CN106081128A - A kind of electric motor mounting structure on double-deck rotor wing unmanned aerial vehicle - Google Patents
A kind of electric motor mounting structure on double-deck rotor wing unmanned aerial vehicle Download PDFInfo
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- CN106081128A CN106081128A CN201610472236.4A CN201610472236A CN106081128A CN 106081128 A CN106081128 A CN 106081128A CN 201610472236 A CN201610472236 A CN 201610472236A CN 106081128 A CN106081128 A CN 106081128A
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- holding frame
- double
- unmanned aerial
- aerial vehicle
- electric motor
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- 238000010276 construction Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 3
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 230000008901 benefit Effects 0.000 description 9
- 239000000463 material Substances 0.000 description 5
- 239000002131 composite material Substances 0.000 description 4
- 238000002474 experimental method Methods 0.000 description 4
- 241000397426 Centroberyx lineatus Species 0.000 description 3
- 230000017525 heat dissipation Effects 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000012544 monitoring process Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000037237 body shape Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000006731 degradation reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012806 monitoring device Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 230000005855 radiation Effects 0.000 description 1
Classifications
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- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
-
- 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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
-
- 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
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Motor Or Generator Frames (AREA)
Abstract
The present invention relates to the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle, including motor cabinet, connecting tube, two motors；Motor cabinet includes holding frame, two mounting seats；The two ends being arranged on holding frame that two mounting seats are corresponding, are connected together between mounting seat and holding frame；Connecting tube includes polygonal body, connects seat；Connect seat to be fastened in the mouth of pipe of body one end；Body is plugged in the installing hole on holding frame away from the one end connecting seat；Holding frame is provided with the installing hole matched with body；The shape of cross section of body is identical with the shape of cross section of installing hole；The shape of cross section of body tube chamber is identical with the shape of cross section of body.The invention has the beneficial effects as follows: effectively reduce the unmanned plane vibrations when flight, be effectively prevented between body and motor cabinet and occur relatively rotating, increase the space of wiring；Improve the unmanned plane stability when flight, safety；The present invention is also equipped with simple in construction, feature easy for installation.
Description
Technical field
The present invention relates to unmanned plane field, particularly relate to the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle.
Background technology
Unmanned air vehicle technique developed rapidly in recent years, and various types of unmanned planes continue to bring out, and many rotor wing unmanned aerial vehicles system has
Handling can hover by force, anywhere plays degradation advantage, can carry the monitoring devices such as all kinds of optical light sensor and photographing unit,
Tasks such as scouting, take photo by plane can be realized convenient, efficiently, be widely used in public safety, power-line patrolling, traffic monitoring,
Fire-fighting, ocean and the application such as hydrological monitoring, military surveillance.
Its flight of many rotor wing unmanned aerial vehicles mainly drives propeller to rotate by brushless electric machine, so that unmanned function
Enough complete flight.Existing many rotor wing unmanned aerial vehicles great majority use monolayer rotor, and the unmanned plane of this monolayer rotor exists
During flight relatively slow, people, in order to solve this problem, develop except the unmanned plane of double-deck rotor, but existing double-deck rotation
There is a defect, i.e. unmanned plane and shake when flight bigger in wing unmanned plane, its main cause is to install motor in use
Structure design unreasonable, it does not offset counteracting force produced by the rotor of positive and negative rotation.
Summary of the invention
The technical problem to be solved is to provide and a kind of can eliminate the unmanned plane vibrations when flight, stability
Good electric motor mounting structure.
The technical scheme is that knot installed by the motor on a kind of double-deck rotor wing unmanned aerial vehicle
Structure, including motor cabinet, connecting tube, two motors；Motor cabinet includes holding frame, two mounting seats；Two corresponding setting of mounting seat
Put the two ends at holding frame, and be connected together between mounting seat and holding frame；What two motors were corresponding is arranged on two mounting seats
On；Connecting tube includes polygonal body, connects seat；Connect seat to be fastened in the mouth of pipe of body one end；Body is away from connecting seat
One end be plugged in the installing hole on holding frame；Holding frame is provided with the installing hole matched with body；The cross section of body
Shape is identical with the shape of cross section of installing hole；The shape of cross section of body tube chamber is identical with the shape of cross section of body.
