CN105818974B - Unmanned plane with detachable rotor structure - Google Patents
Unmanned plane with detachable rotor structure Download PDFInfo
- Publication number
- CN105818974B CN105818974B CN201610280566.3A CN201610280566A CN105818974B CN 105818974 B CN105818974 B CN 105818974B CN 201610280566 A CN201610280566 A CN 201610280566A CN 105818974 B CN105818974 B CN 105818974B
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- 230000005611 electricity Effects 0.000 claims description 45
- 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 11
- 238000010276 construction Methods 0.000 claims description 5
- 238000000926 separation method Methods 0.000 claims description 4
- 238000009423 ventilation Methods 0.000 claims description 4
- 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
- 238000000034 method Methods 0.000 abstract description 8
- 230000007812 deficiency Effects 0.000 abstract description 5
- 230000006835 compression Effects 0.000 description 17
- 238000007906 compression Methods 0.000 description 17
- 238000010586 diagram Methods 0.000 description 14
- 238000009432 framing Methods 0.000 description 10
- 230000008602 contraction Effects 0.000 description 9
- 238000003466 welding Methods 0.000 description 6
- 238000013016 damping Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 5
- 238000005516 engineering process Methods 0.000 description 5
- 230000004048 modification Effects 0.000 description 5
- 238000012986 modification Methods 0.000 description 5
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 229910003460 diamond Inorganic materials 0.000 description 2
- 239000010432 diamond Substances 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
- 239000007787 solid Substances 0.000 description 2
- 241000826860 Trapezium Species 0.000 description 1
- 230000001154 acute effect Effects 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000001595 contractor effect Effects 0.000 description 1
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Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- 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
- B64D47/08—Arrangements of cameras
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Transmission Devices (AREA)
- Connection Of Plates (AREA)
Abstract
The invention discloses a kind of unmanned planes with detachable rotor structure, belong to air vehicle technique field, including：First rotor；Second rotor；Two Quick-dismantle components；Rotor power component, is fixed in rotor shaft, and the first rotor is rotationally fixed to by a Quick-dismantle component on rotor power component, and the second rotor is rotationally fixed to by another Quick-dismantle component on rotor power component；And first rotor diameter be more than the second rotor diameter；Fuselage；First dismounting component, is fixed on body, and be slidably connected with holder.The present invention solves the technological deficiency that multi-rotor unmanned aerial vehicle flight efficiency is low in the prior art.
Description
Technical field
The invention belongs to air vehicle technique field, more particularly to a kind of unmanned plane with detachable rotor structure.
Background technology
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft.Without cockpit 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, passed into line trace, positioning, remote control, telemetering and number to it
It is defeated.It can take off as conventional airplane under wireless remotecontrol or be launched with booster rocket, can also be taken to by machine tool in the air
Launch flight.
Unmanned plane in the prior art, including fuselage, rotor shaft, one end end of rotor shaft are another for fixing rotor
End end is fixed on fuselage, to provide lift by the rotation of rotor for the flight of unmanned plane.But in the prior art
In, for the multi-rotor unmanned aerial vehicle of coaxial double-oar, often diameter, shape are identical for coaxial two rotors, and position
In the both sides up and down of rotor shaft, and the rotor above rotor shaft needs the air-flow for relying on its lower surface when rotation
Upward thrust is generated to the rotor, is then realized to the whole upward lift of unmanned plane.Obviously, the air-flow flowing of lower surface
Area is bigger, then generates that upward thrust is bigger to the rotor, then realizes that integrally upward lift is also more to unmanned plane
Greatly.And exactly since two coaxial rotor sizes are identical, this allows for the rotor of top and the rotor of lower section is rotating
During, the rotor of lower section blocks most of gas of top rotor lower surface due to the spatial area occupied by its own
Flow area is flowed, it is then whole to reduce the upward lift of unmanned plane, cause flight efficiency low.
Invention content
The present invention provides a kind of unmanned plane with detachable rotor structure, solves or part solves in the prior art
The low technological deficiency of multi-rotor unmanned aerial vehicle flight efficiency.
The present invention provides a kind of unmanned planes with detachable rotor structure to solve above-mentioned technical problem, wherein nothing
Man-machine includes rotor shaft, flight control system and holder, and the unmanned plane with detachable rotor structure includes：First rotation
The wing；Second rotor；Two Quick-dismantle components；Rotor power component, the rotor power component are fixed in the rotor shaft, and with
The flight control system connection, with the powered rotation for first rotor and second rotor；And described first
Rotor is rotationally fixed to by a Quick-dismantle component on the rotor power component so that first rotor is relative to described
Rotor shaft is rotatable；Second rotor is rotationally fixed to by another Quick-dismantle component on the rotor power component, is made
It is rotatable relative to the rotor shaft to obtain second rotor；And the diameter of first rotor is more than the straight of second rotor
Diameter, fuselage, the fuselage include：Casing；Body, the inside of the body are in hollow-core construction, and be provided on the body to
A few installing port；Second dismounting component, it is described second dismounting component by the casing it is detachable be connected to the body
On, and the installing port is closed by the cabinet cover；Wherein, component to be installed in the body passes through the installing port phase
The body is placed into or is removed；First dismounting component, the first dismounting component are fixed on the body, and
It is slidably connected with the holder, so that the holder can be slided relative to the first dismounting component or the body；
Wherein, it dismantles component by described first the holder is connected on the body so that the holder passes through described first
It dismantles detachable between component and the body.
Optionally, the rotor power component includes：Refrigerating seat, the refrigerating seat include that the first stationary plane and second are fixed
Face, first stationary plane and second stationary plane horizontal axis centered on the rotor shaft, is symmetrically dispersed in the rotor
The both sides of axis；First motor, the first motor are fixed on first stationary plane, and first rotor is made to pass through one soon
Tear open component rotation be fixed in the first motor；Second motor, second motor are fixed on second stationary plane,
Make what second rotor passed through that another Quick-dismantle component rotates to be fixed on second motor；First electricity is adjusted, and described first
Electricity, which is adjusted, is fixed on the inside of the refrigerating seat, and respectively with the flight control system inside the first motor and the unmanned plane
Connection drives first rotor to be rotated to move the first motor by the described first electric transfer drive；Second electricity is adjusted, described
Second electricity adjusts the inside for being fixed on the refrigerating seat, and is controlled respectively with the flight inside the first motor and the unmanned plane
System connects, and drives second rotor to be rotated to move second motor by the described second electric transfer drive.
Optionally, the refrigerating seat is provided at least one ventilation opening, by the inner space of the refrigerating seat and the external world
Space communicates.
