CN110001940A - A kind of removable quadrotor drone - Google Patents
A kind of removable quadrotor drone Download PDFInfo
- Publication number
- CN110001940A CN110001940A CN201811523543.6A CN201811523543A CN110001940A CN 110001940 A CN110001940 A CN 110001940A CN 201811523543 A CN201811523543 A CN 201811523543A CN 110001940 A CN110001940 A CN 110001940A
- Authority
- CN
- China
- Prior art keywords
- square type
- type shell
- mentioned
- guide
- fuselage
- 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.)
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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
- H01R13/62—Means for facilitating engagement or disengagement of coupling parts or for holding them in engagement
- H01R13/627—Snap or like fastening
- H01R13/6271—Latching means integral with the housing
- H01R13/6273—Latching means integral with the housing comprising two latching arms
-
- 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
- H01R24/20—Coupling parts carrying sockets, clips or analogous contacts and secured only to wire or cable
-
- 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
- H01R24/28—Coupling parts carrying pins, blades or analogous contacts and secured only to wire or cable
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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)
- Connector Housings Or Holding Contact Members (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, the second square type shell could be inserted into the first square type shell far from one end of fuselage far from one end of rotor mechanism after needing for connector assembly to be properly inserted into receiving seat, otherwise the second square type shell, which can not be successfully, is inserted into the first square type shell, it 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.The configuration of the present invention is simple has preferable using effect.
Description
Technical field
The invention belongs to air vehicle technique fields, more particularly to a kind of removable quadrotor drone.
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；Quadrotor drone need in use,
The horn of quadrotor drone and rotor mechanism are quickly assembled on fuselage again；But now quadrotor easy to disassemble nobody
For machine in quick assembling, the electric wire of electric wire and fuselage on horn and rotor mechanism sometimes will appear connection in quick assembling
It is bad or the problem of be not fully connected, so as to cause the quadrotor drone cisco unity malfunction after quick assembling, also need
Quadrotor drone is dismantled again and is assembled again, it is more troublesome in this way.In order to guarantee that horn and rotor mechanism are quickly assembled to
When on fuselage, the electric wire on arm and rotor mechanism is able to maintain the electric wire good connection with fuselage always, so one kind is just needed to exist
After quadrotor drone quick assembling is good, do not need specially to check whether electric 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 use
Following technical scheme is realized.
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, 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, 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, sliding panel, the receiving seat with receiving channel, metal receiving tube, wherein the fixed peace in one end of the first square type shell
On fuselage side；First fixed block is fixedly mounted in the first square type shell, and one end of sliding panel has wedge angle, other end peace
Equipped with receiving seat；Sliding panel is mounted in the first sliding groove of the first fixed block by way of being slidably matched；Receive seat can not
It enters in the first sliding groove, and the one end of seat far from sliding panel is received to be flush with the first square type shell far from one end of fuselage；
Three metal receiving tubes are uniformly mounted in the receiving channel for receiving seat；One end of three the first electric wires is from receiving seat without receiving channel
Side enter and be connected respectively with three metal receiving tubes, the other end passes through fuselage and connects with being electrically connected in fuselage.
Above-mentioned first square type shell also has the A spring for generating pulling force to the first square type shell center position to receiving seat.
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, wherein one end of the second square type shell is connected with above-mentioned rotor mechanism, the other end and the first square type shell are far from fuselage
One end forms insertion cooperation；Three metal ferrules are uniformly mounted in the plug slot of connector assembly；One end of three the second electric wires
Enter from connector assembly without the side of plug slot and be connected respectively with three metal ferrules, the other end passes through the second square type slot and above-mentioned rotation
Motor in wing mechanism is mutually electrically connected.
Three metal ferrules of three metal receiving tubes and connector assembly in above-mentioned receiving seat are mutually inserted into cooperation.
