CN106081059A - A kind of many rotor wing unmanned aerial vehicles - Google Patents
A kind of many rotor wing unmanned aerial vehicles Download PDFInfo
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- CN106081059A CN106081059A CN201610502437.4A CN201610502437A CN106081059A CN 106081059 A CN106081059 A CN 106081059A CN 201610502437 A CN201610502437 A CN 201610502437A CN 106081059 A CN106081059 A CN 106081059A
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- 230000008569 process Effects 0.000 abstract description 8
- 230000009286 beneficial effect Effects 0.000 abstract description 2
- 238000009434 installation Methods 0.000 description 21
- 230000008901 benefit Effects 0.000 description 9
- 238000002474 experimental method Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 230000005611 electricity Effects 0.000 description 3
- 230000005484 gravity Effects 0.000 description 3
- 238000006243 chemical reaction Methods 0.000 description 2
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
-
- 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
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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
- B64D47/00—Equipment not otherwise provided for
- B64D47/02—Arrangements or adaptations of signal or lighting devices
- B64D47/06—Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
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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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- 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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface specially adapted for helicopters
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of many rotor wing unmanned aerial vehicles, including fuselage, the first horn, the second horn, paddle components；First horn includes that first fixes horn and the first movable horn, and the second horn includes that second fixes horn and the second movable horn；First is fixed between horn and the first movable horn and second fixes and all linked into an integrated entity by some adapters and connector between horn and the second movable horn；First fixes horn fixes with connector and second and all threadeds between horn with connector；All it is connected together between first movable horn and connector and between the second movable horn and connector.The invention has the beneficial effects as follows: will be attached between horn and fuselage by using the connector to, fast assembling-disassembling can not only be accomplished, and in disassembly process, eliminate the worry of wiring, it is simultaneously connected with device and in swapping process, is capable of fast accurate to inserting, overall structure is simple, connects rear stability good.
Description
Technical field
The present invention relates to unmanned plane field, particularly relate to a kind of many rotor wing unmanned aerial vehicles.
Background technology
Unmanned plane (UAV), is to start the most practical a kind of aircraft at present, its have maneuverability,
Reaction quickly, unmanned flight, operation require the advantages such as low.Unmanned plane loads multiclass sensor, such as photographic head, Ke Yishi
Existing image real-time Transmission, high-risk areas detecting function, be widely used in fire-fighting, military affairs, traffic, police service, exploration and meteorology etc.
Field, to realize cruise shooting and the supervision specifying region.
The most relatively common unmanned plane is many rotor wing unmanned aerial vehicles, and many rotor wing unmanned aerial vehicles fuselage is typically by center
Plate, horn, undercarriage forms.Mounting circuit boards, flight controller on central plate.Some other equipment such as battery.Horn connects
Central plate, the horn of all installation rotors is the periphery of the 360/N uniform fuselage of degree angle, and positive rotor is alternately arranged with the derotation wing,
Oppositely oriented, lift is upwards.Undercarriage is used for the whole fuselage of load-bearing.
The horn of many rotor wing unmanned aerial vehicles is more, so needing horn one end to disassemble when transport and preservation to roll over
Folded, to save space, need when flight the flight of horn laggard row is installed, be locked use screw, and the time is long, and efficiency is slow,
Need rewiring when dismounting horn simultaneously, very bother.
Summary of the invention
The technical problem to be solved is to provide a kind of horn easy accessibility, can exempt during dismounting wiring worried,
Horn in swapping process can fast accurate to slotting unmanned plane.
The technical scheme is that a kind of many rotor wing unmanned aerial vehicles, including in strip streamline
The fuselage of type, fuselage is provided with multiple the first horn being symmetric relative to the symmetrical plane in fuselage and the second horn,
Each first horn and each second horn are equipped with paddle components away from one end of fuselage；First horn includes that first fixes machine
Arm and the first movable horn, the second horn includes that second fixes horn and the second movable horn, and first fixes horn and second admittedly
Determine horn all one-body molded with fuselage；First fixes between horn and the first movable horn and second fixes horn and the second activity
All linked into an integrated entity by some adapters between horn；First fixes between horn and the first movable horn and second fixes machine
The most all linked into an integrated entity by connector between arm and the second movable horn；First fixes screw thread between horn and connector connects
Connecing, second fixes and threadeds between horn with connector；Being connected together between first movable horn and connector, second is movable
It is connected together between horn and connector.
