CN110001942A - A kind of removable quadrotor drone - Google Patents

A kind of removable quadrotor drone Download PDF

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Publication number
CN110001942A
CN110001942A CN201811524314.6A CN201811524314A CN110001942A CN 110001942 A CN110001942 A CN 110001942A CN 201811524314 A CN201811524314 A CN 201811524314A CN 110001942 A CN110001942 A CN 110001942A
Authority
CN
China
Prior art keywords
square type
mentioned
guide
type shell
seat
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
CN201811524314.6A
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Chinese (zh)
Inventor
不公告发明人
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Quanzhou Qimei Electronic Technology Co Ltd
Original Assignee
Quanzhou Qimei Electronic Technology Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Quanzhou Qimei Electronic Technology Co Ltd filed Critical Quanzhou Qimei Electronic Technology Co Ltd
Priority to CN201811524314.6A priority Critical patent/CN110001942A/en
Publication of CN110001942A publication Critical patent/CN110001942A/en
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/46—Bases; Cases
    • H01R13/502—Bases; Cases composed of different pieces
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/60—Means for supporting coupling part when not engaged
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/627—Snap or like fastening
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
    • H01R13/631—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for engagement only
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R13/00—Details of coupling devices of the kinds covered by groups H01R12/70 or H01R24/00 - H01R33/00
    • H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
    • H01R13/629—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances
    • H01R13/633—Additional means for facilitating engagement or disengagement of coupling parts, e.g. aligning or guiding means, levers, gas pressure electrical locking indicators, manufacturing tolerances for disengagement only
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01R—ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS
    • H01R24/00—Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure
    • H01R24/005—Two-part coupling devices, or either of their cooperating parts, characterised by their overall structure requiring successive relative motions to complete the coupling, e.g. bayonet type

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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)
  • Details Of Connecting Devices For Male And Female Coupling (AREA)

Abstract

The invention belongs to air vehicle technique fields, more particularly to a kind of removable quadrotor drone, it includes fuselage, with mounting mechanism, removable mechanism, rotor mechanism, when being wherein quickly equipped with mounting mechanism and removable mechanism, it needs for connector assembly to be correctly inserted into seat is received, the second square type shell could be inserted into first one end of square type shell far from fuselage far from one end of rotor mechanism after connector assembly enters and receives seat, otherwise seat is received connector assembly to be made to move down, seat is received to cannot be introduced into the second square type shell, and then the second square type shell can not be successfully and be inserted into the first square type shell；In connector assembly and after receiving seat to be correctly plugged, second corresponding one end of square type shell just can smoothly be protected in the corresponding port for being inserted into the first square type shell, ensure that after being quickly equipped with mounting mechanism and removable mechanism, the first electric wire and the second electric wire can be powered well；To eliminate the secondary trouble dismantled and checked.The configuration of the present invention is simple has preferable using effect.

Description

A kind of removable quadrotor drone
Technical field
The invention belongs to air vehicle technique field more particularly to a kind of removable quadrotor drones.
Background technique
It is simple by its structure, just to be widely used in commercial field, especially quadrotor drone for unmanned plane at present In operation, price is economical the features such as, become the mainstream in numerous unmanned planes.It stores or transports for the ease of quadrotor drone It is defeated, have existed a kind of quadrotor drone that can be convenient disassembly on the market now；It is not needed in quadrotor drone In use, the horn of quadrotor drone and rotor mechanism can integrally be removed；When need to use, then by quadrotor without Man-machine horn and rotor mechanism is quickly assembled on fuselage；But quadrotor drone now easy to disassemble is in quick assembling When, it is bad or do not have that the conducting wire of conducting wire and fuselage on horn and rotor mechanism sometimes will appear connection in quick assembling The problem of being fully connected, so as to cause the quadrotor drone cisco unity malfunction after quick assembling, it is also necessary to by quadrotor without Man-machine dismantle again assembles again, just more troublesome in this way.When in order to guarantee that horn and rotor mechanism are quickly assembled on fuselage, arm And the conducting wire on rotor mechanism is able to maintain the conducting wire good connection with fuselage always, so just needing one kind in quadrotor drone After quick assembling is good, do not need specially to check whether conducting wire connects good quadrotor drone.
The present invention design a kind of removable quadrotor drone solve the problems, such as it is as above.
Summary of the invention
To solve drawbacks described above in the prior art, the present invention discloses a kind of removable quadrotor drone, it is to adopt It is realized with following technical scheme.
In the description of the present invention, it should be noted that the indicating positions such as term "inner", "lower", "upper" or position are closed System be orientation based on the figure perhaps positional relationship or the invention product using when the orientation or position usually put Set relationship, it is only for convenient for the description present invention and simplify description, rather than the device or element of indication or suggestion meaning must There must be specific orientation, be constructed or operated with specific orientation, therefore be not considered as limiting the invention.In addition, art Language " first ", " second " etc. are only used for distinguishing description, are not understood to indicate or imply relative importance.
A kind of removable quadrotor drone, it is characterised in that: it includes fuselage, with mounting mechanism, removable mechanism, rotor Mechanism, the structure that the two sides of middle fuselage are installed is identical, for the wherein side of fuselage: two one end with mounting mechanism are symmetrical It is mounted on fuselage side；One end of two removable mechanisms is separately installed with a rotor mechanism, and the other end is matched with two respectively Mounting mechanism is matched far from one end of fuselage.
Above-mentioned rotor mechanism has motor and blade, and motor, which enables blade rotation to generate lift, flies quadrotor drone Row.
It is above-mentioned to match the first square type shell, the first sliding groove with perforation that mounting mechanism includes the first square type slot with perforation The first fixed block, the first sliding panel, A guide rail, the receiving seat with receiving channel, metal receiving tube, wherein the first square type shell One end is fixedly mounted on fuselage side；First fixed block is fixedly mounted in the first square type shell；Two A guide rails are symmetrically mounted on On the two sides groove face of first square type slot, and two A guide rails are located at the first square type shell phase and are connected in one end of fuselage and above-mentioned first solid Determine between block；One end of first sliding panel is snug fit between two A guide rails, and the other end is equipped with receiving seat；First sliding The first sliding groove that there is plate the one end for receiving seat to pass through the first fixed block, and seat is received to cannot be introduced into the first sliding groove； The one end of seat far from the first sliding panel is received to be flush with the first square type shell far from one end of fuselage；Three metal receiving tubes are uniform Ground is mounted in the receiving channel for receiving seat；One end of three the first electric wires enters respectively with three without the side of receiving channel from receiving seat A metal receiving tube is connected, and the other end passes through fuselage and connects with being electrically connected in fuselage.
Above-mentioned removable mechanism include the second square type shell of the second square type slot with perforation, the connector assembly with plug slot, Metal ferrule, square type cylinder, the second sliding panel, fixed plate and leaf spring, wherein one end of the second square type shell and above-mentioned rotor mechanism phase Even, the other end and the first square type shell form insertion far from one end of fuselage and cooperate；Two fixed plates are symmetrically mounted on the second square type In slot；Square type cylinder is mounted between two fixed plates in a manner of sliding up and down, and leaf spring makes square type cylinder and the second square type slot Upper groove surface fit；One end of second sliding panel is mounted in square type cylinder by way of being slidably matched, and the other end is equipped with Connector assembly；Three metal ferrules are uniformly mounted in the plug slot of connector assembly；One end of three the second electric wires from connector assembly without The side of plug slot enters to be connected with three metal ferrules respectively, and the other end passes through in the second square type slot and above-mentioned rotor mechanism Motor is mutually electrically connected.
When the upper groove surface of second square type slot of above-mentioned square type cylinder and the second square type shell fits, leaf spring is in compressive state, Connector assembly is located at one end outside of the second square type shell far from rotor mechanism, the side and second that connector assembly is connected with the second sliding panel The corresponding port surface of square type shell fits, and connector assembly cannot be introduced into the second square type shell.
Also there is position limiting structure, when the second square type shell is inserted into first far from one end of rotor mechanism in above-mentioned removable mechanism After square type shell is far from one end of fuselage, position-limit mechanism limits the second square type shell and the first square type shell simultaneously, the second square type shell without Method is detached from from the first square type shell.
As the further improvement of this technology, above-mentioned rotor mechanism further includes drive shaft and set casing, wherein above-mentioned second One end of square type shell is fixedly connected with set casing；Motor is fixedly mounted in set casing；One end of drive shaft and the motor shaft of motor It is connected, the other end is pierced by the top surface of set casing；Two above-mentioned blades are symmetrically mounted on one end that drive shaft is pierced by set casing top surface On periphery.