Have to form the second square type shell far from one end port of rotor mechanism in above-mentioned second square type shell and blocks effect
Baffle；When baffle is not by external force, B spring can guarantee that baffle hides two square type shells far from one end port of rotor mechanism
Gear；When connector assembly is not affected by external force, connector assembly cannot be introduced into the second square type shell under the effect of blocking of baffle；
After the second square type shell is inserted into the one end of the first square type shell far from fuselage far from one end of rotor mechanism, connector assembly passes through extruding
Baffle and enter in 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 rail, A guide block, the first fixing seat, limit
Mouthful, two of them A guide rail is symmetrically and fixedly mounted on the two sides groove face of the first square type slot of above-mentioned first square type shell；A guide rail position
It is connected between one end of fuselage and above-mentioned first fixed block in the first square type shell phase；The two sides of first fixing seat are symmetrically installed with two
A A guide block；Two A guide blocks are separately mounted in two A guide rails by way of being slidably matched；One end of two above-mentioned A springs
It is separately mounted on two A guide blocks, the other end is separately mounted on the inner wall of two A guide rails；Two A springs are located at two
In a A guide rail.
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 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, between the first fixing seat and receiving seat
Three the first electric wires be in tension, three the first electric wires between the first fixing seat and fuselage outer surface be in relaxation shape
State, A spring is in tensional state at this time.Such design is advantageous in that: receiving seat can be under external force from the first square type
It is pulled out in shell, the damage caused during receiving seat to the first electric wire is pulled out in order to prevent, so the first fixing seat will be set
Counting into can move, and the first electric wire of three between the first fixing seat and fuselage outer surface is in relaxed state.For A spring
Purpose in tensional state is: when receiving seat not by external force, the A spring of tensional state makes the first fixing seat
It receives seat to there is the pulling force to the first square type shell center position always through the first wire pair, guarantees that sliding panel is located at the first fixed block
In, receive seat not to be detached from from the first square type shell.
As the further improvement of this technology, above-mentioned removable mechanism further includes that B guide groove, B guide block, the second sliding groove, C are led
Slot, limited block, C guide block, C spring, the second fixing seat, wherein above-mentioned second square type shell is far from second at one end of rotor mechanism
Possessed structure is identical on the two sides groove face of square type slot, for any one side channel face of the second square type slot: the second square type slot
Open that there are two B guide grooves on side channel face in a manner of symmetrical up and down；The second sliding of perforation is provided on the side channel face of second square type slot
Slot, the two sides of the second sliding groove are symmetrically opened there are two C guide groove；Second sliding groove is located between two B guide grooves.
There are two above-mentioned baffle tools；Two baffles are mounted on the second square type of the second square type shell by way of being slidably matched
In slot, and two baffles are distributed in a manner of symmetrical up and down；The two sides of each baffle are symmetrically installed there are two B guide block；Up and down
There is spacing between two symmetrical baffles.
For the two sides groove face of the second square type slot: on two B guide grooves of upside institute's mounting structure be located at downside
Institute's mounting structure is identical on two B guide grooves, for being located at two B guide grooves of upside: two B guide blocks positioned at the baffle of upside are logical
It crosses the mode being slidably matched to be separately mounted in two B guide grooves, one end of two B springs is separately mounted on two B guide blocks, separately
One end is separately mounted on the side channel face of two B guide grooves, and two B springs are located in two B guide grooves.
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 B guide groove；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 second square type shell and the motor phase in rotor mechanism
Electrical connection, spacing of the same end across two baffles in addition are connected with three metal ferrules on above-mentioned connector assembly.
When B spring is not compressed by external force, B guide block enable corresponding baffle by the second square type shell far from rotor mechanism one
It blocks end port；When connector assembly is located at the outside of the second square type shell, connector assembly and two baffles generate and amplexiform touching and connector assembly
When not squeezing two baffles, three the second electric wires between connector assembly and the second fixing seat are in relaxed state.Connector assembly and
The design that three the second electric wires between two fixing seats are in relaxed state is advantageous in that: convenient for user pick up after connector assembly
Any direction moves connector assembly, is inserted into and receives in seat quickly convenient for connector assembly.