Optionally, first electricity, which is stealthily substituted, includes：First capacitance, first circuit board and the first heat sink；Wherein, described first
Circuit board is connect with first capacitance, the first motor and the flight control system respectively, and first heat sink
It is attached on the first circuit board；With second electricity, which is stealthily substituted, to be included：Second capacitance, second circuit board and the second heat sink；Its
In, the second circuit board is connect with second capacitance, second motor and the flight control system respectively, and described
Second heat sink is attached on the second circuit board.
Optionally, first heat sink and/or second heat sink are aluminium sheets.
Optionally, the first circuit board is between first capacitance and first heat sink；And/or it is described
Second circuit board is between second capacitance and second heat sink.
Optionally, the Quick-dismantle component includes：First screw；Second screw；First screw buckle, first screw buckle
Inner wall is provided with the first internal thread, and the bottom of first screw buckle offers the first screw hole so that first screw is worn
It crosses first screw hole first screw buckle is fixed in the first motor or second motor；First dismounting spiral shell
The outer wall of mother, the first dismounting nut are provided with the first external screw thread, and offer second at the top of the first dismounting nut
Screw hole so that second screw sequentially passes through first rotor, the second screw hole dismantles nut by described first and is fixed on institute
It states on the first rotor, or so that second screw sequentially passes through second rotor, the second screw hole is dismantled described first
Nut is fixed on second rotor；Wherein, first internal thread is adapted with first external screw thread, and by described
Occlusion or separation between first internal thread and first external screw thread, it is corresponding to realize first rotor and described first
Installation or dismounting between motor or between second rotor and second motor.
Optionally, the quantity of first screw is 2；The quantity of second screw is 2；First screw hole
Quantity is 2；The quantity of second screw hole is 2；Wherein, each described first screw corresponds to first spiral shell
Hole so that it is described that each described first screw passes through corresponding one first screw hole to be fixed on first screw buckle
In first motor or second motor；Each described second screw corresponds to second screw hole so that each
Second screw pass through corresponding one second screw hole by first screw buckle be fixed on the first motor or
On second motor.
Optionally, in the vertical direction, first rotor is located at the top of second rotor.
Optionally, the first dismounting component includes：Fixed plate, the fixed plate are fixed on the body, and with institute
It states holder to be slidably connected, so that the holder is slided relative to the fixed plate；Positioning element, the positioning element are fixed
It in the fixed plate, is positioned with the position to the holder relative to the fixed plate, and then realizes the holder phase
The body is installed or is dismantled.
Unmanned plane provided by the invention with detachable rotor structure, the first rotor and the second rotor are corresponding by fast
It tears component open to be fixed on rotor power component, and rotor power component is fixed in rotor shaft, the diameter of the first rotor is more than the
The diameter of two rotors, the whole size for realizing the first rotor are more than the whole size of the second rotor, this allows for the first rotor
During being rotated at the same time with the second rotor, the second rotor is greatly reduced due to its own existing spatial area, right
The obstruction of the air-flow flow area of first its lower surface of rotor ensure that the air-flow of first its lower surface of rotor produces the rotor
Raw upward thrust size then also avoids the unmanned plane technology that lift reduces and influences its flight efficiency whole upwards and lacks
It falls into.Have the characteristics that flight efficiency is high.
Description of the drawings
It in order to more clearly explain the embodiment of the invention or the technical proposal in the existing technology, below will be to institute in embodiment
Attached drawing to be used is needed to be briefly described, it should be apparent that, the accompanying drawings in the following description is only some implementations of the present invention
Example, for those of ordinary skill in the art, without creative efforts, can also obtain according to these attached drawings
Obtain other attached 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 connection relation overall structure diagram of the first dismounting component and holder in the unmanned plane that Fig. 1 is provided；
Fig. 4 is the connection relation overall structure side view of the first dismounting component and holder 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 that first positioning plunger is in the sectional view 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 that first positioning plunger is in the sectional view under raised position in unmanned plane provided in an embodiment of the present invention；
Figure 10 is that first positioning plunger is in the overall structure 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 connection relationship diagram of first motor provided in an embodiment of the present invention, refrigerating seat and rotor shaft three；
Figure 16 is the connection relation sectional view of first motor provided in an embodiment of the present invention, refrigerating seat and rotor shaft three；
Figure 17 is the overall structure diagram that the first electricity provided in an embodiment of the present invention is adjusted；
Figure 18 is the side view that the first electricity provided in an embodiment of the present invention is adjusted；
Figure 19 is first motor provided in an embodiment of the present invention, the connection relation of the second motor, refrigerating seat, 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；
Figure 22 is the overall structure diagram of another unmanned plane provided in an embodiment of the present invention；
Figure 23 is the connection relationship diagram of the first rotor and the second rotor in Figure 22.
Specific implementation mode
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation describes, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the 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
Range；Involved "and/or" keyword wherein in this implementation, indicate 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 is indicated：It includes B to only include A not；It includes A to only include B not；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 components 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 set to " another group
Part, it can be set up 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.
Unmanned plane provided by the invention with detachable rotor structure, the first rotor and the second rotor are corresponding by fast
It tears component open to be fixed on rotor power component, and rotor power component is fixed in rotor shaft, the diameter of the first rotor is more than the
The diameter of two rotors, the whole size for realizing the first rotor are more than the whole size of the second rotor, this allows for the first rotor
During being rotated at the same time with the second rotor, the second rotor is greatly reduced due to its own existing spatial area, right
The obstruction of the air-flow flow area of first its lower surface of rotor ensure that the air-flow of first its lower surface of rotor produces the rotor
Raw upward thrust size then also avoids the unmanned plane technology that lift reduces and influences its flight efficiency whole upwards and lacks
It falls into.Have the characteristics that flight efficiency is high.In order to be done specifically to the unmanned plane provided by the invention with detachable rotor structure
It is bright, to support the technical problems to be solved by the invention, in the following, in embodiment provided by the invention, first to the whole of unmanned plane
Body structure elaborates, and then during describing unmanned plane, further targetedly draws tool provided by the invention
The unmanned plane for having detachable rotor structure, it is complete, clear, clear to achieve the purpose that.
Fig. 1-2,11,14 are referred to, an embodiment of the present invention provides a kind of unmanned planes, including fuselage 1, rotor shaft 2, holder
3, the first dismounting component 4, signal framing component 5 and rotor power component 6.
Wherein, the rotor shaft 2 is rotationally fixed to by one end on the fuselage 1, with realize rotor shaft 2 relative to
Fuselage is foldable, then completes the expansion action or contractive action of rotor shaft 2 and fuselage.In embodiments of the present invention, rotor
The quantity of axis 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 the 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 connect with the flight control system set by 1 inside of fuselage, with the powered rotation for rotor, and
An electricity described above is included at least on the rotor power component 6 to adjust.