The invention has the beneficial effects as follows: by two mounting seats are symmetrically installed on holding frame, and motor is installed
In mounting seat so that two motors are cancelled out each other by counteracting force produced by rotor when operating at the same time, and then effectively
Reduce the unmanned plane vibrations when flight, simultaneously by body with install the installing hole of body and be arranged to polygonized structure, have
Relatively rotating occurs between body and holding frame in preventing of effect, and the tube chamber of body is also configured to polygonized structure, identical material
Body in the case of being equal in weight, the tube chamber wiring space of square tube be greater than pipe tube chamber wiring space, Jin Erzeng
The big space of wiring；Improve the unmanned plane stability when flight, safety；The present invention is also equipped with simple in construction, installation
Feature easily.
On the basis of technique scheme, the present invention can also do following improvement.
Further, the upper and lower two ends of holding frame are equipped with and project outwardly of tenon portion from this holding frame end face；In mounting seat relatively
That answers is provided with the slot matched with tenon portion, and tenon portion snaps in the slot of correspondence.
Further, the cross section of tenon portion and the cross section of slot are the most dovetail-shape or T-shaped.
Use and above-mentioned further provide the benefit that: facilitate and install between mounting seat and holding frame.
Further, body is provided with some radiating grooves running through this side pipe wall at least one sidewall.
Use and above-mentioned further provide the benefit that: convenient circuit intraluminal to body dispels the heat.
Further, what radiating groove all tilted is arranged on body, and the angle of inclination of radiating groove is between 0-45 degree.
Use and above-mentioned further provide the benefit that: area of dissipation is big.
Further, body total length is on body single-sided side walls set by radiating groove between 1-4 times of the length in region.
Use and above-mentioned further provide the benefit that: while body good heat dissipation, ensure that the rigidity of body.
Further, the groove width of radiating groove is between 1-3 times of body wall thickness.
Use and above-mentioned further provide the benefit that: while body good heat dissipation, ensure that the rigidity of body.
Further, the spacing between adjacent two radiating grooves on same sidewall is radiating groove groove width on this sidewall
Between 2-4 times.
Use and above-mentioned further provide the benefit that: while body good heat dissipation, ensure that the rigidity of body.
Further, connect seat and be provided with the connecting hole for being connected with body.
Use and above-mentioned further provide the benefit that: be easy to be connected whole mounting structure with body.
Further, the shape of cross section of body is hexagon, octagon or dodecagon.
Use and above-mentioned further provide the benefit that: good stability, prevent and relatively rotate.
Accompanying drawing explanation
Fig. 1 is the structural representation of the embodiment of the present invention；
Fig. 2 is the side view of Fig. 1；
Fig. 3 is the top view of Fig. 1；
Fig. 4 is the structural representation of motor cabinet in Fig. 1；
Fig. 5 is the structural representation of connecting tube in Fig. 1；
Fig. 6 is the side view of Fig. 1 middle tube body.
In accompanying drawing, the list of parts representated by each label is as follows:
1, motor cabinet, 2, connecting tube, 3, motor, 11, holding frame, 12, mounting seat, 13, installing hole, 21, body, 22, even
Joint chair, 23, radiating groove, 24, connecting hole；25, end cap, 26, draw-in groove, 101, tenon portion, 102, slot, the 103, first through hole,
104, trip bolt, 105, trip bolt hole, 106, trip bolt cross groove, 1001, left side wall, 1002, right side wall, 1003,
One extension, the 1004, second extension, the 1005, the 3rd extension, the 1006, the 4th extension, 1007, roof, 1008, diapire,
1009, routing hole, 1010, wiring groove；211, the first side wall, the 212, second sidewall, the 213, the 3rd sidewall, the 214, the 4th sidewall,
215, the 5th sidewall, the 216, the 6th sidewall, 217, heptalateral wall, the 218, the 8th sidewall.
Detailed description of the invention
Being described principle and the feature of the present invention below in conjunction with accompanying drawing, example is served only for explaining the present invention, and
Non-for limiting the scope of the present invention.
As shown in Figure 1, Figure 2, Figure 3 shows, the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle, including motor cabinet 1, connect
2, two motors 3 of pipe, motor cabinet 1 includes 11, two mounting seats 12 of holding frame；Two mounting seat 12 correspondences be arranged on holding frame
It is connected together between the two ends of 11, and mounting seat 12 and holding frame 11, each mounting seat 12 all fixes motor 3；Connecting tube 2
Including body 21, connecting seat 22, wherein, the one end connecting seat 22 is fastened in the mouth of pipe of body 21 one end, and body 21 is away from even
One end of joint chair 22 is plugged on holding frame 11.