The invention has the beneficial effects as follows: by using the connector to the first horn, carrying out between the second horn and fuselage
Connect, fast assembling-disassembling can not only be accomplished, and in disassembly process, eliminate the worry of wiring, be simultaneously connected with device at swapping process
In be capable of fast accurate to inserting, overall structure is simple, connects rear stability good.
On the basis of technique scheme, the present invention can also do following improvement.
Further, first fix horn and be provided with away from one end of fuselage and first fix the outside projection of horn outer circumference surface from this
First protruding；First movable horn and first is fixed one end that horn is connected and is provided with from this first activity horn outer circumference surface
Project outwardly of second protruding；Second fixes horn is provided with from this away from one end of fuselage that second to fix horn outer circumference surface outside
The 3rd of projection is protruding；Second movable horn and second is fixed one end that horn is connected and is provided with from this second activity horn cylindrical
It is protruding that side face projects outwardly of the 4th；First projection is equivalently-sized with the 3rd projection, the second protruding size with the 4th projection
Identical；It is equipped with external thread section on the first protruding periphery with the 3rd projection；Connector includes the connector of cylindrical structural；
Connector is provided with the first mating holes and the second mating holes along axis direction；First mating holes and the second mating holes are connected composition
Shoulder hole；On connector, cooperation face is formed at the bottom of the hole of the second mating holes；The inwall of the second mating holes is provided with convex with first
The internal thread segment that external thread section on Qiing matches；After connector connects with the first projection or the 3rd raised thread, second is protruding
Or the 4th projection end face abut on a mating.
Use and above-mentioned further provide the benefit that: simple in construction, easy accessibility, good stability.
Further, the brachium of the first horn is between 1.3 times to 2.0 times of brachium of the second horn.
Use and above-mentioned further provide the benefit that: balance quality is good, be prone to convert attitude.
Further, the brachium of the first horn is between 2.71 times to 3.32 times of fuselage diameter.
Further, between 2 times to 5 times of the diameter of a diameter of first horn of fuselage；A diameter of second horn of fuselage
2 times to 5 times of diameter between.
Use and above-mentioned further provide the benefit that: the overall center of gravity of regulation unmanned plane.
Further, paddle components includes the motor being arranged on the first movable horn or the second movable horn and is connected to electricity
Blade on the output shaft of machine, the rotation axis of every a piece of blade is respectively positioned on the same face of cylinder.
Use and above-mentioned further provide the benefit that: guarantee stablizing of flight.
Further, the internal diameter of the second mating holes is more than the internal diameter of the first mating holes；The diameter of the first projection is convex more than second
The diameter risen；The diameter of the second projection is more than the internal diameter of the first mating holes, and the diameter of the second projection is interior less than the second mating holes
Footpath.
Use and above-mentioned further provide the benefit that: guarantee the stability being connected together.
Further, the outer circumference surface of connector is provided with anti-slip veins.
Use and above-mentioned further provide the benefit that: conveniently unscrew or tighten, anti-skidding.
Further, between 2 times to 4 times that brachium is the first brachium fixing horn of the first movable horn；Second is movable
The brachium of horn is between 2 times to 4 times of the second brachium fixing horn.
Use and above-mentioned further provide the benefit that: guarantee the stability of junction.
Further, the end of the first movable horn and the second movable horn is equipped with undercarriage；Undercarriage is cylindrical
Structure, undercarriage is provided with display lamp.
Use and above-mentioned further provide the benefit that: be easy to understand unmanned plane during flying state.
Accompanying drawing explanation
Fig. 1 is the structural representation of the embodiment of the present invention；
Fig. 2 is the top view of Fig. 1；
Fig. 3 is sectional view at A in Fig. 2；
Fig. 4 is part-structure figure at A in Fig. 2；
Fig. 5 is the sectional view of Fig. 4；
B sectional view in Fig. 6 Fig. 2；
Part B structure chart in Fig. 7 Fig. 2；
The sectional view of Fig. 8 Fig. 7.