The second electric wire of above three passes through set casing far from one end of metal ferrule and is mutually electrically connected with motor.
As the further improvement of this technology, above-mentioned mounting mechanism of matching further includes A guide block, the first fixing seat, limited mouth, A bullet Spring, wherein above-mentioned first sliding panel is fixedly installed with the first fixing seat far from one end of receiving seat；The two sides pair of first fixing seat Claiming installation, there are two A guide blocks；Two A guide blocks are separately mounted in two A guide rails by way of being slidably matched；Two A springs One end be separately mounted on two A guide blocks, the other end is separately mounted on the inner wall of two A guide rails；Two A spring difference In two A guide rails.
The two sides of the above-mentioned one end of first square type shell far from fuselage symmetrically open that there are two the limited mouths penetrated through, and first is fixed Block is close to limited mouth.
The first electric wire of above three is mounted in the first fixing seat by way of compressing limit by three housing screws, and It is pierced by the circular hole of the first fixing seat；The same end of three the first electric wires passes through fuselage and connects with being electrically connected in fuselage, in addition The same end pass through above-mentioned first sliding panel respectively with receive seat on three metal receiving tubes be connected.
When the outer bottom seat surface and the first fixed block respective surfaces of receiving seat fit, the first fixing seat and fuselage outer surface Between three the first electric wires be in relaxed state, A spring is in the raw at this time.Such design is advantageous in that: being received Seat can be pulled out from the first square type shell under external force, pull out caused during receiving seat to the first electricity in order to prevent The damage of line, so the first sliding panel and the first fixing seat will be designed to move, and the first fixing seat and fuselage outer surface Between three the first electric wires be in relaxed state.The purpose slided between two A guide rails for the first sliding panel is: When receiving seat not by external force, the first sliding panel is smoothly located between two A guide rails in the first fixed block, avoids connecing Seat of receiving is stablized in the first square type shell；When receiving seat to pull out from the first square type shell, the first sliding panel can be smoothly two It slides between a A guide rail and in the first fixed block, the offset of appearance position when avoiding that seat is received to pull out from the first square type shell is protected Card insertion seat, which can facilitate insertion into, to be received in seat.
As the further improvement of this technology, above-mentioned removable mechanism further includes the second fixing seat, B guide groove, B guide block, second Sliding groove, C guide groove, limited block, C guide block, C spring, B spring, square hole, the second guide block, the second guide groove, wherein above-mentioned two fixation The opposite side of plate is provided with B guide groove, and two B guide grooves are symmetrical；The two sides of above-mentioned square type cylinder are symmetrically installed leads there are two B Block；Square type cylinder is located between two fixed plates, and two B guide blocks are separately mounted in two B guide grooves by way of being slidably matched； Institute's mounting structure is identical in two B guide grooves, and for wherein any one B guide groove: one end of two above-mentioned leaf springs is separately mounted to On corresponding B guide block lower surface, the other end is separately mounted on the lower groove face of B guide groove, and it is in B guide groove and right that two leaf springs are respectively positioned on Claim distribution.
When the upper groove surface of square type cylinder and the second square type slot of the second square type shell fits, B guide block is located at corresponding B guide groove Top, and corresponding leaf spring is in compressive state on B guide block；At this time since leaf spring is in compressive state, then connector assembly not When by external influence, square type cylinder can the upper groove surface always with the second square type slot of the second square type shell fit, and then guarantee insert Headstock cannot be introduced into the second square type shell.
There is third square type slot, the two sides of third square type slot are symmetrically opened there are two the second guide groove in above-mentioned square type cylinder；Square type The square hole of perforation is provided on the cylinder bottom surface in cylinder outside, and square hole is communicated with third square type slot；Above-mentioned second sliding panel is far from plug One end of seat is symmetrically installed there are two the second guide block；Second sliding panel is located in third square type slot far from one end of connector assembly, and Two the second guide blocks on second sliding panel are separately mounted in two the second guide grooves by way of being slidably matched；B spring One end is mounted on the second sliding panel far from one end of connector assembly, and the other end is mounted on the kerve face of third square type slot；B spring In the third square type slot of square type cylinder.
When the side port surface corresponding with the second square type shell that connector assembly and the second sliding panel are connected fits, and connector assembly When cannot be introduced into the second square type shell, the length that the second sliding panel stretches out square type cylinder reaches longest, and C spring is in nature at this time State.
Second fixing seat is fixedly mounted in the second square type slot of above-mentioned second square type shell, and the position of the second fixing seat is leaned on Nearly above-mentioned square type cylinder；The second electric wire of above three is mounted on the second fixing seat by way of compressing limit by three housing screws In, and it is pierced by the circular hole of the second fixing seat；The same end of three the second electric wires passes through in the second square type shell and rotor mechanism Motor is mutually electrically connected, and the same end in addition passes through three gold on the square hole, the second sliding panel and above-mentioned connector assembly of square type cylinder Belong to contact pin to be connected.
The second sliding groove penetrated through there are two symmetrically being opened on the groove face of above-mentioned second square type slot two sides, and the position of the second sliding groove Rest against the nearly one end of second square type shell far from rotor mechanism.
Institute's mounting structure and dependency structure are identical in the second sliding groove on the groove face of above-mentioned second square type slot two sides, for appointing One the second sliding groove of meaning: one end of limited block has the first inclined-plane and the second inclined-plane, and the two sides of the other end are symmetrically installed with two A C guide block；Limited block is mounted in the second sliding groove by way of being slidably matched；Two C guide blocks pass through the side being slidably matched Formula is mounted in corresponding two C guide grooves；One end of two C springs is separately mounted on two C guide blocks, and the other end is installed respectively On the side channel face of two C guide grooves, two C springs are located in two C guide grooves.
As the further improvement of this technology, above-mentioned C spring is compressed spring；When limited block is not affected by external force, Corresponding C spring is not affected by compression, the one end of limited block far from the first inclined-plane to corresponding second sliding groove and the second square type slot phase There are spacing between notch at even.It is such designed for: be squeezed in limited block and to the center of the second square type When line direction is mobile, one end due to limited block far from the first inclined-plane to corresponding second sliding groove and the second square type slot connecting place There are spacing between notch, the one end of limited block far from the first inclined-plane will not be pierced by the second sliding groove and enter the second square type slot In, movement interference when the second square type slot is entered to receiving seat so as to avoid limited block.
As the further improvement of this technology, the side being connected in above-mentioned limited block with the second inclined-plane is named as lateral part surface； Two limited blocks of above-mentioned second square type shell mutually limit cooperation with two limiting cuttings of above-mentioned first square type shell respectively；When second During square type shell is inserted into first one end of square type shell far from fuselage far from one end of rotor mechanism, the first square type shell is separate One end of fuselage can squeeze the first inclined-plane of limited block, and the first inclined-plane enables limited block to be extruded to the first of the first square type shell In square type slot；When limited block is inserted into corresponding limiting cutting, the lateral part surface of limited block is located in corresponding limiting cutting, And there is limited block the one end on the first inclined-plane to be pierced by corresponding limiting cutting.
As the further improvement of this technology, the two sides of the receiving channel of above-mentioned receiving seat are symmetrically opened there are two the first guide groove； One elastic bumps is installed on the side channel face of each guide groove；The two sides of above-mentioned connector assembly are symmetrically installed leads there are two first Block；Two the first guide blocks are slidably matched with two the first guide groove formation respectively；Two the first guide blocks respectively with two the first guide grooves In elastic bumps phase extrusion fit.First guide block and the first guide groove form the effect of being slidably matched: connector assembly is being inserted into receiving Seat receiving channel when, two the first guide blocks can be inserted respectively into two the first guide grooves, the first guide block of two such it is ensured that It receives seat can be steady and is correctly inserted into the receiving channel for receiving seat.
As the further improvement of this technology, above-mentioned elastic bumps are made of rubber material.
As the further improvement of this technology, states and seat is received to be made of insulating material；Above-mentioned metal receiving tube is by copper product It is made.
As the further improvement of this technology, above-mentioned connector assembly is made of insulating material；Above-mentioned metal ferrule is copper product It is made.
The design of A guide block and A spring is: A guide block can guarantee that the first fixing seat can be steady between two A guide rails Sliding, and then guarantee the first sliding panel can between two A guide rails smooth sliding, moreover it is possible to prevent the first fixing seat and first sliding Movable plate is detached from between two A guide rails.When the first fixing seat is mobile to the direction of the first fixed block, first is followed in A guide block In fixing seat motion process, A spring is stretched；After the first fixing seat is no longer influenced by the effect of external force pulling, the reset of A spring So that A guide block drives the first fixing seat is mobile to reset.