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 the first square type shell far from one end of fuselage far from one end of rotor mechanism, the first square type shell is far from machine
One end of body can squeeze the first inclined-plane of limited block, and the first inclined-plane enables limited block to be extruded to the first square of the first square type shell
In type groove；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, above-mentioned receiving seat is made of insulating material；Above-mentioned metal receiving tube is by copper material
Material 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, moreover it is possible to prevent the first fixing seat to be detached from between two A guide rails.When the first fixing seat is moved to the direction of the first fixed block
When dynamic, followed in the first fixing seat motion process in A guide block, A spring continues to be stretched；When the first fixing seat is no longer influenced by external force
After the effect of pulling, the reset of A spring is so that A guide block drives the first fixing seat is mobile to reset.
The design of B guide block and B spring is: B guide block can guarantee that corresponding baffle can be steady in the second square type slot
Sliding, moreover it is possible to prevent corresponding baffle to be detached from from the second square type shell.When baffle is mobile to the direction of the second fixed block,
B guide block follows in baffle motion process, and B spring is compressed；After baffle is no longer influenced by the effect of external force extruding, B spring is answered
Position makes B guide block drive the first fixing seat is mobile to reset.
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.
The first fixed block in the present invention plays the role of track guidance to sliding panel, ensure that sliding panel is solid first
Determining can smooth sliding in block.
Three the first electric wires being located in sliding panel in the present invention, are installed in sliding panel, are receiving seat in this way
When being pulled out by external force, three the first electric wires mainly in sliding panel bear main pulling force, avoid three the first electric wires and three
The tie point of a metal receiving tube is drawn bad.
Relative to traditional removable quadrotor drone, beneficial effects of the present invention:
1, structure is simple, convenient disassembly, just needs for connector assembly to be inserted into before quick assembling and receive in seat, avoids quickly
It is bad or the problem of be not fully connected to occur electric wire connection when assembly.
2, when being quickly equipped with mounting mechanism and removable mechanism, need for connector assembly to be properly inserted into receive in seat after could incite somebody to action
Second square type shell is inserted into the first square type shell far from one end of fuselage far from one end of rotor mechanism, otherwise the second square type shell without
Method is successfully inserted in the first square type shell, ensure that after being quickly equipped with mounting mechanism and removable mechanism, the first electric wire and the second electricity
Line can be powered well；To eliminate the secondary trouble dismantled and checked.
3, receiving seat of the invention and connector assembly when carrying out quick assembling all in the state that can flexibly move, very
It is received in seat convenient for users to connector assembly to be inserted into；In addition, it is flexibly mobile due to receiving seat and connector assembly to allow, then occurring
It receives the metal receiving tube in seat or the metal ferrule in connector assembly to break down when damaging to be also convenient for replacing, avoid to be equipped with
Mechanism or removable mechanism disassemble the trouble of repairing completely.
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 installation diagrammatic cross-section for receiving 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 diagrammatic cross-section for receiving seat.
Figure 12 is the perspective diagram of removable mechanism.
Figure 13 is the partial cutaway schematic of Figure 12.
Figure 14 is part section (one) schematic diagram of the second square type shell.
Figure 15 is part section (two) schematic diagram of the second square type shell.
Figure 16 is the schematic diagram of institute's mounting structure on limited block.
Figure 17 is the installation section schematic top plan view of C guide block.
Figure 18 is the scheme of installation of three the second electric wires.
Figure 19 be three the second electric wires respectively with the diagrammatic cross-section of three metal ferrules being connected.
Figure 20 is the schematic diagram that two baffles stop connector assembly.
Figure 21 is the schematic section elevation that the installation section and two baffles of two baffles stop connector assembly.
Figure 22 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, sliding panel；23, receiving channel；
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,
Two square type shells；31, the second square type slot；32, connector assembly；33, B guide groove；34, the second sliding groove；35, C guide groove；36, baffle；37,B
Guide block；38, B spring；39, the second electric wire；40, the 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, lateral part surface；49, plug slot.