In accompanying drawing, the list of parts representated by each label is as follows:
100, fuselage, the 200, first horn, 210, first fixes horn, and 211, first is protruding, the 220, first movable horn,
221, second is protruding, the 300, second horn, and 310, second fixes horn, and the 311, the 3rd is protruding, the 320, second movable horn, 321,
4th is protruding, and 400, paddle components, 410, blade, 500, adapter, 510, power connector, 520, six core adapters, 511,
Positive source male, 512 power cathode females, 521, six core plug males, 522, six core plug females, 600, connector,
610, connector, the 620, first mating holes, the 630, second mating holes, 640, coordinate face, 700, hollow installation cavity, 800, rise and fall
Frame, 810, display lamp.
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.
The present invention provides a kind of many rotor wing unmanned aerial vehicles, can be that four rotors, six rotors and rotor quantity are more than six and for even
The unmanned plane of number, as it is shown in figure 1, in the present embodiment, these many rotor wing unmanned aerial vehicles include the fairshaped fuselage 100 in strip, than
As, fuselage 100 illustrated in fig. 1 substantially cylindrical bodily form structure, wherein, the diameter in the middle part of fuselage 100 is maximum, the diameter at two ends
Reduction in line style.Fuselage 100 uses composite to make, the most preferably carbon fibre material, strong in satisfied higher use
On the premise of degree and rigidity, can significantly alleviate the weight of fuselage 100, thus reduce the power demand of many rotor wing unmanned aerial vehicles and carry
The mobility of high many rotor wing unmanned aerial vehicles, can also is that glass fiber material certainly.
As in figure 2 it is shown, fuselage 100 be provided with multiple be symmetric relative to the symmetrical plane in fuselage 100 first
Horn 200 and the second horn 300, illustrate below as a example by four rotor wing unmanned aerial vehicles: the quantity of the first horn 200 is two,
The quantity of the second horn 300 is two, and wherein, the first horn 200 is long horn, and the second horn 300 is short horn, fuselage 100
Streamlined in strip, the diameter of fuselage 100 left end is more than the diameter of fuselage 100 right-hand member, and the second horn 300 is arranged on fuselage 100
The both sides of left end, the first horn 200 is arranged on the both sides of fuselage 100 right-hand member, and two the first horns 200 are away from the one of fuselage 100
End and two the second horns 300 are equipped with paddle components 400 away from one end of fuselage 100, and paddle components 400 includes being arranged on machine
Motor on arm and the blade 410 being connected on the output shaft of motor, the rotation axis of every a piece of blade 410 is respectively positioned on same circle
On cylinder, the brachium of the first horn 200 is more than the brachium of the second horn 300, so that four rotor wing unmanned aerial vehicles are at flight course
In involved balance and attitudes vibration control simpler, there is more excellent balance quality, thus improve four rotors without
Man-machine seaworthiness.
As Fig. 3, such as Fig. 4 as it is shown in figure 5, the following horn of rotor wing unmanned aerial vehicles many to the present invention as a example by the first horn 200
Installation is described in detail: the first horn 200 is made up of two sections of horns being removably connected, wherein one section of horn one
Take shape in fuselage 100.First horn 200 includes that detachably connected all-in-one-piece first fixes horn 210 and the first moving machine
Arm 220, wherein, first to fix horn 210 one-body molded with fuselage 100, and the first movable horn 220 is then buckled by screw, card
Structure and other any suitable Detachable connection structure are fixed on the first end fixing horn 210, and paddle components 400 is arranged
On the outer end of the first movable horn 220.