The design of B guide block and leaf spring is: above and below B guide block can guarantee square type cylinder between two fixed plates smoothly Sliding, moreover it is possible to square type cylinder be prevented to be detached from between two fixed plates.When square type cylinder moves down, B guide block follows square type cylinder to transport Dynamic, leaf spring continuation is compressed；After square type cylinder, which is no longer influenced by external force, to be pushed, the reset of leaf spring so that B guide block drive square type cylinder to Upper mobile reset.
The design of second guide block and B spring is: the second guide block can guarantee that the second sliding panel is steady in square type cylinder Sliding, moreover it is possible to prevent the second sliding panel to be detached from from square type cylinder.When the second sliding panel is mobile to the center position of square type cylinder, B spring is compressed；After the second sliding panel, which is no longer influenced by external force, to be squeezed, the reset of B spring is so that the mobile reset of the second sliding panel.
The design of C guide block and C spring is: C guide block can guarantee that corresponding limited block can be in corresponding second sliding It is smoothly slided in slot, moreover it is possible to corresponding limited block be prevented to be detached from from corresponding second sliding groove.When limited block is to the second square When the direction of shell center line is mobile, followed in limited block motion process in C guide block, C spring is compressed；When limit plate no longer by After the effect squeezed to external force, the reset of C spring is so that C guide block drives limited block is mobile to reset.
Three the first electric wires being located in the first sliding panel in the present invention, are installed in the first sliding panel, in this way When receiving seat to be pulled out by external force, three the first electric wires in mainly the first sliding panel bear main pulling force, avoid three First electric wire and the tie point of three metal receiving tubes are drawn bad.
Relative to traditional removable quadrotor drone, beneficial effects of the present invention:
1, structure is simple, convenient disassembly, and quick assembling avoids in just needing for connector assembly and receiving seat to be correctly inserted into before It is bad or the problem of be not fully connected to occur electric wire connection when quick assembling.
2, it needs for connector assembly to be correctly inserted into seat is received, it could be by the second square type after connector assembly enters and receives seat Shell is inserted into the first square type shell far from one end of fuselage far from one end of rotor mechanism, otherwise receive seat will not make connector assembly to Lower movement receives seat to cannot be introduced into the second square type shell, and then the second square type shell can not be successfully and be inserted into the first square type shell； In connector assembly and after receiving seat to be correctly plugged, second corresponding one end of square type shell just can smoothly protect the phase for being inserted into the first square type shell It answers in port, ensure that after being quickly equipped with mounting mechanism and removable mechanism, the first electric wire and the second electric wire can be powered well；To Eliminate the secondary trouble dismantled and checked.
3, receiving seat of the invention and connects when carrying out quick assembling all in that can pull out the first square type shell convenient for user Seat of receiving also continues maintain the state parallel with the first square type shell center line after pulling out, user very convenient in this way is by plug Seat to be inserted into receive seat in；In addition, due to receiving seat and connector assembly that can be in the first square type shell and the second square type shell respectively Outside, then occurring receiving the metal receiving tube in seat or the metal ferrule failure in connector assembly to be also convenient for more when damaging It changes, avoids that the trouble of repairing will be disassembled completely with mounting mechanism or removable mechanism.
Detailed description of the invention
Fig. 1 is unmanned plane global facility schematic diagram.
Fig. 2 is the scheme of installation of rotor mechanism.
Fig. 3 is the diagrammatic cross-section of rotor mechanism.
Fig. 4 is the perspective diagram with mounting mechanism.
Fig. 5 is the diagrammatic cross-section with mounting mechanism.
Fig. 6 is the diagrammatic cross-section of the first square type shell.
Fig. 7 is the installation diagrammatic cross-section of A guide block.
Fig. 8 is the scheme of installation of the first fixing seat.
Fig. 9 is the first fixing seat schematic diagram that three the first electric wires is fixed.
Figure 10 be three the first electric wires respectively with the diagrammatic cross-section of three metal receiving tubes being connected.
Figure 11 is the installation diagrammatic cross-section of the first sliding panel.
Figure 12 is the diagrammatic cross-section for receiving seat.
Figure 13 is the perspective diagram of removable mechanism.
Figure 14 is part section (one) schematic diagram of Figure 13.
Figure 15 is part section (two) schematic diagram of Figure 13.
Figure 16 is installation section (one) schematic diagram of fixed plate and the second fixing seat.
Figure 17 is the installation diagrammatic cross-section of fixed plate.
Figure 18 is the perspective diagram that B guide block and B guide groove are slidably matched.
Figure 19 is the diagrammatic cross-section of square type cylinder.
Figure 20 is the diagrammatic cross-section that the second sliding panel slides on square type cylinder.
Figure 21 is the second fixing seat schematic diagram that three the second electric wires is fixed.
Figure 22 is the scheme of installation of connector assembly.
Figure 23 be three the second electric wires respectively with the diagrammatic cross-section of three metal ferrules being connected.
Figure 24 is the schematic diagram of institute's mounting structure on limited block.
Figure 25 is the installation section schematic top plan view of C guide block.
Figure 26 is the schematic diagram that limited block is matched with corresponding limited mouth.
Figure label title: 1, fuselage；2, match mounting mechanism；3, removable mechanism；4, rotor mechanism；5, blade；6, drive shaft； 7, set casing；8, motor；10, the first square type shell；12, limited mouth；13, seat is received；14, the first fixed block；16, first is fixed Seat；17, the first electric wire；18, A guide rail；19, the first sliding groove；20, A guide block；21, A spring；22, the first sliding panel；23, it receives Slot；24, the first guide groove；25, elastic bumps；26, metal receiving tube；27, housing screw；28, wedge angle；29, the first square type slot； 30, the second square type shell；31, the second square type slot；32, connector assembly；34, the second sliding groove；35, C guide groove；39, the second electric wire；40, Second fixing seat；41, the first guide block；42, metal ferrule；43, limited block；44, C guide block；45, C spring；46, the first inclined-plane； 47, the second inclined-plane；48, side is kept off；49, plug slot；50, fixed plate；51, B guide groove；52, B guide block；53, leaf spring；54, square type Cylinder；55, third square type slot；56, the second guide groove；57, square hole；58, the second sliding panel；59, the second guide block；60, B spring.
Specific embodiment
As shown in Figure 1, it includes fuselage 1, with mounting mechanism 2, removable mechanism 3, rotor mechanism 4, as shown in Figure 1, wherein machine The structure that the two sides of body 1 are installed is identical, for the wherein side of fuselage 1: two one end with mounting mechanism 2 are symmetrically mounted on machine On 1 side of body；One end of two removable mechanisms 3 is separately installed with a rotor mechanism 4, and the other end matches mounting mechanism with two respectively 2 one end far from fuselage 1 match.
As shown in Fig. 2, above-mentioned rotor mechanism 4 has motor 8 and blade 5, motor 8, which makes the rotation of blade 5 generate lift, makes four Rotor wing unmanned aerial vehicle can fly.
As shown in Figure 4,5, above-mentioned to match the first square type shell 10, tool that mounting mechanism 2 includes the first square type slot 29 with perforation There are the first fixed block 14 of the first sliding groove 19 of perforation, the first sliding panel 22, A guide rail 18, as shown in figure 11, there is receiving channel 23 receiving seat 13, metal receiving tube 26, as shown in Fig. 1,4, wherein one end of the first square type shell 10 is fixedly mounted on 1 side of fuselage On face；As shown in figure 5, the first fixed block 14 is fixedly mounted in the first square type shell 10；As shown in fig. 6, two A guide rails 18 are symmetrical It is mounted on the two sides groove face of the first square type slot 29, and two A guide rails 18 are located at one end that the first square type shell 10 is connected in fuselage 1 Between above-mentioned first fixed block 14；As shown in Fig. 5,8, one end of the first sliding panel 22 be snug fit at two A guide rails 18 it Between, the other end, which is equipped with, receives seat 13；As shown in figure 11, the first sliding panel 22 there is the one end for receiving seat 13 to pass through first fixed First sliding groove 19 of block 14, and seat 13 is received to cannot be introduced into the first sliding groove 19；As shown in figure 5, receiving seat 13 separate One end of first sliding panel 22 is flush with the first square type shell 10 far from one end of fuselage 1；As shown in Figure 11,12, three metals Receiving tube 26 is uniformly mounted in the receiving channel 23 for receiving seat 13；As shown in Figures 9 and 10, one end of three the first electric wires 17 from It receives seat 13 to enter without the side of receiving channel 23 to be connected with three metal receiving tubes 26 respectively, the other end passes through fuselage 1 and fuselage 1 Interior being electrically connected connects.