As shown in Figure 1, shown in Figure 5, the shape of cross section of body 21 can be hexagon, octagon or dodecagon, this enforcement
Example illustrates with body 21 shape of cross section for octagon:
As shown in Figure 4, holding frame 11 is provided with the octagonal installing hole 13 identical with body 21 shape of cross section, pipe
One end of body 21 is positioned at installing hole 13；Connection seat 22 is positioned at shape of cross section and body 21 tube chamber of the part of body 21
Shape of cross section is identical, is octagon.Screw is used to carry out tightly between body 21 and holding frame 11 in installing hole 13
It is solidly connected.
As shown in Figure 4, the concrete structure being connected together between mounting seat 12 and holding frame 11 is: holding frame about 11 two ends
Being equipped with and project outwardly of tenon portion 101 from this holding frame 11 end face, the shape of cross section of tenon portion 101 is swallow-tail form or T-shaped, this
In embodiment, the shape of cross section with tenon portion 101 illustrates for swallow-tail form；Corresponding being provided with and tenon portion 101 in mounting seat 12
The slot 102 matched, slot 102 is in order to suitable with tenon portion 101, and the shape of cross section of slot 102 is swallow-tail form,
Tenon portion 101 snaps in the slot 102 of correspondence.
As shown in Figure 4, the concrete structure of holding frame 11 is: holding frame 11 includes left side wall 1001, right side wall 1002；Left side
The upper end of wall 1001 and right side wall 1002 bends towards the direction of its opposing sidewalls respectively and extends, and forms the first extension 1003
With the second extension 1004；The bottom of left side wall 1001 and right side wall 1002 is prolonged towards the bending of the direction of its opposing sidewalls respectively
Stretch, form the 3rd extension 1005 and the 4th extension 1006；The upper end of the first extension 1003 bends towards horizontal direction
Extend, and be crossed to form roof 1007 with the second extension 1004；The bottom of the 3rd extension 1005 is curved towards horizontal direction
Folding extends, and is crossed to form diapire 1008 with the 4th extension 1006；Left side wall 1001, right side wall the 1002, first extension
1003, the second extension the 1004, the 3rd extension the 1005, the 4th extension 1006, roof 1007 and diapire 1008 enclose shape
Octagonal installing hole 13 described in one-tenth；Left side wall the 1001, first extension the 1003, the 3rd extension 1005 forms class X font
Structure；Right side wall the 1002, second extension the 1004, the 3rd extension 1005 forms the structure of class X font；Tenon portion 101 is positioned at
On diapire 1008 and roof 1007.
As shown in Figure 4, it is also possible to holding frame 11 is carried out following improvement:
First extension the 1003, second extension the 1004, the 3rd extension the 1005, the 4th extension at holding frame 11
Being respectively provided with the first through hole 103 running through this extension on 1006, the contour shape of the first through hole 103 is class triangle.
Four trip bolt holes 105 are set in mounting seat 12, and at each trip bolt hole 105, are equipped with a fastening
Groove 106 crossed by screw；Mounting seat 12 is fastenedly connected with motor 3 by four trip bolts 104, and each trip bolt 104 both passes through
Corresponding trip bolt hole 105.
Diapire 1008 and roof 1007 are equipped with a routing hole 1009, routing hole on the installed surface connecting motor 3
1009 centers being positioned at installed surface；Diapire 1008 is provided with wiring groove with on roof 1007 at the end face relative with motor 3 installed surface
1010, the setting direction of wiring groove 1010 is identical with the direction of tenon portion 101；Routing hole 1009 is connected with wiring groove 1010；Cloth
Wire casing 1010 two ends are all in opening.
Body 21 can also be carried out following improvement:
As shown in Figure 1, Figure 2, Figure 5, it is arranged with end cap 25, body 21 in the body 21 mouth of pipe away from the one end connecting seat 22
Upper relevant position is provided with draw-in groove 26, and wherein one end of draw-in groove 26 is opening-like.