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, sliding panel 22, as shown in figure 11, the receiving seat with receiving channel 23 of the first sliding groove 19 of perforation
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；Such as Fig. 5
Shown, the first fixed block 14 is fixedly mounted in the first square type shell 10, and as shown in Figure 8,9, one end of sliding panel 22 has wedge angle
28, the other end, which is equipped with, receives seat 13；Sliding panel 22 is mounted on the first cunning of the first fixed block 14 by way of being slidably matched
In dynamic slot 19；Seat 13 is received to cannot be introduced into the first sliding groove 19, as shown in figure 5, and receiving seat 13 far from sliding panel 22
One end is flush with the first square type shell 10 far from one end of fuselage 1；As shown in Fig. 8,11, three metal receiving tubes 26 are equably pacified
In the receiving channel 23 for receiving seat 13；As shown in Figure 10, one end of three the first electric wires 17 is from receiving seat 13 without receiving channel 23
Side enter and be connected respectively with three metal receiving tubes 26, the other end passes through fuselage 1 and connects with being electrically connected in fuselage 1.
Above-mentioned first square type shell 10 also has the A spring for generating pulling force to 10 center position of the first square type shell to receiving seat 13
21。
As shown in Figure 12,13, above-mentioned removable mechanism 3 include with perforation the second square type slot 31 the second square type shell 30,
As shown in figure 19, with connector assembly 32, the metal ferrule 42 of plug slot 49, as shown in Figure 1, 2, wherein the one of the second square type shell 30
End is connected with above-mentioned rotor mechanism 4, and the other end and the first square type shell 10 form insertion far from one end of fuselage 1 and cooperate；Such as Figure 18
Shown, three metal ferrules 42 are uniformly mounted in the plug slot 49 of connector assembly 32；As shown in figure 19, three the second electric wires 39
One end enter from connector assembly 32 without the side of plug slot 49 and be connected respectively with three metal ferrules 42, the other end passes through the second square
Type groove 31 is electrically connected with 8 phase of motor in above-mentioned rotor mechanism 4.
Three 42 phases of metal ferrule of three metal receiving tubes 26 and connector assembly 32 in above-mentioned receiving seat 13, which are inserted into, to be cooperated.
As shown in figure 13, there is one end end to the second square type shell 30 far from rotor mechanism 4 in above-mentioned second square type shell 30
Mouth forms the baffle 36 for effect of blocking；When baffle 36 is not by external force, B spring 38 can guarantee baffle 36 by two square type shells
It blocks one end port far from rotor mechanism 4；When connector assembly 32 is not affected by external force, connector assembly 32 is blocked baffle 36
Effect is lower and cannot be introduced into the second square type shell 30；When the second square type shell 30 is inserted into first far from one end of rotor mechanism 4
Behind the one end of square type shell 10 far from fuselage 1, connector assembly 32 is entered in the second square type shell 30 by squeezing baffle 36.
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.