As shown in Figure 13,14,15, above-mentioned removable mechanism 3 includes the second square type shell of the second square type slot 31 with perforation 30, as shown in figure 22, with connector assembly 32, metal ferrule 42, square type cylinder 54, the second sliding panel 58, such as Figure 18 of plug slot 49 It is shown, fixed plate 50 and leaf spring 53, as shown in Fig. 3,13, wherein one end of the second square type shell 30 is connected with above-mentioned rotor mechanism 4, As shown in Figure 1, the other end and the first square type shell 10 form insertion cooperation far from one end of fuselage 1；As shown in Figure 14,15, two Fixed plate 50 is symmetrically mounted in the second square type slot 31；As shown in Figure 14,15, square type cylinder 54 is mounted in a manner of sliding up and down Between two fixed plates 50, and leaf spring 53 makes square type cylinder 54 and the upper groove surface of the second square type slot 31 fit；Second sliding panel 58 one end is mounted in square type cylinder 54 by way of being slidably matched, and the other end is equipped with connector assembly 32；Such as Figure 22,23 institutes Show, three metal ferrules 42 are uniformly mounted in the plug slot 49 of connector assembly 32；One end of three the second electric wires 39 is from plug 32 sides without plug slot 49 of seat enter and are connected respectively with three metal ferrules 42, the other end across the second square type slot 31 with it is above-mentioned 8 phase of motor electrical connection in rotor mechanism 4.
As shown in Figure 14,15, the upper groove surface of above-mentioned square type cylinder 54 and the second square type slot 31 of the second square type shell 30 fits When, leaf spring 53 is in compressive state, and connector assembly 32 is located at one end outside of the second square type shell 30 far from rotor mechanism 4, connector assembly The 32 side port surfaces corresponding with the second square type shell 30 being connected with the second sliding panel 58 fit, and connector assembly 32 cannot be introduced into Into the second square type shell 30.
Also there is position limiting structure, when the second square type shell 30 is inserted into far from one end of rotor mechanism 4 in above-mentioned removable mechanism 3 Behind first one end of square type shell 10 far from fuselage 1, position-limit mechanism limits the second square type shell 30 and the first square type shell 10 simultaneously, the Two square type shells 30 can not be detached from from the first square type shell 10.
As shown in Figure 2,3, above-mentioned rotor mechanism 4 further includes drive shaft 6 and set casing 7, as shown in Fig. 2, wherein above-mentioned One end of two square type shells 30 is fixedly connected with set casing 7；As shown in figure 3, motor 8 is fixedly mounted in set casing 7；Drive shaft 6 One end is connected with 8 axis of motor of motor 8, and the other end is pierced by the top surface of set casing 7；Two above-mentioned blades 5 are symmetrically mounted on driving Axis 6 is pierced by one end periphery of 7 top surface of set casing.
The second electric wire of above three 39 passes through set casing 7 far from one end of metal ferrule 42 and is electrically connected with 8 phase of motor.
As shown in Figure 6,7, above-mentioned with mounting mechanism 2 further includes A guide block 20, the first fixing seat 16, limited mouth 12, A spring 21, As shown in figure 8, wherein the separate one end for receiving seat 13 of above-mentioned first sliding panel 22 is fixedly installed with the first fixing seat 16；Such as Fig. 9 Shown, the two sides of the first fixing seat 16 are symmetrically installed there are two A guide block 20；As shown in fig. 7, two A guide blocks 20 are matched by sliding The mode of conjunction is separately mounted in two A guide rails 18；One end of two A springs 21 is separately mounted on two A guide blocks 20, another End is separately mounted on the inner wall of two A guide rails 18；Two A springs 21 are located in two A guide rails 18.
As shown in fig. 6, the two sides of above-mentioned first square type shell, 10 one end far from fuselage 1 are symmetrically opened, there are two the limits penetrated through Mouth 12, and the first fixed block 14 is close to limited mouth 12.
As shown in figure 9, the first electric wire of above three 17 is mounted on by way of compressing limit by three housing screws 27 In first fixing seat 16, and it is pierced by the circular hole of the first fixing seat 16；The same end of three the first electric wires 17 passes through fuselage 1 and machine Being electrically connected in body 1 connects, as shown in Figures 9 and 10, other the same end pass through above-mentioned first sliding panel 22 respectively with receive seat 13 On three metal receiving tubes 26 be connected.
As shown in figure 5, first is fixed when the outer bottom seat surface and 14 respective surfaces of the first fixed block of receiving seat 13 fit Three the first electric wires 17 between seat 16 and 1 outer surface of fuselage are in relaxed state, and A spring 21 is in the raw at this time.This The design of sample is advantageous in that: being received seat 13 that can pull out from the first square type shell 10 under external force, is pulled out in order to prevent The damage to the first electric wire 17 is caused during receiving seat 13, so the first sliding panel 22 and the first fixing seat 16 will be designed to It can move, and three the first electric wires 17 between 1 outer surface of the first fixing seat 16 and fuselage are in relaxed state.For first The purpose that sliding panel 22 slides between two A guide rails 18 is: when receiving seat 13 not by external force, the first sliding panel 22 are smoothly located between two A guide rails 18 and in the first fixed block 14, avoid that seat 13 is received to stablize in the first square type shell 10 In；When receiving seat 13 to pull out from the first square type shell 10, the first sliding panel 22 can be smoothly between two A guide rails 18 and the It is slided in one fixed block 14, the offset of appearance position when avoiding that seat 13 is received to pull out from the first square type shell 10 guarantees insertion seat It can facilitate insertion into and receive in seat 13.
As shown in Figure 14,16,19,20, above-mentioned removable mechanism 3 further include the second fixing seat 40, B guide groove 51, B guide block 52, Second sliding groove 34, C guide groove 35, limited block 43, C guide block 44, C spring 45, B spring 60, square hole 57, the second guide block 59, second Guide groove 56, as shown in Figure 16,17, wherein the opposite side of above-mentioned two fixed plate 50 is provided with B guide groove 51, and two B guide grooves 51 is symmetrical；As shown in figure 19, the two sides of above-mentioned square type cylinder 54 are symmetrically installed there are two B guide block 52；As shown in figure 14, square type cylinder 54 are located between two fixed plates 50, and as shown in figure 18, two B guide blocks 52 are separately mounted to two by way of being slidably matched In B guide groove 51；As shown in figure 18, institute's mounting structure is identical in two B guide grooves 51, for wherein any one B guide groove 51: as schemed Shown in 18, one end of two above-mentioned leaf springs 53 is separately mounted on corresponding 52 lower surface of B guide block, and the other end is separately mounted to B On the lower groove face of guide groove 51, two leaf springs 53 are respectively positioned in B guide groove 51 and symmetrical.
As shown in figure 15, when the upper groove surface of square type cylinder 54 and the second square type slot 31 of the second square type shell 30 fits, such as Shown in Figure 18, B guide block 52 is located at the top of corresponding B guide groove 51, and corresponding leaf spring 53 is in compressive state on B guide block 52；This When compressive state is in due to leaf spring 53, then when connector assembly 32 is not affected by external influence, square type cylinder 54 can be always with second The upper groove surface of second square type slot 31 of square type shell 30 fits, and then guarantees that connector assembly 32 cannot be introduced into the second square type shell 30 In.
As shown in figure 19, there is third square type slot 55, the two sides of third square type slot 55 are symmetrically provided in above-mentioned square type cylinder 54 Two the second guide grooves 56；The square hole 57 of perforation, and square hole 57 and third square type slot 55 are provided on the cylinder bottom surface in 54 outside of square type cylinder It communicates；As shown in Figure 22,23, above-mentioned second sliding panel 58 is symmetrically installed far from one end of connector assembly 32 there are two the second guide block 59；As shown in Figure 20,21, the second sliding panel 58 is located in third square type slot 55 far from one end of connector assembly 32, and the second sliding Two the second guide blocks 59 on plate 58 are separately mounted in two the second guide grooves 56 by way of being slidably matched；B spring 60 One end is mounted on second one end of sliding panel 58 far from connector assembly 32, and the other end is mounted on the kerve face of third square type slot 55 On；B spring 60 is located in the third square type slot 55 of square type cylinder 54.