Meanwhile the first dismounting component 4 is fixed on the fuselage 1, and dismantling component 4 by described first will be described
Holder 3 is detachable to be connected on the fuselage 1 so that the holder 3 by it is described first dismantle component 4 can with it is described
Fuselage 1 quickly, is flexibly dismantled, to constitute double paddle structures of the present invention applied to unmanned plane.Certainly, the first dismounting component
The mode that is fixedly connected between 4 and the fuselage 1 can be diversified, such as can be bolted, can be screw connect
It connects, can be welding, can also be to be integrally formed, be not limited in this embodiment of the present invention, as long as the first dismounting can be realized
Component 4 is fixed on the fuselage 1.
Further, the signal framing component 5 is fixed on the fuselage 1, and setting in the signal framing component 5
There are one locators 53.Certainly, locator 53 is mainly used between unmanned plane and earth station in embodiments of the present invention into line position
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 by the signal framing component 6 in institute
It states on fuselage 1, allows for isolating locator 53 and the external air flow of the fuselage 1 by signal framing component 6 in this way；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 rubbing with 53 Long Term Contact of locator makes moist or damages, and has safety
The high feature of energy.
In the following, being elaborated to the building block of each section of unmanned plane.
Firstly, for it is above-mentioned first dismounting component 4 for, please refer to Fig. 3-11, wherein it is described first dismounting component 4 to
Include less：Fixed plate 41 and positioning element 42.
Wherein, the fixed plate 41 is fixed on the fuselage 1, and is slidably connected with the holder 3, so that the holder
3 are slided relative to the fixed plate 41, and due to fixed plate 41 relative to fuselage 1 fix, and then realize holder 3 relative to
Fuselage 1 is slided.Certainly, the mode that is fixedly connected between fixed plate 41 and the fuselage 1 can be diversified, such as may be used
Be bolted, can be screw connection, can be welding, can also 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, it is positioned with the position to the holder 3 relative to the fixed plate 41, and then realize the holder 3 relative to described
Fuselage is installed or dismounting.
Herein, positioning element 42 is equivalent to a screens component, when needing holder 3 being installed on fuselage 1, at this time
A certain position is slid into relative to fixed plate 41 between holder 3 and fixed plate 41, then by positioning element 42 to the position
Holder 3 is positioned, to prevent holder 3 from being slided relative to fixed plate 41.And when needing to remove holder 3, it only needs at this time manually
Positioning element 42 is stirred, holder 3 is allowed to be skidded off relative to fixed plate 41, you can realizes quick, the flexible dismounting of holder 3.This mistake
Cheng Zhong, the installation and removal of holder are easy to operate without any extraneous utensil such as spanner etc., have quickly, it is 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 at least may include：First side plate 411；Second side plate 412 and transverse slat 413.Its
In, first side plate 411 and second side plate 412 are parallel；And first side plate 411 and second side plate 412
It is perpendicular with the transverse slat 413, and the transverse slat 413 connects with first side plate 411 and second side plate 412 sliding respectively
It connects, the holder 3 is fixedly connected with the transverse slat 413, and then by the transverse slat 413 so that the holder 3 is relative to described
First side plate 411 and second side plate 412 are slided.Meanwhile the positioning element 41 is individually fixed in first side
On plate 411 and second side plate 412, with to the transverse slat 413 relative to first side plate 411 and second side plate
412 position is positioned.Certainly, the fixed company between first side plate 411, second side plate 412 and the fuselage 1
The mode of connecing can be diversified, such as can be bolted, can be screw connection, can be welding, can also be one
It is body formed, it is not limited in this embodiment of the present invention, as long as can realize that first side plate 411, second side plate 412 are solid
Due to the fuselage 1.
Same principle, the mode that is fixedly connected between the holder 3 and the transverse slat 413 can also be varied
, such as can be bolted, can be screw connection, can be welding, can also be integrally formed, herein the present invention implement
Example be not limited, as long as can realize that the holder 3 is relatively fixed with the transverse slat 413, protection scope of the present invention it
It is interior.
It further, can be with the first side plate 411,412 spirit of the second side plate for ease of being fixed with the transverse slat 413 of holder 3
Living, quickly sliding, in order to which holder 3 is flexible, quickly installation or dismounting.A kind of embodiment party as the embodiment of the present invention
It is respectively arranged with a sliding slot on formula, first side plate 411 and second side plate 412, the transverse slat 413 is arranged in institute
State in sliding slot so that the transverse slat 413 by the sliding slot relative to first side plate 411 and second side plate 412 into
Row sliding.
Meanwhile the positioning element 42 one end it is corresponding pass through first side plate 411, second side plate 412, and
In the sliding slot internal projection or contraction so that one end of the positioning element 42 relative to the sliding slot in the sliding slot convex
When rising, one end of the positioning element 42 stops that the transverse slat 413 is slided in the sliding slot, the positioning element 42
Relative to the sliding slot in the sliding slot contract, one end of the positioning element 42 is separated with the transverse slat 413 for one end,
So that the transverse slat 413 is slided in the sliding slot.
What needs to be explained here is that in embodiments of the present invention, it is described " protrusion ", it can be understood as to be a component
It slides into some component, " contraction " can be understood as a component and skid off some component.For example, described above is described
Relative to the sliding slot in the sliding slot internal projection, that is, the one end for referring to the positioning element 42 slides into for one end of positioning element 42
In the sliding slot, one end of positioning element 42 described above relative to the sliding slot in the sliding slot contract, that is, refer to described in
One end of positioning element 42 skids off the sliding slot.With this by positioning element 42 come realize holder 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 realization method of the present embodiment, institute
Stating positioning element 42 can include at least：First positioning plunger and the second positioning plunger.And the first positioning plunger packet
Include the first positioning end；The second positioning plunger includes the second positioning end.
Wherein, first positioning end is corresponding passes through first side plate, and the sliding slot in first side plate 411
Internal projection or contraction, so that first positioning end is when relative to sliding slot internal projection in first side plate 411, it is described
First positioning end stops that the transverse slat 413 is slided in sliding slot, and first positioning end is relative to first side plate
When sliding slot contract in 411, first positioning end is separated with the transverse slat 413, so that the transverse slat 413 is in sliding slot
It is slided.Wherein, second positioning end is corresponding passes through second side plate 412, and in second side plate 412
Sliding slot internal projection or contraction, so that second positioning end is when relative to sliding slot internal projection in second side plate 412,
Second positioning end stops that the transverse slat 413 is slided in sliding slot, and second positioning end is relative to described second
When sliding slot contract in side plate 412, second positioning end is separated with the transverse slat, so that the transverse slat 413 is in sliding slot
Inside slided.