As it is shown in figure 5, the motor of paddle components 400 need to electrically connect with the electric-control system of configuration in fuselage 100, therefore realize
Control to motor, it is contemplated that first fixes horn 210 and the first movable horn 220 for splitting structure, solid in order to exempt first
Determining horn 210 and the wiring in swapping process of the first movable horn 220 is worried, first fixes horn 210 and the first moving machine
Arm 220 is electrically connected by adapter 500, and wherein, the quantity of the adapter 500 being electrically connected is three, and two is electricity
Source connector 510, another is six core adapters 520, and first fixes horn 210 is merging place's shape with the first movable horn 220
Becoming hollow installation cavity 700, hollow installation cavity 700 is made up of two parts, and wherein part installation cavity is positioned at first and fixes horn 210
On, another part installation cavity is positioned on the first movable horn 220.Power connector 510 is by the positive source male being mutually adapted
511 and power cathode female 512 form, two power connectors 510 then have two positive source males 511 and two power supplys
Negative pole female 512.In this example, a positive source male 511 and a power cathode female 512 are arranged on first and fix
In installation cavity on horn 210, another positive source male 511 and another power cathode female 512 are arranged on first and live
In installation cavity on motivation arm 220.When carrying out the grafting that first fixes horn 210 and the first movable horn 220, first fixes
Positive source male 511 in installation cavity on horn 210 can be with the power cathode in the installation cavity on the first movable horn 220
Female 512 electrically connects, same, and first fixes the power cathode female 512 in the installation cavity on horn 210 can be movable with first
Positive source male 511 in installation cavity on horn 220 electrically connects.Certainly this is only the mounting means of the present embodiment, and
Being not excluded for, first fixes two positive source males 511 of installation on horn 210, and the first movable horn 220 installs two power supplys
Negative pole female 512；Or first fix on horn 210 two power cathode females 512 of installation, the first movable horn 220 is installed
Two positive source males 511.
As it is shown in figure 5, six core adapters 520 are by six core plug male 521 and the six core plug females 522 groups being mutually adapted
Becoming, in this example, six core plug females 522 are arranged in the installation cavity on the first movable horn 220, six core plug males
521 are arranged on first fixes on horn 210 in installation cavity, fixes inserting of horn 210 and the first movable horn 220 carrying out first
When connecing, six core plug females 522 can be electrically connected with six core plug males 521.Certainly this is only the installation of the present embodiment
Mode, it is not excluded that, six core plug females 522 are arranged in the first installation cavity fixed on horn 210, six core plug males
521 are arranged on the first movable horn 220 in installation cavity.Additionally, in this example because of wiring need select six core adapters
520, connector, 4-pin or eight core adapters can also be selected by concrete wiring condition when actually used.
As it is shown on figure 3, in order to further strengthen first fix when horn 210 is connected with the first movable horn 220 steady
Qualitative, first fixes horn 210 is attached also by connector 800 with the first movable horn 220；For fit connection
The connection of 800, first fixes horn 210 is provided with from this away from one end of fuselage 100 that first to fix horn 210 outer circumference surface outside
First projection 211 of projection, the first movable horn 220 is fixed one end that horn 210 is connected and is provided with from this first work with first
Motivation arm 220 outer circumference surface projects outwardly of the second projection 221, and the first protruding 211 and second projection 221 is the most ringwise.Connect
Part 800 is made up of the connector 810 in cylindrical structural, and two end faces of connector 810 are along the axis direction of connector 810
Corresponding respectively offering the first mating holes 820 and the second mating holes 830, the first mating holes 820 is connected with the second mating holes 830
Logical, constitute shoulder hole, on connector 810, at the bottom of the hole of the second mating holes 830, form cooperation face 840.In processing dimension, second
The internal diameter of mating holes 830 is more than the internal diameter of the first mating holes 820；The diameter of the first projection 211 is straight more than the second projection 221
Footpath；The diameter of the second projection 221 is less than the second mating holes more than the internal diameter of the first mating holes 820, the diameter of the second projection 221
The internal diameter of 830.The periphery of the first projection 211 is provided with external screw thread, and the inwall of the second mating holes 830 is provided with protruding with first
The female thread that external screw thread on 211 matches.When connecting cooperation, the first movable horn 220 is allowed to have the one of the second projection 221
End is positioned at the second mating holes 830 of connector 810, and the other end of the first movable horn 220 is through the first mating holes 820；
After female thread in second mating holes 830 and the external screw thread in the first projection 211 match, due to, the diameter of the second projection 221
Less than the internal diameter of the second mating holes 830, therefore the end face of the second projection 221 can abut cooperation face 840, plays second protruding
221 are stuck in the effect in the second mating holes 830, and then have reached to further enhance first and fix horn 210 and the first moving machine
The effect of stability when arm 220 connects.