As shown in figure 15, when the side port corresponding with the second square type shell 30 that connector assembly 32 is connected with the second sliding panel 58 Face fits, and when connector assembly 32 be cannot be introduced into the second square type shell 30, and as shown in figure 20, the second sliding panel 58 stretches out square type The length of cylinder 54 reaches longest, and C spring 45 is in the raw at this time.
As shown in figure 16, the second fixing seat 40 is fixedly mounted in the second square type slot 31 of above-mentioned second square type shell 30, and Second fixing seat 40 is located proximate to above-mentioned square type cylinder 54；As shown in figure 21, the second electric wire of above three 39 is by three compression spiral shells Nail 27 is mounted in the second fixing seat 40 by way of compressing limit, and is pierced by the circular hole of the second fixing seat 40；Three The same end of two electric wires 39 passes through the second square type shell 30 and is electrically connected with 8 phase of motor in rotor mechanism 4, as shown in figure 23, separately Outer the same end passes through square hole 57, the second sliding panel 58 and three 42 phases of metal ferrule on above-mentioned connector assembly 32 of square type cylinder 54 Even.
As shown in Figure 16,17, symmetrically opened on above-mentioned second square type slot, 31 two sides groove face there are two penetrate through the second sliding groove 34, and the second sliding groove 34 is located proximate to second one end of square type shell 30 far from rotor mechanism 4.
Institute's mounting structure and dependency structure are identical in the second sliding groove 34 on above-mentioned second square type slot, 31 two sides groove face, right In any one the second sliding groove 34: as shown in figure 24, one end of limited block 43 has the first inclined-plane 46 and the second inclined-plane 47, separately The two sides of one end are symmetrically installed there are two C guide block 44；As shown in figure 25, limited block 43 is mounted on by way of being slidably matched In two sliding grooves 34；Two C guide blocks 44 are mounted in corresponding two C guide grooves 35 by way of being slidably matched；Two C springs 45 one end is separately mounted on two C guide blocks 44, and the other end is separately mounted on the side channel face of two C guide grooves 35, two C bullets Spring 45 is located in two C guide grooves 35.
As shown in figure 25, above-mentioned C spring 45 is compressed spring；When limited block 43 is not affected by external force, corresponding C bullet Spring 45 is not affected by compression, the one end of limited block 43 far from the first inclined-plane 46 to corresponding second sliding groove 34 and 31 phase of the second square type slot There are spacing between notch at even.It is such designed for: be squeezed in limited block 43 and into the second square type When heart line direction is mobile, one end due to limited block 43 far from the first inclined-plane 46 to corresponding second sliding groove 34 and the second square type slot There are spacing between the notch of 31 connecting places, limited block 43 far from the one end on the first inclined-plane 46 will not be pierced by the second sliding groove 34 and It enters in the second square type slot 31, movement when receiving seat 13 to enter the second square type slot 31 so as to avoid 43 pairs of limited block is dry It relates to.
As shown in figure 24, the side being connected in above-mentioned limited block 43 with the second inclined-plane 47 is named as lateral part surface；Above-mentioned second Two limiting cuttings of two limited blocks 43 of square type shell 30 respectively with above-mentioned first square type shell 10 mutually limit cooperation；In Figure 26 (a) shown in, when the second square type shell 30 is inserted into first one end of square type shell 10 far from fuselage 1 far from one end of rotor mechanism 4 In the process, first one end of square type shell 10 far from fuselage 1 can squeeze the first inclined-plane 46 of limited block 43, and the first inclined-plane 46 to limit Position block 43 can be extruded in the first square type slot 29 of the first square type shell 10；In Figure 26 shown in (b), when limited block 43 is inserted into When in corresponding limiting cutting, the lateral part surface of limited block 43 is located in corresponding limiting cutting, and limited block 43 is oblique with first The one end in face 46 is pierced by corresponding limiting cutting.
As shown in Figure 11,12, the two sides of the receiving channel 23 of above-mentioned receiving seat 13 are symmetrically opened there are two the first guide groove 24；It is each One elastic bumps 25 is installed on the side channel face of a guide groove；As shown in figure 22, the two sides of above-mentioned connector assembly 32 are symmetrically installed with Two the first guide blocks 41；Two the first guide blocks 41 are slidably matched with two the first guide groove 24 formation respectively；Two the first guide blocks 41 Respectively with the 25 phase extrusion fit of elastic bumps in two the first guide grooves 24.First guide block 41 and the first guide groove 24 form sliding and match Cooperation is used: for connector assembly 32 when being inserted into the receiving channel 23 for receiving seat 13, two the first guide blocks 41 can be inserted respectively into two the In one guide groove 24, the first guide block of two such 41 is it is ensured that receiving seat 13 can be steady and being correctly inserted into connecing for receiving seat 13 It receives in slot 23.
Above-mentioned elastic bumps 25 are made of rubber material.
It states and seat 13 is received to be made of insulating material；Above-mentioned metal receiving tube 26 is made of copper product.
Above-mentioned connector assembly 32 is made of insulating material；Above-mentioned metal ferrule 42 is made of copper product.
Quadrotor drone of the invention can fly in the sky, hover to execute particular task；Such as: fly, monitor, Delivery takes photo by plane, sprays insecticide.Quadrotor drone can carry scheduled functional module, such as: sensor, equipment of taking photo by plane, Freight house etc., to realize specific function.
Fuselage 1 in the present invention is the load-bearing part of quadrotor drone, can carry biography on fuselage 1 or inside fuselage 1 The elements such as sensor, circuit board, middle control processor, communication module, battery.1 shell of fuselage in the present invention is streamlined, can subtract Windage when small flight.By the adjusting to four rotor mechanisms 4, quadrotor drone of the invention can be made to realize The movement such as winged, smooth flight, landing.
Workflow of the invention: idle and removable mechanism 3 is in quadrotor drone of the invention and has been disassembled In the case where, with the state in mounting mechanism 2 and removable mechanism 3 are as follows:
With mounting mechanism 2: as shown in figure 5, the outer bottom seat surface of seat 13 is received to fit with 14 respective surfaces of the first fixed block, the Three the first electric wires 17 between 1 outer surface of one fixing seat 16 and fuselage are in relaxed state, and A spring 21 is in nature shape at this time State.
Removable mechanism 3: as shown in Figure 14,15, the upper groove surface of the second square type slot 31 of square type cylinder 54 and the second square type shell 30 When fitting, leaf spring 53 is in compressive state, and connector assembly 32 is located at one end outside of the second square type shell 30 far from rotor mechanism 4, Connector assembly 32 fits with the side port surface corresponding with the second square type shell 30 that the second sliding panel 58 is connected, and 32 nothing of connector assembly Method enters in the second square type shell 30；As shown in figure 25, limited block 43 is not affected by external force, and corresponding C spring 45 is not affected by Compression, the notch of the one end of limited block 43 far from the first inclined-plane 46 to 31 connecting place of corresponding second sliding groove 34 and the second square type slot Between there are spacing.
When removable mechanism 3 needs are quickly assembled to mounting mechanism 2, the process of quick assembling: user will receive seat 13 The parallel pull-out from the second square type shell 30, the first sliding panel 22, which follows, receives seat 13 to move, and the first fixing seat 16 follows first Sliding panel 22 moves, and A guide block 20 follows the first fixing seat 16 to move, and A spring 21 is stretched.User will receive seat 13 and plug Seat 32 is aligned, and receives seat 13 mobile to 32 direction of connector assembly, and connector assembly 32 is inserted into and is received in seat 13.Connector assembly 32 exists During being inserted into the receiving channel 23 for receiving seat 13, two the first guide blocks 41 can be inserted respectively into two the first guide grooves 24, The first guide block of two such 41 is it is ensured that receiving seat 13 can be steady and being correctly inserted into the receiving channel 23 for receiving seat 13；It inserts Three metal ferrules 42 in headstock 32 are inserted respectively into three metal receiving tubes 26 for receiving seat 13；When connector assembly 32 is close When receiving the bottom of the receiving channel 23 of seat 13, sliding of first guide block 41 in corresponding first guide groove 24 can squeeze and cross first Rubber bumps in guide groove 24；When connector assembly 32 is located at the bottom for receiving the receiving channel 23 of seat 13, three metal ferrules 42 divide It is not completely inserted into three metal receiving tubes 26, the first guide block 41 goes just past the rubber bumps in the first guide groove 24, at this time Rubber bumps can play the role of the first guide block 41 the first guide block 41 is prevented to be not easily disconnected from from the first guide groove 24, so that Connector assembly 32 will not be detached from easily from receiving in seat 13.
