherein, each described first screw 71 is corresponding one
First screw 77 so that each described first screw 71 passes through corresponding one first screw 77 by described first
Screw buckle 73 is fixed on first motor 61；Corresponding second screw 79 of each described second screw 72, makes
Obtain each described second screw 72 and first screw buckle 73 is fixed on institute through corresponding one second screw 79
State on the first motor 61.
Finally it should be noted that the present embodiment although merely illustrates the first motor and the first rotor passes through Quick-dismantle component
7 are attached so that its first rotor has the characteristics of fast quick-detach.But for multi-rotor unmanned aerial vehicle, described above
Between second rotor and the second motor, it can also be attached by Quick-dismantle component 7 so that the second rotor, which equally has, quickly to be torn open
The characteristics of unloading.Connected mode for the second motor and the second rotor by Quick-dismantle component, with the first motor and the first rotor it
Between exercise mode it is identical, here is omitted.
Although preferred embodiments of the present invention have been described, but those skilled in the art once know basic creation
Property concept, then can make other change and modification to these embodiments.So appended claims be intended to be construed to include it is excellent
Select embodiment and fall into having altered and changing for the scope of the invention.
Obviously, those skilled in the art can carry out the essence of various changes and modification without departing from the present invention to the present invention
God and scope.So, if these modifications and variations of the present invention belong to the scope of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to comprising including these changes and modification.
Claims (5)
1. a kind of multi-rotor unmanned aerial vehicle, wherein, unmanned plane includes fuselage, the first rotor, rotor shaft, head and flight control system
System, it is characterised in that the multi-rotor unmanned aerial vehicle includes：
First dismounting component, the first dismounting component are fixed on the fuselage；
Signal framing component, the signal framing component are fixed on the fuselage, and are provided with the signal framing component
For carrying out the locator of signal framing to unmanned plane；
Rotor power component, the rotor power component is fixed in the rotor shaft, and is connected with the flight control system,
Think the powered rotation of first rotor, and the rotor power component comprises at least an electricity and adjusted；
Quick-dismantle component, first rotor are rotationally fixed on the rotor power component by the Quick-dismantle component；
Wherein, the head is connected on the fuselage by the described first dismounting component so that the head passes through described
It is detachable between first dismounting component and the fuselage, and the locator is arranged on the machine by the signal framing component
With, the external air flow of the locator and the fuselage is isolated；
The first dismounting component includes：
Fixed plate, the fixed plate are fixed on the fuselage, and are slidably connected with the head so that the head relative to
The fixed plate enters line slip；
Positioning element, the positioning element are fixed in the fixed plate, with the position to the head relative to the fixed plate
Put and positioned, and then realize that the head is installed or dismantled relative to the fuselage；
The fixed plate includes：
First side plate；
Second side plate, first side plate and second side plate are parallel；
Transverse slat, first side plate and second side plate and the transverse slat are perpendicular, and the transverse slat is respectively with described first
Side plate and second side plate are slidably connected, and the head is fixedly connected with the transverse slat, and then pass through the transverse slat institute
State head and enter line slip relative to first side plate and second side plate；
The positioning element is individually fixed on first side plate and second side plate, with to the transverse slat relative to described
The position of first side plate and second side plate is positioned；
A chute is respectively arranged with first side plate and second side plate, the transverse slat is arranged on the chute
It is interior so that the transverse slat enters line slip by the chute relative to first side plate and second side plate；
Through first side plate, second side plate corresponding to one end of the positioning element, and in the chute internal projection
Or shrink so that one end of the positioning element relative to the chute in the chute internal projection, the positioning element
One end stop that the transverse slat enters line slip in the chute, one end of the positioning element is relative to the chute described
During chute contract, one end of the positioning element is separated with the transverse slat, so that the transverse slat is carried out in the chute
Slide；
The positioning element includes：
First positioning plunger, the first positioning plunger include the first positioning end；
Second positioning plunger, the second positioning plunger include the second positioning end；
Wherein, first side plate, and the chute internal projection in first side plate are passed through corresponding to first positioning end
Or shrink, so that first positioning end, in the chute internal projection in relative to first side plate, described first positions
End resistance keeps off the transverse slat and enters line slip in chute, and first positioning end is received in the chute in relative to first side plate
During contracting, first positioning end is separated with the transverse slat, so that the transverse slat enters line slip in chute；
Wherein, second side plate, and the chute internal projection in second side plate are passed through corresponding to second positioning end
Or shrink, so that second positioning end, in the chute internal projection in relative to second side plate, described second positions
End resistance keeps off the transverse slat and enters line slip in chute, and second positioning end is received in the chute in relative to second side plate
During contracting, second positioning end is separated with the transverse slat, so that the transverse slat enters line slip in chute,
The first positioning plunger includes：
First bolt, first bolt are provided with first positioning end；
First positioning thread insert, first positioning thread insert are set on first bolt, and first positioning thread insert
One first compression stroke is provided between first bolt；
First retaining spring, first retaining spring are arranged in first compression stroke；
Wherein, first positioning end sequentially passes through first retaining spring, first compression stroke and first side
Plate, with the chute internal projection in first side plate or contraction；
With,
The second positioning plunger includes：
Second bolt, second bolt are provided with second positioning end；
Second positioning thread insert, second positioning thread insert are set on second bolt, and second positioning thread insert
One second compression stroke is provided between second bolt；
Second retaining spring, second retaining spring are arranged in second compression stroke；
Wherein, second positioning end sequentially passes through second retaining spring, second compression stroke and second side
Plate, with the chute internal projection in second side plate or contraction.
2. multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that
On first positioning end of first bolt, one first card convex is provided with, by first retaining spring
It is limited in first compression stroke, and first positioning end is received in the chute in relative to first side plate
During contracting, first retaining spring is compressed by first card convex；
And/or
On second positioning end of second bolt, one second card convex is provided with, by second retaining spring
It is limited in second compression stroke, and second positioning end is received in the chute in relative to second side plate
During contracting, second retaining spring is compressed by second card convex.
3. multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that the signal framing component also includes：
Locating rod, the locating rod include a fixing end and a support end, and the locating rod is fixed on institute by the fixing end
State on fuselage；
Spiral shell disk, the spiral shell disk are fixed in the locating rod by the support end, and the inside of the spiral shell disk is in hollow-core construction,
So that the locator is fixed in the spiral shell disk.
4. multi-rotor unmanned aerial vehicle as claimed in claim 1, it is characterised in that the rotor power component includes：
First motor so that the first rotor rotational is fixed on first motor；
Refrigerating seat, the refrigerating seat are fixed in the rotor shaft, and first motor is fixed on the refrigerating seat；
First electricity is adjusted, and first electricity, which is adjusted, is fixed on the inside of the refrigerating seat, and respectively with first motor and described flying
Row control system connects, and is rotated with the first rotor described in moving first motor driven by the described first electric transfer drive；
Wherein, the refrigerating seat is provided with least one ventilating opening, by the inner space of the refrigerating seat and free surrounding space phase
It is logical.
5. multi-rotor unmanned aerial vehicle as claimed in claim 4, it is characterised in that first electricity, which is stealthily substituted, to be included：
First electric capacity；
First circuit board；And
First heat sink；
Wherein, the first circuit board is connected with first electric capacity, first motor and the flight control system respectively,
And first heat sink is attached on the first circuit board.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610283293.8A CN105818997B (en) | 2016-04-29 | 2016-04-29 | Multi-rotor unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610283293.8A CN105818997B (en) | 2016-04-29 | 2016-04-29 | Multi-rotor unmanned aerial vehicle |
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| CN105818997A CN105818997A (en) | 2016-08-03 |
| CN105818997B true CN105818997B (en) | 2018-03-27 |
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| CN201610283293.8A Expired - Fee Related CN105818997B (en) | 2016-04-29 | 2016-04-29 | Multi-rotor unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203301847U (en) * | 2013-04-27 | 2013-11-20 | 湖北易瓦特科技有限公司 | Heat radiation circuit board for unmanned plane |
| CN105151286A (en) * | 2015-08-27 | 2015-12-16 | 蔡强 | Module combined type manufacturing method for four-axis aircraft and four-axis aircraft |
| CN204916154U (en) * | 2015-07-10 | 2015-12-30 | 哈瓦国际航空技术（深圳）有限公司 | Integration aircraft organism |
| CN205010500U (en) * | 2015-08-10 | 2016-02-03 | 普宙飞行器科技（深圳）有限公司 | Unmanned vehicles's cloud platform quick detach device |
| CN105366041A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Multi-rotor structure applied in unmanned aerial vehicle |
| CN205707408U (en) * | 2016-04-29 | 2016-11-23 | 易瓦特科技股份公司 | Many rotor wing unmanned aerial vehicles |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SG194241A1 (en) * | 2012-04-11 | 2013-11-29 | Singapore Tech Aerospace Ltd | A rotor-arm assembly and a multi-rotorcraft |
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2016
- 2016-04-29 CN CN201610283293.8A patent/CN105818997B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203301847U (en) * | 2013-04-27 | 2013-11-20 | 湖北易瓦特科技有限公司 | Heat radiation circuit board for unmanned plane |
| CN204916154U (en) * | 2015-07-10 | 2015-12-30 | 哈瓦国际航空技术（深圳）有限公司 | Integration aircraft organism |
| CN205010500U (en) * | 2015-08-10 | 2016-02-03 | 普宙飞行器科技（深圳）有限公司 | Unmanned vehicles's cloud platform quick detach device |
| CN105151286A (en) * | 2015-08-27 | 2015-12-16 | 蔡强 | Module combined type manufacturing method for four-axis aircraft and four-axis aircraft |
| CN105366041A (en) * | 2015-11-30 | 2016-03-02 | 湖北易瓦特科技股份有限公司 | Multi-rotor structure applied in unmanned aerial vehicle |
| CN205707408U (en) * | 2016-04-29 | 2016-11-23 | 易瓦特科技股份公司 | Many rotor wing unmanned aerial vehicles |
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| CN105818997A (en) | 2016-08-03 |
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