As Fig. 6, such as Fig. 7, as shown in Figure 8, first fix horn 210 connect end structure and second fix horn 310
Connect end structure identical；The structure connecting end of the first movable horn 220 and the knot connecting end of the second movable horn 320
Structure is identical；So identical power connector 510, the six core adapter 520 of convenient use and connector 800.Second horn 300
Mounting means and the mounting means of the first horn 200 identical: second fix between horn 310 and the second movable horn 320 logical
Crossing, second fixes between horn 310 and the second movable horn 320 by two power connectors 510 and six core adapters
520 are attached, and wherein, one end of two power connectors 510 fixes horn 310 with second or the second movable horn 320 connects
Connecing, the other end and the second movable horn 320 or the second are fixed horn 310 and are connected；Same, one end of six core adapters 520 with
Second fixes horn 310 or the second movable horn 320 connects, and the other end fixes horn 310 with the second activity horn 320 or the second
Connect.Additionally, second fixes and be attached also by connector 800 between horn 310 and the second movable horn 320, second is solid
Determining the on horn 310 the 3rd protruding 311 to threaded between connector 800, the 4th on the second movable horn 320 is protruding
It is connected together between 321 and connector 800.
As it is shown in figure 1, unmanned plane is in use, need the operation carrying out landing and taking off, when landing due to nothing
Man-machine have certain impulsive force, is therefore provided with undercarriage 800 on the second movable horn 320 and the first movable horn 220,
The cylindrical structure that undercarriage 800 is stepped, undercarriage 800 is arranged on the underface of paddle components 400.
As it is shown in figure 1, night people for convenience recognize the state of flight of unmanned plane, undercarriage 800 is equipped with
Display lamp 810, display lamp 810 color set on four undercarriages 800 all differs, and is so convenient for people to recognize whether out
Existing fault, display lamp 810 can be arranged on the outer circumference surface of undercarriage 800, it is also possible to is arranged on the cascaded surface of undercarriage 800
Place；In the present embodiment, display lamp 810 is arranged on the outer circumference surface on undercarriage 800, offers corresponding on undercarriage 800
Installing hole, convenient installation display lamp 810.
The brachium of the first horn 200 is between 1.3 times to 2.0 times of the brachium of the second horn 300, the brachium of the longest horn
Between 1.3 times to 2.0 times of the brachium of short horn, show that the brachium when the first horn 200 is the according to many experiments data
Being optimum during 1.5 times of the brachium of two horns 300, when 1.5 times, balance quality during unmanned plane during flying is best, and is prone to
Conversion flight attitude.
The brachium of the first horn 200 is between 2.71 times to 3.32 times of fuselage 100 diameter, obtains according to many experiments data
Go out when 2.94 times that the brachium of the first horn 200 is fuselage 100 diameter for optimum, it is possible in the flight ensureing that unmanned plane is enough
The most lower moment obtaining maximum.
Between 2 times to 5 times of the diameter of a diameter of first horn 200 of fuselage 100, draw according to many experiments data and work as
Being optimum during 3.19 times of the diameter of a diameter of first horn 200 of fuselage 100, package size is more reasonable.
Same, between 2 times to 5 times of the diameter of a diameter of second horn 300 of fuselage 100, according to many experiments number
According to being optimum when 3.19 times of the diameter of a diameter of second horn 300 drawn when fuselage 100, package size is more reasonable.
Between 2 times to 4 times that brachium is the first brachium fixing horn 210 of first movable horn 220.
The brachium and first of the first movable horn 220 fixes the multiple proportion of the brachium of horn 210 to junction stability
Impact, as shown in table 1.
Table 1
| The brachium and first of the first movable horn fixes the multiple proportion of the brachium of horn | Junction stability |
| 1.5 | Difference |
| 2 | Good |
| 2.7 | Good |
| 4 | Good |
| 5 | Difference |
Draw when the brachium of the first movable horn 220 is the first brachium fixing horn 210 according to many experiments data
Being optimum when 2.7 times, when 2.7 times, the first movable horn 220 and first fixes horn 210 by adapter 500 and connector
After 600 connect, it is best that the first movable horn 220 and first fixes the stability between horn 210, the most also can reduce collection body
Long-pending.