It 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, allow for being inserted into first side plate while both sides of the transverse slat 413 correspond in this way
411 and second side plate 412 sliding slot that is opened up in, realize the transverse slat 413 for being fixed with holder 3 relative to the first side with this
Plate 411 and the second side plate 412 are slided.Meanwhile in order to preferably be positioned to the transverse slat 413 in sliding process.This hair
For bright embodiment by the first positioning plunger and the second positioning plunger, what is be symmetrically arranged is fixed in the both sides of transverse slat 413 namely first
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 first side plate 411 identical can also be different with the structure of the second side plate 412, the first positioning plunger
It identical can also be different with the second positioning plunger.And in embodiments of the present invention, for convenience of description, selected
Side plate 411 is identical with 412 structure of the second side plate, 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 either the first side plate 411 can be the second side plate of trapezium structure 412 can be square or
The polygonized structures such as rectangle or diamond shape.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 of the first side plate 411 and the opposite sliding of the second side plate 412 and
Second side plate, 412 structure, 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 carry out protrusion or flexible in its each comfortable corresponding sliding slot, with to cross
Plate 413, which is limited, to the greatest extent may be used.Whether the planform for being placed in the first positioning plunger and the second positioning plunger is identical, the present invention
Embodiment does not further limit.
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, shown in Fig. 7-10
For 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 positioning bolt 4211, the first positioning thread insert 4212,
One retaining spring 4213.Wherein, first positioning bolt 4211 is provided with the first positioning end 4211a；Described first is fixed
Position swivel nut 4212 is set on first positioning bolt 4211, and first positioning thread insert 4212 and the first positioning spiral shell
One first compression stroke 4214 is provided between bolt 4211.It can be understood as first positioning thread insert in embodiments of the present invention
4212 internal diameter is more than the outer diameter of first positioning bolt 4211, allow in this way the first positioning thread insert 4212 be set in it is described
When on the first positioning bolt 4211, there is neutral gear region therebetween, this neutral gear region is above-mentioned first compression stroke
4214.First retaining spring is set in first compression stroke 4214；Wherein, the first positioning end 4211a according to
It is secondary to pass through first retaining spring 4213, first compression stroke 4214 and first side plate 411, with described first
Sliding slot internal projection in side plate 411 or contraction.
It is noted that being the first positioning end 4211a shown in Fig. 7-8 in the sliding slot in first side plate 411
Schematic diagram when contraction state.It is sliding slot convexes of the first positioning end 4211a in first side plate 411 shown in Fig. 9-10
The schematic diagram when 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 positioning 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 make described first
Positioning end 4211a passes through first card convex 4215 and compresses institute when relative to sliding slot contract in first side plate 411
State the first retaining spring 4213.
Specifically, for the embodiment of the present invention during actual job, the first retaining spring 4213 is in the first compression stroke
In 4214, whole process allows in its natural state in this way in compression or pre-compressed state, and the first retaining spring 4213 is the
The first positioning end 4211a is pushed to enter institute by the first side plate 411 by the elasticity tension of itself in one compression stroke 4214
In the sliding slot for stating the first side plate 411, and then the transverse slat 413 in sliding slot is positioned.And works as and need transverse slat 413 from cunning
When being skidded off in slot, namely when needing to dismantle holder 3 from fuselage 1, the first positioning bolt of manual toggle 4211 is only needed at this time,
So that the first positioning end 4211a compresses the first retaining spring 4213 by the first card convex 4215, then so that the first positioning end
4211a is skidded off out of the first side plate 411 sliding slot, 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 positioning bolt 4211, under the elasticity tension effect of the first retaining spring 4213, first is continued to press on
Positioning end 4211a carries out the working condition of return namely Fig. 9 or the first positioning plunger 421 shown in Fig. 10.It is effective to realize
The installation and removal of holder are without any extraneous utensil such as spanner etc., and easy to operate, it is quick, convenient to have the characteristics that.
In embodiments of the present invention, the second positioning plunger includes：Second positioning bolt, second positioning bolt are set
It is equipped with second positioning end；Second positioning thread insert, second positioning thread insert is set on second positioning bolt, and institute
It states and is provided with one second compression stroke between the second positioning thread insert and second positioning bolt；Second retaining spring, described
Two retaining springs are set in second compression stroke；Wherein, second positioning end sequentially passes through the second positioning bullet
Spring, second compression stroke and second side plate, in second side plate sliding slot internal projection or contraction.It is described
On second positioning end of second positioning bolt, it is provided with one second card convex, second retaining spring is limited to institute
It states in the second compression stroke, and makes second positioning end when relative to sliding slot contract in second side plate, lead to
It crosses second card convex and compresses 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, no longer repeats herein the internal structure of the second positioning plunger, for the inside of the second positioning plunger
The non-detailed portion of structure sees 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, the embodiment of the present invention are seen
The fuselage 1 of offer has the characteristics that removable.It is convenient, fast when allowing for inside installing device to fuselage 1 again in this way.Tool
For body, the fuselage 1 at least may include：Body 12, casing 11 and second dismantle component 13.Wherein, the body 12
Inside is in hollow-core construction；At least one installing port 121 is provided on the body 12；Described second dismantles component 13 by the machine
Shell 11 is detachable to be connected on the body 12.Meanwhile the 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 component to be installed in the body 12 is described in
Installing port is placed into or is removed relative to the body 12.Preferably, second dismounting in the embodiment of the present invention
The quantity of component 13 is at least 2, and 2 two dismountings components are symmetrically dispersed in the both sides of the casing 11, so as to machine
Connection between shell 11 and body 12 is more secured.
Further, Figure 12 is seen, the second dismounting component 13 includes：Socket 131 and third position plunger 132.
Wherein, the socket 131 is fixed on the body 12；The third positioning plunger 132 is fixed on the casing 11, and institute
It includes third positioning end to state third positioning plunger 132.Allow for that the third positioning end is corresponding to be inserted into the socket 131 in this way
In, the casing 11 and the body 12 are clamped.
Herein it should be noted that socket 131 is for the component progress to insertion in the second dismounting component 13
The effect of screens is similar to keeper principle.Third positioning plunger 132 is for insertion into socket in the second dismounting component 13
In 131, and then plays the role of bridge with body 12 to casing 11 and connect.Certainly, third positions plunger in the embodiment of the present invention
132 structure can be diversified.