As shown in Figure 6, body 21 is eight-sided formation, including eight sidewalls, and respectively the first side wall the 211, second sidewall
212, the 3rd sidewall 213, the 4th sidewall 214, the 5th sidewall 215, the 6th sidewall 216, heptalateral wall 217, the 8th sidewall 217；
The first side wall the 211, second sidewall 212, the 3rd sidewall 213, the 4th sidewall 214, the 5th sidewall 215, the 6th sidewall 216, the 7th
Sidewall 217, the 8th sidewall 217 is symmetrical；Body 21 is provided with on the 3rd sidewall 213 and heptalateral wall 217 and some runs through this
The radiating groove 23 of side pipe wall, the region of the radiating groove 23 that the 3rd sidewall 213 and heptalateral wall 217 are offered is equal.Do not arrange
Except arrange on the first side wall the 211, the 5th sidewall 215 arrange on radiating groove 23, or the second sidewall the 212, the 6th sidewall 216 scattered
Arranging radiating groove 23 on heat channel 23, or the 4th sidewall the 214, the 8th sidewall 217, the present embodiment is preferably the 3rd sidewall 213 He
Arranging radiating groove 23 on heptalateral wall 217, its main cause is, it is easy to processing, and area of dissipation is big.
Radiating groove 23 on body 21 can also be improved as follows:
The spacing between adjacent two radiating grooves 23 on same sidewall is equal, and radiating groove 23 is the most in the same direction
Tilting, in the present embodiment, the incline direction of radiating groove 23 is all towards connecting seat 22, and angle of inclination is between 0-45 degree.According to
Many experiments draws, when the angle of inclination of radiating groove 23 is 15 degree for optimum, its main cause is easy to process, area of dissipation
Greatly.
Between on same sidewall 2-4 times that spacing is radiating groove 23 groove width between adjacent two radiating grooves 23.
Drawing according to many experiments, for optimum during between adjacent two radiating grooves 23 2.5 times that spacing is radiating groove 23 groove width, it is main
Wanting reason is in same area, it is possible to arrange more radiating groove 23, improves thermal diffusivity, is the most also avoided that body 21 uses
Time part between two adjacent radiating grooves 23 fractureing occurs or ruptures occur that fractureing or the reason ruptured are, two dissipate
Heat channel 23 spacing is too small, and the rigidity causing part between two radiating grooves 23 is inadequate.
The groove width of radiating groove 23 is between 1-3 times of body 21 wall thickness.Draw according to many experiments, the groove width of radiating groove 23
Be optimum during for 1.5 times of body 21 wall thickness, if its main cause is radiating groove 23 offer excessive, body 21 is at radiating groove 23
The rigidity at place is less, body 21 frangibility or rupture, and preferably 1.5 times, allows radiating groove 23 while guaranteeing rigidity
Groove width offers maximum.
Body 21 total length is on body 21 single-sided side walls set by radiating groove 23 between 1-4 times of the length in region.Root
Draw according to many experiments, when body 21 total length is 3 times of the length in region set by radiating groove 23 on body 21 single-sided side walls
For optimum, while ensure that body 21 has good thermal diffusivity, also ensure body 21 rigidity in use.
Radiating groove 23 on 3rd sidewall 213 and heptalateral wall 217 is when offering, and the length of radiating groove 23 is less than the 3rd side
Wall 213 or the wall width of heptalateral wall 217, it is to avoid radiating groove 23 is offered on adjacent sidewall, facilitate the processing of radiating groove 23, keep away
Exempt to affect the rigidity of the junction of adjacent two sidewalls.
Body 21 uses composite to make；Described composite includes that carbon fibre composite, glass fibre are compound
Material or honeycomb sandwich composite.
Connect seat 22 for convenience to be connected with body, connect seat 22 and be provided with connecting hole 24, connect and connecting on seat 22
It is provided with yielding groove at hole 24, conveniently connection seat 22 is connected with body.
If the multiple proportion between table 1, the groove width of radiating groove and body wall thickness is on the impact of body rigidity and to heat radiation
The impact of property.
Table 1
| Multiple between groove width and the body wall thickness of radiating groove | Body rigidity | Body thermal diffusivity |
| 0.5 times | The highest | Difference |
| 1.5 again | Higher | Good |
| 2 times | High | Very well |
| 4 times | Low | The best |
As table 2, body total length be on body single-sided side walls set by the multiple proportion pair of length in region of radiating groove
The impact of body rigidity and the impact on thermal diffusivity.