Same, the brachium of the second movable horn 320 is between 2 times to 4 times of the second brachium fixing horn 310.
The brachium and second of the second movable horn 320 fixes the multiple proportion of the brachium of horn 310 to junction stability
Impact, as shown in table 2.
Table 2
Draw when the brachium of the second movable horn 320 is the second brachium fixing horn 310 according to many experiments data
Being optimum when 2.7 times, when 2.7 times, the second movable horn 320 and second fixes horn 310 by adapter 500 and connector
After 600 connect, it is best that the second movable horn 320 and second fixes the stability between horn 310, the most also can reduce collection body
Long-pending.
Additionally, maximum by fuselage 100 is arranged to mid diameter, the diameter at two ends is the reduction of line style, and fuselage 100
The diameter of left end is more than the diameter of fuselage 100 right-hand member, and the second horn 300 is arranged on the both sides of fuselage 100 left end, the first horn
200 both sides being arranged on fuselage 100 right-hand member, and 2.71 times that the brachium of the first horn 200 is fuselage 100 diameter are to 3.32 times
Between, the brachium of the first horn 200 is between 1.3 times to 2.0 times of the brachium of the second horn 300, a diameter of the of fuselage 100
Between 2 times to 5 times of the diameter of one horn 200, between 2 times to 5 times of the diameter of a diameter of second horn 300 of fuselage 100,
This structure makes the center of gravity of unmanned plane can be between integral forward lead 15mm-25mm, after overall center of gravity reach, convenient installs electricity
Pond, and the control that flies of unmanned plane can be modified in certain limit, thus expand the range of unmanned plane.
Many rotor wing unmanned aerial vehicles of the present invention, by utilizing adapter 500 by the first horn 200 and the second horn
It is attached between 300 and fuselage 100, fast assembling-disassembling can not only be accomplished, and in disassembly process, eliminate the worry of wiring,
Be simultaneously connected with device 500 be capable of in swapping process fast accurate to insert, overall structure is simple.
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. rotor wing unmanned aerial vehicle more than a kind, it is characterised in that include fairshaped fuselage (100) in strip, on described fuselage (100)
It is provided with multiple the first horn (200) being symmetric relative to the symmetrical plane in described fuselage (100) and the second horn
(300), each first horn (200) and each second horn (300) are equipped with blade group away from one end of described fuselage (100)
Part (400)；Described first horn (200) includes that first fixes horn (210) and the first movable horn (220), described second machine
Arm (300) includes that second fixes horn (310) and the second movable horn (320), and described first fixes horn (210) and second admittedly
Determine horn (310) all one-body molded with described fuselage (100)；Described first fixes horn (210) and the first movable horn (220)
Between and described second fix and all connected into by some adapters (500) between horn (310) and the second movable horn (320)
Integrally；Described first fixes between horn (210) and the first movable horn (220) and described second fixes horn (310) and the
The most all linked into an integrated entity by connector (600) between two movable horns (320)；Described first fixes horn (210) with described
Between connector (600) threaded, described second fixes and threadeds between horn (310) with described connector (600)；Institute
Stating and be connected together between the first movable horn (220) and described connector (600), the described second movable horn (320) is with described
Connector is connected together between (600).
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that described first fixes horn (210) far
Disembark one end of body (100) is provided with and first fixes horn (210) outer circumference surface from this and project outwardly of first protruding (211)；Institute
State the first movable horn (220) to fix one end that horn (210) is connected with first and be provided with from this first activity horn (220) outward
Periphery projects outwardly of second protruding (221)；Described second fix horn (310) away from one end of fuselage (100) be provided with from
This second is fixed horn (310) outer circumference surface and projects outwardly of the 3rd protruding (311)；Described second movable horn (320) and the
Two fix one end that horn (310) is connected is provided with that to project outwardly of the 4th from this second movable horn (320) outer circumference surface convex
Rise (321)；Described first protruding (211) are equivalently-sized with the 3rd protruding (311), and described second protruding (221) are convex with the 4th
Play the equivalently-sized of (321)；It is equipped with external thread section on the periphery of described first protruding (211) and the 3rd protruding (311)；Institute
State connector (600) and include the connector (610) of cylindrical structural；Described connector (610) is provided with first along axis direction
Mating holes (620) and the second mating holes (630)；Described first mating holes (620) is connected with the second mating holes (630) and constitutes rank
Ladder hole；At described connector (610) upper formation cooperation face (640) at the bottom of the hole of described second mating holes (630)；Join described second
The inwall closing hole (630) is provided with the internal thread segment matched with the external thread section on described first protruding (211)；Described connection
After part (600) is threadeded with described first protruding (211) or the 3rd protruding (311), described second protruding (220) or the 4th convex
The end face playing (320) is connected on described cooperation face (640).