For example, can be as shown in figure 12, the third positioning plunger 132 may include：Positioning column 1321 and third limit spiral shell
Bolt 1322, the positioning column 1321 are fixed on the casing 11, and the third caging bolt 1322 is fixed on the positioning
On column 1321；The third caging bolt 1322 is provided with the third positioning end.And then socket is inserted by third positioning end
Casing 11 and body 12 are detachably connected in 131.As the quantity of above-mentioned second dismounting component 13 is at least 2, and 2
A 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 third caging bolt 1322 and socket 131 of side, then in the third caging bolt 1322 and socket of the corresponding matching other side
131.Certainly, in such embodiment, casing 11 can also be to be made of flexible material so that flexible spy is presented in casing 11
Sign, the both sides for pinching casing 11 by hand so may make casing 11 to prolong the center portion thereof position and be bent, casing 11 after bending
Corresponding body 12 of placing is fixed on the position there are two socket 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
At three caging bolts 1322 and two 131 corresponding positions of socket, the casing 11 after restoring is allowed in this way and i.e. corresponding is passed through
Two third caging bolts 1322 are respectively inserted into two sockets 131, complete the quick connection with body 12.With convenient, fast
Prompt feature.
For another example, the third positioning plunger 132 in the embodiment of the present invention can also be such as the in above-mentioned first dismounting component 4
The structure of one positioning plunger.I.e.：The third positions plunger 132：Positioning column 1321, the positioning column 1321 are fixed
In on the casing 11；Third positioning bolt, the third positioning bolt are fixed on the positioning column, and the third positions spiral shell
Bolt is provided with the third positioning end；Third positioning thread insert, the third positioning thread insert are set on the third positioning bolt,
And a third compression stroke is provided between the third positioning thread insert and the third positioning bolt；Third retaining spring, institute
Third retaining spring is stated to be set in the third compression stroke；Wherein, it is fixed to sequentially pass through the third for the third positioning end
Position spring, the third compression stroke are inserted into the socket.Further, the third positioning of the third positioning bolt
On end, it is provided with a third card convex, the third retaining spring is limited in the third compression stroke, and is made described
When third positioning end is separated with the socket, the third retaining spring is compressed by the third card convex.
In embodiments of the present invention, as a preferred embodiment, the third caging bolt and/or the third positioning bolt
It is mutually perpendicular to the positioning column.Being fixedly connected between the positioning column and the casing is welding；And/or the positioning
Column and the casing are integrally formed.Between the positioning column and the third caging bolt and/or the third positioning bolt
It is welding to be fixedly connected；And/or the positioning column and the third caging bolt are integrally formed.
Again, for the signal framing component 5,3-14 is please referred to Fig.1, the signal framing component 5 further 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 is logical
The fixing end 511 is crossed to be fixed on the casing 11.The spiral shell disk 52 is fixed on the locating rod by the support end 512
On 51, 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 positioning
Device 53 is arranged by locating rod 51 and spiral shell disk 52 on the fuselage 1, is allowed for locator 53 and institute in this way through spiral shell disk 52
The external air flow for stating fuselage 1 is isolated；It is effective to avoid directly exposed in external fuselage, the unmanned plane during flying mistake of locator 53
External air flow in journey, extraneous moisture either extraneous shelter because of locator with 53 Long Term Contact of locator or caused by rubbing
53 make moist or damage, and have the characteristics that 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, be the equal of a protective cover of locator 53 for spiral shell disk 52, for positioning
Device 53 is protected, and in embodiments of the present invention, the spiral shell disk 52 can include at least：First blind nut 521, first blind nut
521 are provided with internal thread；Second blind nut 522, second blind nut 522 are provided with external screw thread, first blind nut 521 and described
Second blind nut 522, which is threadedly coupled, constitutes the spiral shell disk 52；Wherein, first blind nut 521 and second blind nut 522 can be in
Round, can also be square shape or diamond shaped, and the embodiment of the present invention is not limited.It is noted that the locating rod
The angle constituted between 51 and the casing 11 is an acute angle.That is, the center vertical pivot of locating rod 51 and 11 place of casing
Plane is not mutually perpendicular to, and the inclined surface of locating rod 51 also further reduces locating rod 51 in this way with towards tail orientation
During unmanned plane during flying with the contact resistance of external air flow.
Again, for rotor power component 6,5-16 is please referred to Fig.1, the rotor power component 6 includes at least：The
One motor 61, refrigerating seat 63 and first electricity adjust 64 (first electricity adjust 64 and following second electricity adjust can be understood as heat radiating type electricity
It adjusts).The first rotor rotational that power is provided due to rotating to be unmanned plane during flying is fixed in the first motor 61；It is described cold
But seat 63 is fixed in the rotor shaft 2, and the 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
The first motor 61 is connected with the flight control system inside fuselage 1, to control institute by the flight control system
It states the first electricity and adjusts 64, realize and drive the first motor 61 that first rotor is driven to be rotated.
It should be strongly noted that the refrigerating seat 63 is provided at least one ventilation opening 631, by the refrigerating seat 63
Inner space communicated with free surrounding space.It allows in this way when the first electricity tune 64 is fixed on the inside of refrigerating seat 63, in real time
Convection current is formed with the cold air of 63 periphery of refrigerating seat, to adjust 64 to be cooled down in real time the first electricity, is effectively avoided because of first
Electricity adjusts 64 to overheat the technological deficiencies scalded and the first electricity tune 64 is caused to be unable to operate normally.Meanwhile it is the first electricity tune 64 is directly solid
Due to the peripheral position of fuselage 1, and due to the first rotor be mounted on refrigerating seat 63 on, 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 caused by long there are circuit work(
Rate is lost, and has efficient, energy saving feature.
Certainly, in embodiments of the present invention, 9 are please referred to Fig.1, rotor power component 6 can also include 62 He of the second motor
Second electricity is adjusted, and second electricity is adjusted and connect respectively with second motor 62 and the flight control system.At this point it is possible to manage
Solution is that the refrigerating seat 63 includes the first stationary plane and the second stationary plane, and the 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 the way that 2 motors and 2 electricity are arranged shown in Figure 19, 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 reconciliation, which is adjusted, and 64 are adjusted with the first electricity
For, 7-18 is please referred to Fig.1, at least may include：First capacitance 641, first circuit board 642 and the first heat sink 643.Its
In, the first circuit board 642 connects with first capacitance 641, the first motor 61 and the flight control system respectively
It connects, 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 ventilation 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 as the first electricity tune 64 for the second electricity is adjusted, can also include：Second capacitance；Second circuit board；And the
Two heat sinks；Wherein, the second circuit board respectively with second capacitance, second motor and the flight control system
Connection, and second heat sink is attached on the second circuit board.Since 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 details are not described herein again, the non-detailed portion of internal structure that the second electricity is adjusted,
The first electricity is please referred to adjust.
Preferably, the first circuit board is between first capacitance and first heat sink；And/or institute
Second circuit board is stated between second capacitance and second heat sink.