Then, the second square type shell 30 is inserted into the first square type shell 10 far from machine far from one end of rotor mechanism 4 by user In one end of body 1；One of the first square type shell 10 far from fuselage 1 is inserted into far from one end of rotor mechanism 4 in the second square type shell 30 During end, seat 13 is received to be pressed downward the second sliding panel 58 through connector assembly 32, so the second sliding panel 58 drive square type cylinder 54 to Lower movement, B guide block 52 follow square type cylinder 54 to move, and the continuation of leaf spring 53 is compressed；When be located at receive seat 13 in connector assembly 32 to After lower movement is a certain amount of, the corresponding port of the second square type shell 30 no longer to connector assembly 32 and receives seat 13 to enter the second square type shell 30 It causes to hinder, to guarantee the second square type shell 30 when being inserted into the first square type shell 10, connector assembly 32 will not be to the second square type shell 30 Insert action cause to hinder.
After receiving seat 13 to be aligned with the corresponding port of the second square type shell 30, user is by the second square type shell 30 far from rotor One end of mechanism 4 is inserted into first one end of square type shell 10 far from fuselage 1；In the second square type shell 30 far from rotor mechanism 4 One end is inserted into during first one end of square type shell 10 far from fuselage 1, and in Figure 26 shown in (a), the first square type shell 10 is separate One end of fuselage 1 can squeeze the first inclined-plane 46 of limited block 43, and the first inclined-plane 46 enables limited block 43 to be extruded to the first square In first square type slot 29 of shell 10, C guide block 44 follows limited block 43 to move, and C spring 45 is compressed；Limited block 43 is expressed to In one square type slot 29, guarantee that second one end of square type shell 30 far from rotor mechanism 4 can continue to be successfully inserted at the first square type shell 10 In one end far from fuselage 1.In Figure 26 shown in (b), when the second square type shell 30 one correcting and first far from rotor mechanism 4 When fixed block 14 is in contact, the limited block 43 of the second square type shell 30 is placed exactly at the corresponding limiting cutting of the first square type shell 10, So under the reset response of C spring 45, the reset of C spring 45 is so that C guide block 44 drives limited block 43 to fast move resets, limit Position block 43 is inserted into corresponding limiting cutting, and the lateral part surface of limited block 43 is located in corresponding limiting cutting, and limited block 43 One end with the first inclined-plane 46 is pierced by corresponding limiting cutting.The lateral part surface of limited block 43 is located at corresponding limiting cutting, this Sample limited block 43 can generate limit to the first square type shell 10, and then the first square type shell 10 and the second square type shell 30 are limited block 43 It all limits, it is therefore prevented that the second square type shell 30 is detached from from the first square type shell 10.
One end mistake of the first square type shell 10 far from fuselage 1 is inserted into far from one end of rotor mechanism 4 in the second square type shell 30 Cheng Zhong positioned at the connector assembly 32 received in seat 13 and receives seat 13 that can enter in the second square type shell 30, then 32 meeting of connector assembly Push the second sliding panel 58 mobile to the center position of square type cylinder 54, B spring 60 is compressed.When in the separate rotation of the second square type shell 30 After one end of wing mechanism 4 is completely inserted into first one end of square type shell 10 far from fuselage 1, the reset of A spring 21, so that A guide block 20 drive the first fixing seats 16 are mobile to reset, the first fixing seat 16 through the first sliding panel 22, receive seat 13 drive connector assembly 32 to The direction of first fixed block 14 is mobile, until receiving seat 13 to be restored to the position being bonded with 14 respective surfaces of the first fixed block, this When connector assembly 32 position make 60 decrement of B spring on the second sliding panel 58 have certain reduction；Seat 13 is being received to reset During, due to the position-limiting action of rubber bumps, connector assembly 32 will not be detached from from receiving in seat 13.Seat 13 is being received to reset knot Shu Hou receives seat 13 and connector assembly 32 to be respectively positioned in the second square type shell 30.Removable mechanism 3 is quickly assembled to mounting mechanism 2 at this time Movement complete.
After four removable mechanisms 3 are quickly assembled to four on mounting mechanism 2 respectively, quadrotor drone of the invention is matched It installs into, quadrotor drone at this time just can be carried out manipulation flight.
When removable mechanism 3 is needed from rapid removal on mounting mechanism 2, user presses the limited block for being pierced by limiting cutting 43 one end, limited block 43 are pressed completely into limiting cutting, and the second inclined-plane 47 of limited block 43 is fully located at limit and cuts at this time In mouthful, the first inclined-plane 46 of limited block 43 is located in limiting cutting and corresponding second sliding groove 34, the lateral part surface of limited block 43 It is placed exactly in corresponding second sliding groove 34；Limited block 43 so at this time will not cause to limit to the first square type shell 10.Make User pulls out second one end of square type shell 30 far from rotor mechanism 4 from the first square type shell 10 far from one end of fuselage 1, limited block 43 follow the second square type shell 30 to move, then the second inclined-plane 47 of limited block 43 will receive in the first square type shell 10, accordingly limit is cut The side of mouth squeezes, and limited block 43 is expressed to completely again in corresponding second sliding groove 34, guarantees that the second square type shell 30 is remote One end from rotor mechanism 4 can smoothly be pulled out from first one end of square type shell 10 far from fuselage 1.It is separate in the second square type shell 30 After one end pull-out of the first square type shell 10 far from fuselage 1, limit plate is no longer influenced by the work of external force extruding for one end of rotor mechanism 4 With the reset of C spring 45 is so that C guide block 44 drives limited block 43 is mobile to reset.
It was pulled out from the first square type shell 10 far from one end of fuselage 1 in second one end of square type shell 30 far from rotor mechanism 4 Cheng Zhong, connector assembly 32 are not detached from from receiving seat 13, and seat 13 and connector assembly 32 is received to progressively disengage from the second square type shell 30, Seat 13 is received to drive A guide block 20 to the movement of the direction of the first fixed block 14, A spring through the first sliding panel 22, the first fixing seat 16 21 are stretched again, and connector assembly 32 drives the second sliding panel 58 gradually to pull out from square type cylinder 54, and the gradually reset of B spring 60 has Help the second sliding panel 58 gradually to come out from square type cylinder 54.When second one end of square type shell 30 far from rotor mechanism 4 is from first After square type shell 10 is pulled out far from one end of fuselage 1, B spring 60 is restored to nature, receives seat 13 and receives inserting in seat 13 Headstock 32 is located at outside the corresponding port of the second square type shell 30；Finally, user extracts connector assembly 32 from receiving seat 13, then Under the reset response of A spring 21, so that A guide block 20 drives the first fixing seat 16 is mobile to reset, the first fixing seat 16 is through first Sliding panel 22 receives seat 13 to drive connector assembly 32 mobile to the direction of the first fixed block 14, until receiving seat 13 to be restored to and the The position of one fixed block, 14 respective surfaces fitting.In connector assembly 32 after being extracted in receiving seat 13, in the reset response of leaf spring 53 Under, B guide block 52 drives square type cylinder 54 to move up reset, until the second square type slot 31 of square type cylinder 54 and the second square type shell 30 When upper groove surface fits again, connector assembly 32 is still located at one end outside of the second square type shell 30 far from rotor mechanism 4, connector assembly The 32 side port surfaces corresponding with the second square type shell 30 being connected with the second sliding panel 58 fit, and connector assembly 32 still can not It enters in the second square type shell 30.
In conclusion main beneficial effect of the invention is: when being quickly equipped with mounting mechanism and removable mechanism, needing to insert Headstock with receive seat be correctly inserted into, connector assembly enter receive seat after could by the second square type shell far from rotor mechanism one End is inserted into the first square type shell far from one end of fuselage, otherwise seat is received connector assembly will not to be made to move down, receives seat can not It enters in the second square type shell, and then the second square type shell can not be successfully and be inserted into the first square type shell；In connector assembly and receive seat After being correctly plugged, second corresponding one end of square type shell just can smoothly be protected in the corresponding port for being inserted into the first square type shell, ensure that After being quickly equipped with mounting mechanism and removable mechanism, the first electric wire and the second electric wire can be powered well；To eliminate secondary dismantle The trouble checked.The configuration of the present invention is simple has preferable using effect.