Table 2
Electric motor mounting structure on double-deck rotor wing unmanned aerial vehicle of the present invention, by the peace by two mounting seat 12 symmetries
It is contained on holding frame 11, and motor 3 is arranged in mounting seat 12 so that two motors 3 are produced by rotor when operating at the same time
Raw counteracting force is cancelled out each other, and then effectively reduces the unmanned plane vibrations when flight, simultaneously by body 21 and peace
The installing hole 13 of tubulature body 21 is arranged to polygonized structure, is effectively prevented between body 21 with holding frame 11 relative turn of appearance
Dynamic, the tube chamber of body 21 is also configured to polygonized structure, the body of identical material in the case of being equal in weight, the tube chamber of square tube
Wiring space is greater than the space of the tube chamber wiring of pipe, and then increases the space of wiring；Improve unmanned plane when flight
Stability, safety；The present invention is also equipped with simple in construction, feature easy for installation.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ", " length ", " width ",
" thickness ", " on ", D score, "front", "rear", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward ", " up time
Pin ", " counterclockwise ", " axially ", " radially ", the orientation of the instruction such as " circumferential " or position relationship be based on orientation shown in the drawings or
Position relationship, is for only for ease of the description present invention and simplifies description rather than instruction or imply that the device of indication or element must
Must have specific orientation, with specific azimuth configuration and operation, be therefore not considered as limiting the invention.
Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or hint relative importance
Or the implicit quantity indicating indicated technical characteristic.Thus, define " first ", the feature of " second " can express or
Implicitly include at least one this feature.In describing the invention, " multiple " are meant that at least two, such as two, three
Individual etc., unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, term " install ", " being connected ", " connection ", " fixing " etc.
Term should be interpreted broadly, and connects for example, it may be fixing, it is also possible to be to removably connect, or integral；Can be that machinery connects
Connect, it is also possible to be electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, in can being two elements
The connection in portion or the interaction relationship of two elements, unless otherwise clear and definite restriction.For those of ordinary skill in the art
For, above-mentioned term concrete meaning in the present invention can be understood as the case may be.
In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature " on " or D score permissible
It is that the first and second features directly contact, or the first and second features are by intermediary mediate contact.And, fisrt feature exists
Second feature " on ", " top " and " above " but fisrt feature directly over second feature or oblique upper, or be merely representative of
Fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " lower section " and " below " can be
One feature is immediately below second feature or obliquely downward, or is merely representative of fisrt feature level height less than second feature.
In the description of this specification, reference term " embodiment ", " some embodiments ", " example ", " specifically show
Example " or the description of " some examples " etc. means to combine this embodiment or example describes specific features, structure, material or spy
Point is contained at least one embodiment or the example of the present invention.In this manual, to the schematic representation of above-mentioned term not
Identical embodiment or example must be directed to.And, the specific features of description, structure, material or feature can be in office
One or more embodiments or example combine in an appropriate manner.Additionally, in the case of the most conflicting, the skill of this area
The feature of the different embodiments described in this specification or example and different embodiment or example can be tied by art personnel
Close and combination.
Although above it has been shown and described that embodiments of the invention, it is to be understood that above-described embodiment is example
Property, it is impossible to being interpreted as limitation of the present invention, those of ordinary skill in the art within the scope of the invention can be to above-mentioned
Embodiment is changed, revises, replaces and modification.
Claims (10)
1. the electric motor mounting structure on a double-deck rotor wing unmanned aerial vehicle, it is characterised in that include motor cabinet (1), connecting tube (2),
Two motors (3)；Described motor cabinet (1) includes holding frame (11), two mounting seats (12)；Said two mounting seat (12) is corresponding
The two ends being arranged on described holding frame (11), and be connected together between described mounting seat (12) and described holding frame (11)；Institute
State corresponding being arranged in said two mounting seat (12) of two motors (3)；Described connecting tube (2) includes polygonal body
(21), seat (22) is connected；Described connection seat (22) is fastened in the mouth of pipe of described body (21) one end；Described body (21) away from
The one end connecting seat (22) is plugged in described holding frame (11)；Described holding frame (11) is provided with and matches with described body (21)
The installing hole (13) closed；The shape of cross section of described body (21) is identical with the shape of cross section of described installing hole (13)；Described
The shape of cross section of body (21) tube chamber is identical with the shape of cross section of described body (21).
Electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle the most according to claim 1, it is characterised in that described folder
Hold frame (11) up and down two ends to be equipped with and project outwardly of tenon portion (101) from this holding frame (11) end face；In described mounting seat (12)
Corresponding is provided with the slot (102) matched with described tenon portion (101), and described tenon portion (101) snaps in the described card of correspondence
Close in groove (102).
Electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle the most according to claim 2, it is characterised in that described tenon
The cross section in portion (101) and the cross section of described slot (102) are the most dovetail-shape or T-shaped.
Electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle the most according to claim 1, it is characterised in that described pipe
Body (21) is provided with some radiating grooves (23) running through this side pipe wall at least one sidewall.
Electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle the most according to claim 4, it is characterised in that described scattered
What heat channel (23) all tilted is arranged on described body (21), and the angle of inclination of described radiating groove (23) is between 0-45 degree.
6. according to the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle described in claim 4 or 5, it is characterised in that institute
Stating body (21) total length is on body (21) single-sided side walls set by radiating groove (23) between 1-4 times of the length in region.
7. according to the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle described in claim 4 or 5, it is characterised in that institute
State between 1-3 times that groove width is body (21) wall thickness of radiating groove (23).
8. according to the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle described in claim 4 or 5, it is characterised in that position
The spacing between adjacent two radiating grooves (23) on same sidewall be on this sidewall 2-4 times of radiating groove (23) groove width it
Between.
Electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle the most according to claim 1, it is characterised in that described company
Joint chair (22) is provided with the connecting hole (24) for being connected with body.
10., according to the electric motor mounting structure on a kind of double-deck rotor wing unmanned aerial vehicle described in claim 1 to 5 any one, it is special
Levying and be, the shape of cross section of described body (21) is hexagon, octagon or dodecagon.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610472236.4A CN106081128B (en) | 2016-06-23 | 2016-06-23 | It is a kind of bilayer rotor wing unmanned aerial vehicle on electric motor mounting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610472236.4A CN106081128B (en) | 2016-06-23 | 2016-06-23 | It is a kind of bilayer rotor wing unmanned aerial vehicle on electric motor mounting structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106081128A true CN106081128A (en) | 2016-11-09 |
| CN106081128B CN106081128B (en) | 2018-08-21 |
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| CN201610472236.4A Active CN106081128B (en) | 2016-06-23 | 2016-06-23 | It is a kind of bilayer rotor wing unmanned aerial vehicle on electric motor mounting structure |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204399473U (en) * | 2014-12-12 | 2015-06-17 | 华南农业大学 | A kind of folding many rotor unmanned aircrafts of fast disassembly type |
| US20150375859A1 (en) * | 2014-06-26 | 2015-12-31 | Rotorschmiede Gmbh | Coaxial lifting system |
| CN205131632U (en) * | 2015-11-16 | 2016-04-06 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn device |
| CN205150241U (en) * | 2015-11-06 | 2016-04-13 | 东莞华南设计创新院 | Differential vector impels servo |
| CN205273848U (en) * | 2015-11-30 | 2016-06-01 | 湖北易瓦特科技股份有限公司 | Be applied to unmanned aerial vehicle's wing structure of revolving more |
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- 2016-06-23 CN CN201610472236.4A patent/CN106081128B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20150375859A1 (en) * | 2014-06-26 | 2015-12-31 | Rotorschmiede Gmbh | Coaxial lifting system |
| CN204399473U (en) * | 2014-12-12 | 2015-06-17 | 华南农业大学 | A kind of folding many rotor unmanned aircrafts of fast disassembly type |
| CN205150241U (en) * | 2015-11-06 | 2016-04-13 | 东莞华南设计创新院 | Differential vector impels servo |
| CN205131632U (en) * | 2015-11-16 | 2016-04-06 | 湖南云顶智能科技有限公司 | Unmanned aerial vehicle horn device |
| CN205273848U (en) * | 2015-11-30 | 2016-06-01 | 湖北易瓦特科技股份有限公司 | Be applied to unmanned aerial vehicle's wing structure of revolving more |
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| CN106081128B (en) | 2018-08-21 |
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