Further, continuing with referring to Figure 20-23, between first motor 61 and the first rotor 8 connection relation,
For connection relation between second motor 62 and the second rotor 9, the embodiment of the present invention additionally provides a kind of Quick-dismantle component, is used for
Quick Release connection between first motor 61 and the first rotor, between the second motor 62 and the second rotor 9.It realizes and is carrying out the first rotation
When the wing 8, the installation of the second rotor 9 or dismantlement work, it is only necessary to by rotating first rotor 8 or second rotor 9,
The fastening or separation between the first rotor 8 and first motor 61, between the second motor 62 and the second rotor 9 can be realized,
Installation or the dismantlement work of the first rotor 8 can be completed without external operation tool (such as handle), have fast, just
It takes and feature that operating efficiency is high.
Specifically, first motor 61 includes first surface 611 and second surface 612 in the present embodiment.In embodiment,
First surface 611 can be understood as the upper surface of first motor 61, and second surface 612 can be understood as first motor 61
Lower surface, and the first motor 61 is fixed on by the first surface 611 on the first stationary plane of refrigerating seat 63, described
Two motors 62 are fixed on by the second surface 612 on the second stationary plane of refrigerating seat 63.
It is significant to note that in the prior art for the multi-rotor unmanned aerial vehicle of coaxial double-oar, coaxial two
Often diameter, shape are identical for a rotor, and positioned at the both sides up and down of rotor shaft, and the rotor above rotor shaft is revolving
When turning, the air-flow for relying on its lower surface is needed to generate upward thrust to the rotor, then realize it is whole to unmanned plane to
On lift.Obviously, the air-flow flow area of lower surface is bigger, then it is bigger to generate upward thrust to the rotor, then
Realize that integrally upward lift is also bigger to unmanned plane.And exactly since two coaxial rotor sizes are identical, this is just
So that the rotor of top and the rotor of lower section be during rotation, the rotor of lower section is due to the spatial area occupied by its own
And most of air-flow flow area of top rotor lower surface is blocked, and it is then whole to reduce the upward lift of unmanned plane, it leads
Cause flight efficiency low.
And in the present embodiment, it is by the horizontal axis centered on the rotor shaft, the first rotor 8 and the second rotor 9 is symmetrical
Ground is distributed in the both sides of rotor shaft 2, and the diameter of the first rotor 8 is more than the diameter of the second rotor 9, realizes the first rotor 8
Whole size is more than the whole size of the second rotor 9, this allows for the process that the first rotor 8 and the second rotor 9 rotate at the same time
In, the second rotor 9 is greatly reduced due to its own existing spatial area, to the air-flow stream of 8 its lower surface of the first rotor
The obstruction of dynamic area, ensure that the air-flow of 8 its lower surface of the first rotor to thrust size upward caused by the rotor, then
Also avoiding the whole lift upwards of unmanned plane reduces and influences the technological deficiency of its flight efficiency.With the high spy of flight efficiency
Point.
For Quick-dismantle component 7, two Quick-dismantle components 7 can be selected so that first rotor 8 passes through a Quick Release
Component correspondence is rotationally fixed in the first motor, and second rotor 9 is corresponded to rotationally by another Quick-dismantle component
It is fixed on second motor.Since the first rotor 8 is by connection relation, the action principle of Quick-dismantle component 7 and first motor,
It is identical with connection relation, the action principle of the second motor by Quick-dismantle component 7 with the second rotor 9, therefore, following implementations
Example for being connect with first motor 61 by a Quick-dismantle component by the first rotor 8 only by being described in detail, the second rotor 9
It is repeated no more by the connection relation action principle between a Quick-dismantle component and the second motor 61, it can be together refering to following first
Connection description between rotor 8 and first motor 61.
Specifically, during actual job, both the first rotor 8 and first motor 61 are threadedly coupled by Quick-dismantle component 7.
So that during actual job when needing the first rotor to unmanned plane to be installed or dismantled, rotation institute is only needed
The first rotor 8 is stated, such as rotates clockwise the first rotor 8 or counterclockwise the first rotor 8 of rotation, you can realize first rotor
Installation or removal between 8 and the first motor 61.The first rotor 8 is directly fixed on the using bolt compared to traditional
On one motor 61, when needing to dismantle the first rotor 8 from first motor 61, or installing, it is both needed to come by extraneous handle
Bolt is turned, the disassembly and installation work of the first rotor 8 can be completed.And due to being used to connect the first rotor 8 and first motor
61 fixing bolt is the individual component of individualism, when turning bolt by handle and being unloaded, often due to scene behaviour
Make the complexity of environment, easily cause the loss of fixing bolt, once and fixing bolt lose, then can not just complete the first rotor
8 and first motor 61 installment work, that is, the serious consequence for causing flight equipment that can not fly.And the present embodiment, it is exactly based on
Both first rotor 8 and first motor 61 are threadedly coupled using Quick-dismantle component 7 so that the two is in installation or dismounting, nothing
Fast and conveniently, need to have the characteristics that operating efficiency is high by external operation tool (such as handle).
For Quick-dismantle component 7, continuing with referring to Figure 21, the Quick-dismantle component 7 includes at least：First screw 71, the second spiral shell
It follows closely the 72, first screw buckle 73 and first and dismantles nut 74.Wherein, the inner wall 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 hole 77 so that first screw 432 passes through first spiral shell
First screw buckle 73 is fixed on the first surface 611 of the first motor 61 by hole 77.The first dismounting nut 74
Outer wall be provided with first external screw thread 78 compatible with first internal thread 76, and the top of the first dismounting nut 74
Offer the second screw hole 79 so that second screw 72 sequentially passes through first rotor 8, second screw hole 79 will be described
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 by the second screw 72 on the first rotor 8.And first screw buckle 73 inner wall opened up first in spiral shell
The first external screw thread 78 for being opened up of outer wall that line 76 and first dismantles nut 74 exactly matches namely the first internal thread 76 and the
Occlusion locking may be implemented between one external screw thread 78.It allows in this way, when needing the first rotor 8 being mounted in rotor shaft 3,
Since first motor 61 is fixed on the end of rotor shaft 3, also the first rotor 8 is mounted in first motor 61.At this time, it is only necessary to
The first rotor of manual rotation 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 for dismantling nut 74 and the first screw buckle 73, since the first dismounting nut 74 is fixed on the first rotor 8, the first screw buckle
73 are fixed in first motor 61, namely realize the locking installation of the first rotor 8 and first motor 61 (rotor shaft 3).And work as
It when needing dismounting, only needs to reversely rotate the first rotor 8 at this time, realizes that the separation of the first external screw thread 78 and the first internal thread 76 is
It can.It is swift to operate, convenient to have the characteristics that.