Claims (10)

1. a kind of removable quadrotor drone, it is characterised in that: it includes fuselage, with mounting mechanism, removable mechanism, gyroplane Structure, the structure that the two sides of middle fuselage are installed is identical, for the wherein side of fuselage: symmetrically pacifying two one end with mounting mechanism On fuselage side；One end of two removable mechanisms is separately installed with a rotor mechanism, and the other end is equipped with two respectively Mechanism is matched far from one end of fuselage；
Above-mentioned rotor mechanism has motor and blade, and motor, which enables blade rotation to generate lift, makes quadrotor drone fly；
It is above-mentioned with mounting mechanism include the first square type shell with the first square type slot penetrated through, the first sliding groove with perforation the One fixed block, the first sliding panel, A guide rail, the receiving seat with receiving channel, metal receiving tube, wherein one end of the first square type shell It is fixedly mounted on fuselage side；First fixed block is fixedly mounted in the first square type shell；Two A guide rails are symmetrically mounted on first On the two sides groove face of square type slot, and two A guide rails be located at the first square type shell phase be connected in fuselage one end and above-mentioned first fixed block Between；One end of first sliding panel is snug fit between two A guide rails, and the other end is equipped with receiving seat；First sliding panel tool There is the one end for receiving seat to pass through the first sliding groove of the first fixed block, and seat is received to cannot be introduced into the first sliding groove；It receives Seat is flush with the first square type shell far from one end of fuselage far from one end of the first sliding panel；Three metal receiving tubes are equably pacified In the receiving channel for receiving seat；One end of three the first electric wires from receive seat without the side of receiving channel enter respectively with three gold Belong to receiving tube to be connected, the other end passes through fuselage and connects with being electrically connected in fuselage；
Above-mentioned removable mechanism includes the second square type shell, the connector assembly with plug slot, metal of the second square type slot with perforation Contact pin, square type cylinder, the second sliding panel, fixed plate and leaf spring, wherein one end of the second square type shell is connected with above-mentioned rotor mechanism, separately One end and the first square type shell form insertion far from one end of fuselage and cooperate；Two fixed plates are symmetrically mounted in the second square type slot； Square type cylinder is mounted between two fixed plates in a manner of sliding up and down, and leaf spring makes the upper slot of square type cylinder and the second square type slot Face fits；One end of second sliding panel is mounted in square type cylinder by way of being slidably matched, and the other end is equipped with connector assembly； Three metal ferrules are uniformly mounted in the plug slot of connector assembly；One end of three the second electric wires is from connector assembly without plug slot Side enters to be connected with three metal ferrules respectively, and it is mutually electric with the motor in above-mentioned rotor mechanism that the other end passes through the second square type slot Gas connection；
When the upper groove surface of second square type slot of above-mentioned square type cylinder and the second square type shell fits, leaf spring is in compressive state, plug Seat is located at one end outside of the second square type shell far from rotor mechanism, the side and the second square type that connector assembly is connected with the second sliding panel The corresponding port surface of shell fits, and connector assembly cannot be introduced into the second square type shell；
Also there is position limiting structure, when the second square type shell is inserted into the first square type far from one end of rotor mechanism in above-mentioned removable mechanism After shell is far from one end of fuselage, position-limit mechanism limits the second square type shell and the first square type shell simultaneously, and the second square type shell can not be from It is detached from first square type shell.
2. a kind of removable quadrotor drone according to claim 1, it is characterised in that: above-mentioned rotor mechanism also wraps Drive shaft and set casing are included, wherein one end of above-mentioned second square type shell is fixedly connected with set casing；Motor is fixedly mounted on set casing In；One end of drive shaft is connected with the motor shaft of motor, and the other end is pierced by the top surface of set casing；Two above-mentioned blades are symmetrically installed On one end periphery that drive shaft is pierced by set casing top surface；
The second electric wire of above three passes through set casing far from one end of metal ferrule and is mutually electrically connected with motor.
3. a kind of removable quadrotor drone according to claim 1, it is characterised in that: above-mentioned also to be wrapped with mounting mechanism A guide block, the first fixing seat, limited mouth, A spring are included, wherein above-mentioned first sliding panel is fixedly installed with far from one end of receiving seat First fixing seat；The two sides of first fixing seat are symmetrically installed there are two A guide block；Two A guide blocks are divided by way of being slidably matched It is not mounted in two A guide rails；One end of two A springs is separately mounted on two A guide blocks, and the other end is separately mounted to two On the inner wall of A guide rail；Two A springs are located in two A guide rails；
The two sides of the above-mentioned one end of first square type shell far from fuselage are symmetrically opened there are two the limited mouth penetrated through, and the first fixed block leans on Nearly limited mouth；
The first electric wire of above three is mounted in the first fixing seat by way of compressing limit by three housing screws, and is worn The circular hole of first fixing seat out；The same end of three the first electric wires passes through fuselage and connects with being electrically connected in fuselage, in addition same One end passes through above-mentioned first sliding panel and is connected respectively with three metal receiving tubes on seat are received；
When the outer bottom seat surface and the first fixed block respective surfaces of receiving seat fit, between the first fixing seat and fuselage outer surface Three the first electric wires be in relaxed state, A spring is in the raw at this time.
4. a kind of removable quadrotor drone according to claim 1, it is characterised in that: above-mentioned removable mechanism is also wrapped Include the second fixing seat, B guide groove, B guide block, the second sliding groove, C guide groove, limited block, C guide block, C spring, B spring, square hole, second Guide block, the second guide groove, wherein the opposite side of above-mentioned two fixed plate is provided with B guide groove, and two B guide grooves are symmetrical；It is above-mentioned The two sides of square type cylinder are symmetrically installed there are two B guide block；Square type cylinder is located between two fixed plates, and two B guide blocks are matched by sliding The mode of conjunction is separately mounted in two B guide grooves；Institute's mounting structure is identical in two B guide grooves, and wherein any one B is led Slot: one end of two above-mentioned leaf springs is separately mounted on corresponding B guide block lower surface, and the other end is separately mounted under B guide groove On groove face, two leaf springs are respectively positioned in B guide groove and symmetrical；
When the upper groove surface of square type cylinder and the second square type slot of the second square type shell fits, B guide block is located at the top of corresponding B guide groove Portion, and corresponding leaf spring is in compressive state on B guide block；
There is third square type slot, the two sides of third square type slot are symmetrically opened there are two the second guide groove in above-mentioned square type cylinder；Outside square type cylinder The square hole of perforation is provided on the cylinder bottom surface of side, and square hole is communicated with third square type slot；Above-mentioned second sliding panel is far from connector assembly One end is symmetrically installed there are two the second guide block；Second sliding panel is located in third square type slot far from one end of connector assembly, and second Two the second guide blocks on sliding panel are separately mounted in two the second guide grooves by way of being slidably matched；One end of B spring The second sliding panel is mounted on far from one end of connector assembly, the other end is mounted on the kerve face of third square type slot；B spring is located at In the third square type slot of square type cylinder；
When the side port surface corresponding with the second square type shell that connector assembly and the second sliding panel are connected fits, and connector assembly can not When entering in the second square type shell, the length that the second sliding panel stretches out square type cylinder reaches longest, and C spring is in nature shape at this time State；
Second fixing seat is fixedly mounted in the second square type slot of above-mentioned second square type shell, and the second fixing seat is located proximate to State square type cylinder；The second electric wire of above three is mounted in the second fixing seat by way of compressing limit by three housing screws, And it is pierced by the circular hole of the second fixing seat；The same end of three the second electric wires passes through the motor in the second square type shell and rotor mechanism It is mutually electrically connected, the same end in addition passes through three metals on the square hole, the second sliding panel and above-mentioned connector assembly of square type cylinder and inserts Needle is connected；
The second sliding groove penetrated through there are two symmetrically being opened on the groove face of above-mentioned second square type slot two sides, and the position of the second sliding groove is leaned on The nearly one end of second square type shell far from rotor mechanism；
Institute's mounting structure and dependency structure are identical in the second sliding groove on the groove face of above-mentioned second square type slot two sides, for any one A second sliding groove: one end of limited block has the first inclined-plane and the second inclined-plane, and the two sides of the other end are symmetrically installed leads there are two C Block；Limited block is mounted in the second sliding groove by way of being slidably matched；Two C guide blocks are installed by way of being slidably matched In corresponding two C guide grooves；One end of two C springs is separately mounted on two C guide blocks, and the other end is separately mounted to two On the side channel face of C guide groove, two C springs are located in two C guide grooves.