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that the brachium of described first horn (200)
Between 1.3 times to 2.0 times of the brachium of described second horn (300).
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that the brachium of described first horn (200)
Between 2.71 times to 3.32 times of fuselage (100) diameter.
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that a diameter of the of described fuselage (100)
Between 2 times to 5 times of the diameter of one horn (200)；2 times of the diameter of a diameter of second horn (300) of described fuselage (100)
Between 5 times.
The many rotor wing unmanned aerial vehicles of one the most according to claim 1, it is characterised in that described paddle components (400) includes peace
It is contained in the motor on the described first movable horn (220) or the second movable horn (320) and is connected to the output shaft of described motor
On blade (410), the rotation axis of every a piece of blade (410) is respectively positioned on the same face of cylinder.
The many rotor wing unmanned aerial vehicles of one the most according to claim 2, it is characterised in that described second mating holes (630) interior
Footpath is more than the internal diameter of described first mating holes (620)；The diameter of described first protruding (211) is more than described second protruding (221)
Diameter；The diameter of described second protruding (221) is more than the internal diameter of described first mating holes (620), described second protruding (221)
Diameter less than the internal diameter of described second mating holes (630).
The many rotor wing unmanned aerial vehicles of one the most according to claim 2, it is characterised in that the excircle of described connector (610)
Face is provided with anti-slip veins.
The many rotor wing unmanned aerial vehicles of one the most according to claim 1 and 2, it is characterised in that the described first movable horn (220)
2 times to 4 times that brachium is the described first brachium fixing horn (210) between；The brachium of the described second movable horn (320)
Between 2 times to 4 times of the described second brachium fixing horn (310).
The many rotor wing unmanned aerial vehicles of one the most according to claim 1 and 2, it is characterised in that the described first movable horn
(220) end of and the second movable horn (320) is equipped with undercarriage (800)；Described undercarriage (800) is tied in cylindrical
Structure, described undercarriage 800 is provided with display lamp (810).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610472073X | 2016-06-23 | ||
| CN201610472073 | 2016-06-23 |
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| CN106081059A true CN106081059A (en) | 2016-11-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610502437.4A Pending CN106081059A (en) | 2016-06-23 | 2016-06-29 | A kind of many rotor wing unmanned aerial vehicles |
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| Country | Link |
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| CN (1) | CN106081059A (en) |
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| CN107021224A (en) * | 2017-04-28 | 2017-08-08 | 深圳市轻准科技有限公司 | Hang down and throw howitzer unmanned plane |
| CN107161320A (en) * | 2017-04-28 | 2017-09-15 | 深圳思博航空科技有限公司 | Multi-rotor unmanned aerial vehicle horn contracting mechanism |
| CN107628224A (en) * | 2017-09-25 | 2018-01-26 | 安徽瓦尔特机械贸易有限公司 | A kind of unmanned plane |
| CN109070990A (en) * | 2017-12-28 | 2018-12-21 | 深圳市大疆创新科技有限公司 | Horn component and unmanned plane |
| CN110077571A (en) * | 2019-06-10 | 2019-08-02 | 山东蜂巢航空科技有限公司 | A kind of unmanned plane horn connection component and unmanned plane |
| CN111688906A (en) * | 2020-06-28 | 2020-09-22 | 深圳高度创新技术有限公司 | Contact type connecting device for unmanned aerial vehicle arm |
| CN111688907A (en) * | 2020-06-28 | 2020-09-22 | 深圳高度创新技术有限公司 | Blade type connecting device for unmanned aerial vehicle arm |
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Application publication date: 20161109 |