It should be noted that unmanned plane, during practical flight, the direction of rotation of the first rotor 8 is rotation side counterclockwise
To, at this point, due in flight course the first rotor 8 be to be in rotating state, and the first rotor 8 and first motor in itself
Itself it is also the connection type that fastening is realized using rotation in embodiment between 61.For example, when the first rotor 8 is relative to first
Motor 61 is when realizing fastening therebetween by rotating clockwise, since the normal of the first rotor 8 rotates to be in flight course
Counterclockwise, there is the inverse time as the normal rotation counterclockwise of the first rotor 8 namely the first rotor 8 are equivalent to first motor 61 at this time
The driving of needle rotation.And due to the first rotor 8 relative to first motor 61 be by rotate clockwise could realize therebetween
Fastening, then it is on the contrary when it is to rotate counterclockwise the first rotor 8 occur relative to first motor 61, i.e., it can cause the first rotor
Fastening relationships between 8 and first motor 61 loosen, and even result in the first rotor 8 and fly away from first motor 61 and cause nobody
The phenomenon that machine crashes.
Therefore, in order to avoid unmanned plane in flight course the is caused due to the normal rotation counterclockwise of the first rotor 8
Fastening relationships between one rotor 8 and first motor 61 loosen, and the embodiment of the present invention is by the first rotor 8 and 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 inner wall of first external screw thread 78 and the first screw buckle 73 is also counterclockwise
Direction.It is allowed in this way when the first rotor 8 is to realize fastening therebetween by rotating counterclockwise relative to first motor 61,
Since the normal of the first rotor 8 rotates to be counterclockwise in flight course, at this time with the normal rotation counterclockwise of the first rotor 8,
Namely first rotor 8 be equivalent to first motor 61 also and have the tendency that rotating counterclockwise.
And due to the first rotor 8 relative to first motor 61 exactly by rotate counterclockwise could realize it is between the two
Fastening, so on the one hand, effectively prevent ought the first rotor 8 relative to first motor 61 stung by rotating clockwise realization
When closing locking, the fastening between the first rotor 8 and first motor 61 is caused due to normal rotate to be counterclockwise of the first rotor 8
Relationship loosens, even result in the first rotor 8 fly away from first motor 61 and cause unmanned plane crash technological deficiency.Another party
Face, since the first rotor 8 is also that could realize fastening between the two by rotation counterclockwise relative to first motor 4 itself,
When the normal rotation counterclockwise with the first rotor 8, and the first rotor 8 is made to be equivalent to first motor 61 also and have rotation counterclockwise
Trend, just also increase 61 fastening relationships between the two of the first rotor 8 and first motor at this time, ensure that flight equipment
Normal safe flight has the characteristics that security performance is high.
Further, as described above continuing with referring to Figure 20-21, when sequentially passing through described by the second screw 72
When the first dismounting nut 74 is fixed on first rotor 8 by one rotor 8, second screw hole 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 first motor 61 and/or rotor shaft 3, however, prolonged vibrations can make the
Connection relation between two screws 72, the first rotor 8 and first dismounting 74 three of nut is extremely unstable, or even causes the second screw
72 loosen, and then cause safety accident.Therefore, the present embodiment is by adding 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, first rotor, 8 and second spiral shell
Nut 437 is dismantled by described first and is fixed on first rotor 8 in 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 8 upper surface of the first rotor, by the second screw 72 by the first vibration damping sheet 75
With 8 upper surface of the first rotor relative to fastening, to reduce vibrations of first rotor 8 relative to 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 hole 77 is 2；The quantity of second screw hole 79 is 2.Wherein, each described first screw 71 corresponds to one
First screw hole 77 so that each described first screw 71 passes through corresponding one first screw hole 77 by described first
Screw buckle 73 is fixed in the first motor 61；Each described second screw 72 corresponds to second screw hole 79, makes
It obtains each described second screw 72 and first screw buckle 73 is fixed on institute across corresponding one second screw hole 79
It states in first motor 61.
Although preferred embodiments of the present invention have been described, it is created once a person skilled in the art knows basic
Property concept, then additional changes and modifications may be made to these embodiments.So it includes excellent that the following claims are intended to be interpreted as
It selects embodiment and falls into all change and modification of the scope of the invention.
Obviously, various changes and modifications can be made to the invention without departing from essence of the invention by those skilled in the art
God and range.In this way, if these modifications and changes of the present invention belongs to the range of the claims in the present invention and its equivalent technologies
Within, then the present invention is also intended to include these modifications and variations.
Claims (9)
1. a kind of unmanned plane with detachable rotor structure, wherein unmanned plane includes rotor shaft, flight control system and cloud
Platform, which is characterized in that the unmanned plane with detachable rotor structure includes：
First rotor；
Second rotor；
Two Quick-dismantle components；
Rotor power component, the rotor power component is fixed in the rotor shaft, and is connect with the flight control system,
Think the powered rotation of first rotor and second rotor；And first rotor is turned by a Quick-dismantle component
It is fixed on dynamicly on the rotor power component so that first rotor is rotatable relative to the rotor shaft；Described second
Rotor is rotationally fixed to by another Quick-dismantle component on the rotor power component so that second rotor is relative to institute
It is rotatable to state rotor shaft；And the diameter of first rotor is more than the diameter of second rotor,
Fuselage, the fuselage include：
Casing；
The inside of body, the body is in hollow-core construction, and at least one installing port is provided on the body；
Second dismounting component, the second dismounting component is connected to the casing is detachable on the body, and is passed through
The cabinet cover closes the installing port；Wherein, component to be installed in the body by the installing port relative to described
Body is placed into or is removed；
First dismounting component, the first dismounting component is fixed on the body, and is slidably connected with the holder, so that institute
Stating holder can be slided relative to the first dismounting component or the body；
Wherein, it dismantles component by described first the holder is connected on the body so that the holder passes through described
It is detachable between first dismounting component and the body；
Described first, which dismantles component, includes：
Fixed plate, the fixed plate are fixed on the body, and are slidably connected with the holder so that the holder relative to
The fixed plate is slided；
Positioning element, the positioning element are fixed in the fixed plate, with the position to the holder relative to the fixed plate
It sets and is positioned, and then realize that the holder is installed or dismantled relative to the body；
The U-shaped shape in fixed plate section, including：First side plate；Second side plate and transverse slat；Wherein, first side plate and institute
It is parallel to state the second side plate；And first side plate and second side plate and the transverse slat are perpendicular, and the transverse slat is distinguished
It is slidably connected with first side plate and second side plate, the holder is fixedly connected with the transverse slat, and then by described
Transverse slat makes the holder be slided relative to first side plate and second side plate；The positioning element is fixed respectively
In on first side plate and second side plate, with to the transverse slat relative to first side plate and second side plate
Position is positioned；One end of the positioning element is corresponding to pass through first side plate, second side plate, and in sliding slot
Protrusion or shrink so that one end of the positioning element relative to the sliding slot in the sliding slot internal projection, the positioning
One end of component stops that the transverse slat is slided in the sliding slot, and one end of the positioning element exists relative to the sliding slot
When the sliding slot contract, one end of the positioning element is separated with the transverse slat, so that the transverse slat is in the sliding slot
It is slided.