5. a kind of removable quadrotor drone according to claim 4, it is characterised in that: above-mentioned C spring is compression Spring；When limited block is not affected by external force, corresponding C spring is not affected by compression, the one end of limited block far from the first inclined-plane To there are spacing between corresponding second sliding groove and the notch of the second square type slot connecting place.
6. a kind of removable quadrotor drone according to claim 3 or 4, it is characterised in that: in above-mentioned limited block The side being connected with the second inclined-plane is named as lateral part surface；Two limited blocks of above-mentioned second square type shell respectively with above-mentioned first square type Two limiting cuttings of shell mutually limit cooperation；When far from one end of rotor mechanism to be inserted into the first square type shell separate for the second square type shell During one end of fuselage, first one end of square type shell far from fuselage can squeeze the first inclined-plane of limited block, and the first inclined-plane makes Obtaining limited block can be extruded in the first square type slot of the first square type shell；When limited block is inserted into corresponding limiting cutting, The lateral part surface of limited block is located in corresponding limiting cutting, and limited block is pierced by corresponding limit with the one end on the first inclined-plane and cuts Mouthful.
7. a kind of removable quadrotor drone according to claim 1, it is characterised in that: the receiving of above-mentioned receiving seat It symmetrically opens there are two the first guide groove the two sides of slot；One elastic bumps is installed on the side channel face of each guide groove；Above-mentioned plug The two sides of seat are symmetrically installed there are two the first guide block；Two the first guide blocks are slidably matched with two the first guide groove formation respectively；Two A first guide block respectively with the elastic bumps phase extrusion fit in two the first guide grooves.
8. a kind of removable quadrotor drone according to claim 7, it is characterised in that: above-mentioned elastic bumps are by rubber Glue material is made.
9. a kind of removable quadrotor drone according to claim 1, it is characterised in that: state and receive seat by insulation material Material is made；Above-mentioned metal receiving tube is made of copper product.
10. a kind of removable quadrotor drone according to claim 1, it is characterised in that: above-mentioned connector assembly is by exhausted Edge material is made；Above-mentioned metal ferrule is made of copper product.
CN201811524314.6A 2018-12-13 2018-12-13 A kind of removable quadrotor drone Withdrawn CN110001942A (en)

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110667844A (en) * 2019-08-30 2020-01-10 南京精微迅智能科技有限公司 Environment detection unmanned aerial vehicle for fire rescue

Citations (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5174772A (en) * 1992-01-22 1992-12-29 The United States Of America As Represented By The Administrator Of The National Aeronautics & Space Administration Work attachment mechanism/work attachment fixture
EP0627786A1 (en) * 1993-06-02 1994-12-07 AEROSPATIALE Société Nationale Industrielle Process and system for the physical separation of two joint electrically connected bodies
CN103474846A (en) * 2013-09-04 2013-12-25 航天东方红卫星有限公司 Inter-satellite power supplying device
CN104332763A (en) * 2014-07-14 2015-02-04 中航光电科技股份有限公司 Separation break-away connector assembly, plug and socket thereof
CN106058564A (en) * 2016-07-07 2016-10-26 绵阳柏瑞电子有限公司 Quick miniature connecting waterproof connector for unmanned aerial vehicle
CN205960333U (en) * 2016-08-23 2017-02-15 深圳加西亚联合技术有限公司 Unmanned aerial vehicle connection structure and unmanned aerial vehicle
CN206003990U (en) * 2016-08-10 2017-03-08 北方天途航空技术发展（北京）有限公司 Unmanned plane and the wire connecting base for unmanned plane
CN106477039A (en) * 2016-12-21 2017-03-08 深圳市道通智能航空技术有限公司 A kind of rotor wing unmanned aerial vehicle
CN106532303A (en) * 2015-09-10 2017-03-22 贵州航天电器股份有限公司 Floating plug-in electrical connector
CN106716742A (en) * 2016-01-22 2017-05-24 深圳市大疆创新科技有限公司 Connector of electronic speed regulator and motor, power system and unmanned aerial vehicle
CN106877074A (en) * 2017-03-20 2017-06-20 浙江科技学院 A kind of unmanned plane charges and is tethered at line automatic releasing device
CN107054623A (en) * 2017-03-13 2017-08-18 普宙飞行器科技（深圳）有限公司 Unmanned plane slidingtype horn device and unmanned plane
CN107465040A (en) * 2017-03-17 2017-12-12 梧州市中盟贸易有限公司 A kind of USB joint
CN107672784A (en) * 2017-11-08 2018-02-09 沈阳旋飞航空技术有限公司 The support bar quick-disassembly structure of the dynamic unmanned plane of oil
CN207141419U (en) * 2017-09-14 2018-03-27 上海歌尔泰克机器人有限公司 Attachment means and unmanned plane device
CN207199911U (en) * 2017-09-15 2018-04-06 顺丰科技有限公司 A kind of fast combination hub, plug and combinations thereof connector
CN207282816U (en) * 2017-08-17 2018-04-27 深圳兴启发电路板有限公司 A kind of electric connection structure of adjacent circuit plate
CN207737495U (en) * 2017-09-02 2018-08-17 深圳市莲花百川科技有限公司 The multi-rotor unmanned aerial vehicle of detachable rotor
CN108583851A (en) * 2018-06-29 2018-09-28 拓攻（南京）机器人有限公司 A kind of Quick Release undercarriage and the multi-rotor unmanned aerial vehicle containing it

Patent Citations (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5174772A (en) * 1992-01-22 1992-12-29 The United States Of America As Represented By The Administrator Of The National Aeronautics & Space Administration Work attachment mechanism/work attachment fixture
EP0627786A1 (en) * 1993-06-02 1994-12-07 AEROSPATIALE Société Nationale Industrielle Process and system for the physical separation of two joint electrically connected bodies
CN103474846A (en) * 2013-09-04 2013-12-25 航天东方红卫星有限公司 Inter-satellite power supplying device
CN104332763A (en) * 2014-07-14 2015-02-04 中航光电科技股份有限公司 Separation break-away connector assembly, plug and socket thereof
CN106532303A (en) * 2015-09-10 2017-03-22 贵州航天电器股份有限公司 Floating plug-in electrical connector
CN106716742A (en) * 2016-01-22 2017-05-24 深圳市大疆创新科技有限公司 Connector of electronic speed regulator and motor, power system and unmanned aerial vehicle
CN106058564A (en) * 2016-07-07 2016-10-26 绵阳柏瑞电子有限公司 Quick miniature connecting waterproof connector for unmanned aerial vehicle
CN206003990U (en) * 2016-08-10 2017-03-08 北方天途航空技术发展（北京）有限公司 Unmanned plane and the wire connecting base for unmanned plane
CN205960333U (en) * 2016-08-23 2017-02-15 深圳加西亚联合技术有限公司 Unmanned aerial vehicle connection structure and unmanned aerial vehicle
CN106477039A (en) * 2016-12-21 2017-03-08 深圳市道通智能航空技术有限公司 A kind of rotor wing unmanned aerial vehicle
CN107054623A (en) * 2017-03-13 2017-08-18 普宙飞行器科技（深圳）有限公司 Unmanned plane slidingtype horn device and unmanned plane
CN107465040A (en) * 2017-03-17 2017-12-12 梧州市中盟贸易有限公司 A kind of USB joint
CN106877074A (en) * 2017-03-20 2017-06-20 浙江科技学院 A kind of unmanned plane charges and is tethered at line automatic releasing device
CN207282816U (en) * 2017-08-17 2018-04-27 深圳兴启发电路板有限公司 A kind of electric connection structure of adjacent circuit plate
CN207737495U (en) * 2017-09-02 2018-08-17 深圳市莲花百川科技有限公司 The multi-rotor unmanned aerial vehicle of detachable rotor
CN207141419U (en) * 2017-09-14 2018-03-27 上海歌尔泰克机器人有限公司 Attachment means and unmanned plane device
CN207199911U (en) * 2017-09-15 2018-04-06 顺丰科技有限公司 A kind of fast combination hub, plug and combinations thereof connector
CN107672784A (en) * 2017-11-08 2018-02-09 沈阳旋飞航空技术有限公司 The support bar quick-disassembly structure of the dynamic unmanned plane of oil
CN108583851A (en) * 2018-06-29 2018-09-28 拓攻（南京）机器人有限公司 A kind of Quick Release undercarriage and the multi-rotor unmanned aerial vehicle containing it

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110667844A (en) * 2019-08-30 2020-01-10 南京精微迅智能科技有限公司 Environment detection unmanned aerial vehicle for fire rescue

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