2. the unmanned plane with detachable rotor structure as described in claim 1, which is characterized in that the rotor power component
Including：
Refrigerating seat, the refrigerating seat include the first stationary plane and the second stationary plane, and first stationary plane and described second are fixed
Face horizontal axis centered on the rotor shaft, is symmetrically dispersed in the both sides of the rotor shaft；
First motor, the first motor are fixed on first stationary plane, and first rotor is made to pass through a Quick Release group
Part rotation is fixed in the first motor；
Second motor, second motor are fixed on second stationary plane, and second rotor is made to pass through another Quick Release
Component rotation is fixed on second motor；
First electricity is adjusted, and first electricity, which is adjusted, is fixed on the inside of the refrigerating seat, and respectively with the first motor and the nothing
The flight control system of man-machine inside connects, and first rotor is driven to move the first motor by the described first electric transfer drive
It is rotated；
Second electricity is adjusted, and second electricity, which is adjusted, is fixed on the inside of the refrigerating seat, and respectively with second motor and the nothing
The flight control system of man-machine inside connects, and second rotor is driven to move second motor by the described second electric transfer drive
It is rotated.
3. the unmanned plane with detachable rotor structure as claimed in claim 2, which is characterized in that
The refrigerating seat is provided at least one ventilation opening, and the inner space of the refrigerating seat is communicated with free surrounding space.
4. the unmanned plane with detachable rotor structure as claimed in claim 3, which is characterized in that
First electricity, which is stealthily substituted, to be included：First capacitance, first circuit board and the first heat sink；Wherein, the first circuit board difference
Connect with first capacitance, the first motor and the flight control system, and first heat sink be attached to it is described
On first circuit board；
With,
Second electricity, which is stealthily substituted, to be included：Second capacitance, second circuit board and the second heat sink；Wherein, the second circuit board difference
Connect with second capacitance, second motor and the flight control system, and second heat sink be attached to it is described
On second circuit board.
5. the unmanned plane with detachable rotor structure as claimed in claim 4, which is characterized in that
First heat sink and/or second heat sink are aluminium sheets.
6. the unmanned plane with detachable rotor structure as described in claim 4 or 5, which is characterized in that
The first circuit board is between first capacitance and first heat sink；
And/or
The second circuit board is between second capacitance and second heat sink.
7. the unmanned plane with detachable rotor structure as claimed in claim 2, which is characterized in that the Quick-dismantle component packet
It includes：
First screw；
Second screw；
The inner wall of first screw buckle, first screw buckle is provided with the first internal thread, and the bottom of first screw buckle is opened
Equipped with the first screw hole so that first screw passes through first screw hole that first screw buckle is fixed on first electricity
On machine or second motor；
The outer wall of first dismounting nut, the first dismounting nut is provided with the first external screw thread, and described first dismantles nut
Top offers the second screw hole so that second screw sequentially passes through first rotor, the second screw hole is torn open described first
Removing nut is fixed on first rotor, or second screw is made to sequentially pass through second rotor, the second screw hole
Nut is dismantled by described first to be fixed on second rotor；
Wherein, first internal thread is adapted with first external screw thread, and passes through first internal thread and described first
Occlusion between external screw thread or separation, between corresponding realization first rotor and the first motor or described
Installation or dismounting between two rotors and second motor.
8. the unmanned plane with detachable rotor structure as claimed in claim 7, which is characterized in that
The quantity of first screw is 2；
The quantity of second screw is 2；
The quantity of first screw hole is 2；
The quantity of second screw hole is 2；
Wherein, each described first screw corresponds to first screw hole so that each described first screw passes through phase
First screw buckle is fixed in the first motor or second motor by first screw hole answered；It is each
A second screw corresponds to second screw hole so that each described second screw passes through corresponding one described the
First screw buckle is fixed in the first motor or the second motor by two screw holes.
9. the unmanned plane with detachable rotor structure as described in claim 1, which is characterized in that
In the vertical direction, first rotor is located at the top of second rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610280566.3A CN105818974B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with detachable rotor structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610280566.3A CN105818974B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with detachable rotor structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105818974A CN105818974A (en) | 2016-08-03 |
| CN105818974B true CN105818974B (en) | 2018-10-19 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610280566.3A Expired - Fee Related CN105818974B (en) | 2016-04-29 | 2016-04-29 | Unmanned plane with detachable rotor structure |
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|---|---|
| CN (1) | CN105818974B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106437997A (en) * | 2016-10-26 | 2017-02-22 | 天津曙光天成科技有限公司 | Cooling device for engine of multi-rotor unmanned aerial vehicle and multi-rotor unmanned aerial vehicle |
| CN107380418A (en) * | 2017-08-10 | 2017-11-24 | 河南谷翼自动化科技有限公司 | A kind of axle plant protection unmanned plane of modular assembly four |
| CN109557102A (en) * | 2019-01-15 | 2019-04-02 | 成都圭目机器人有限公司 | A kind of ship type underground sewer detection robot |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201989945U (en) * | 2011-04-15 | 2011-09-28 | 天津全华时代航天科技发展有限公司 | Modular quick-splicing type unmanned aerial vehicle |
| 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 |
| US9573683B2 (en) * | 2014-04-28 | 2017-02-21 | Arch-Aerial, Llc | Collapsible multi-rotor UAV |
| CN104787317B (en) * | 2015-04-17 | 2019-01-25 | 珠海磐磊智能科技有限公司 | Aircraft and its control method |
| 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 |
| CN105366041B (en) * | 2015-11-30 | 2019-02-12 | 易瓦特科技股份公司 | More rotor structures applied to unmanned plane |
| CN205707330U (en) * | 2016-04-29 | 2016-11-23 | 易瓦特科技股份公司 | There is the unmanned plane of dismountable rotor structure |
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2016
- 2016-04-29 CN CN201610280566.3A patent/CN105818974B/en not_active Expired - Fee Related
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| CN105818974A (en) | 2016-08-03 |
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Address after: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant after: Ewatt Technology Co.,Ltd. Address before: 430000 Hubei province Wuhan City Jiang'an District Lake Street Bridge Road No. 5 Building 1 layer 4 Applicant before: Ewatt Technology Co.,Ltd. |
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