It with mounting mechanism 2 further include A guide rail 18, A guide block 20, the first fixing seat 16, limited mouth 12 as shown in figure 5, above-mentioned, such as
Shown in Fig. 6, two of them A guide rail 18 is symmetrically and fixedly mounted to the two sides groove face of the first square type slot 29 of above-mentioned first square type shell 10
On；A guide rail 18 is located at the first square type shell 10 and is connected between one end of fuselage 1 and above-mentioned first fixed block 14；As shown in figure 9,
The two sides of first fixing seat 16 are symmetrically installed there are two A guide block 20；As shown in fig. 7, two A guide blocks 20 pass through the side being slidably matched
Formula is separately mounted in two A guide rails 18；One end of two above-mentioned A springs 21 is separately mounted on two A guide blocks 20, the other end
It 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, and as shown in Figures 9 and 10, the same end in addition passes through above-mentioned sliding panel 22 respectively and on receiving seat 13
Three metal receiving tubes 26 are 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
Seat 16 and three the first electric wires 17 between seat 13 is received to be in tension, between 1 outer surface of the first fixing seat 16 and fuselage
Three the first electric wires 17 be in relaxed state, as shown in figure 9, A spring 21 is in tensional state at this time.Such design benefit
It is: receives seat 13 that can pull out from the first square type shell 10 under external force, pulls out the mistake for receiving seat 13 in order to prevent
The damage to the first electric wire 17 is caused in journey, so the first fixing seat 16 will be designed to move, and the first fixing seat 16 with
Three the first electric wires 17 between 1 outer surface of fuselage are in relaxed state.The purpose for being in tensional state for A spring 21 exists
In: when receiving seat 13 not by external force, the A spring 21 of tensional state makes the first fixing seat 16 right through the first electric wire 17
It receives seat 13 to there is the pulling force to 10 center position of the first square type shell always, guarantees that sliding panel 22 is located in the first fixed block 14,
Seat 13 is received not to be detached from from the first square type shell 10.
As shown in Figure 13,15,16, above-mentioned removable mechanism 3 further includes that B guide groove 33, B guide block 37, the second sliding groove 34, C are led
Slot 35, limited block 43, C guide block 44, C spring 45, the second fixing seat 40, as shown in Figure 14,15, wherein above-mentioned second square type shell 30
Possessed structure is identical on the two sides groove face of the second square type slot 31 at one end far from rotor mechanism 4, for the second square type
Any one side channel face of slot 31: open that there are two B in a manner of symmetrical up and down as shown in figure 14, on the side channel face of the second square type slot 31
Guide groove 33；As shown in figure 15, the second sliding groove 34 of perforation is provided on the side channel face of the second square type slot 31, the second sliding groove 34
It symmetrically opens there are two C guide groove 35 two sides；As shown in figure 14, the second sliding groove 34 is located between two B guide grooves 33.
There are two the above-mentioned tools of baffle 36；As shown in Figure 13,21, two baffles 36 are mounted on by way of being slidably matched
In second square type slot 31 of two square type shells 30, and two baffles 36 are distributed in a manner of symmetrical up and down；As shown in figure 20, each
The two sides of baffle 36 are symmetrically installed there are two B guide block 37；There is spacing between two baffles 36 of distribution symmetrical above and below.
For the two sides groove face of the second square type slot 31: positioned at institute's mounting structure on two B guide grooves 33 of upside and under being located at
Institute's mounting structure is identical on two B guide grooves 33 of side, for being located at two B guide grooves 33 of upside: as shown in figure 13, being located at upside
Two B guide blocks 37 of baffle 36 be separately mounted to by way of being slidably matched in two B guide grooves 33, two B springs 38
One end is separately mounted on two B guide blocks 37, and the other end is separately mounted on the side channel face of two B guide grooves 33, two B springs 38
It is located in two B guide grooves 33.
As shown in figure 13, 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 B guide groove 33；As shown in figure 18, the second electric wire of above three 39 is led to by three housing screws 27
It crosses the mode for compressing and limiting to be mounted in the second fixing seat 40, and is pierced by the circular hole of the second fixing seat 40；Three the second electric wires
39 the same end 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 18,21, in addition
Spacing of the same end across two baffles 36 is connected with three metal ferrules 42 on above-mentioned connector assembly 32.
As shown in figure 13, when B spring 38 is not compressed by external force, B guide block 37 enables corresponding baffle 36 by the second square type
Shell 30 is blocked far from one end port of rotor mechanism 4；When connector assembly 32 is located at the outside of the second square type shell 30, connector assembly 32 and two
A baffle 36, which generates, amplexiforms touching and when connector assembly 32 does not squeeze two baffles 36, as shown in Figure 13,18, connector assembly 32 and second
Three the second electric wires 39 between fixing seat 40 are in relaxed state.Three second between connector assembly 32 and the second fixing seat 40
The design that electric wire 39 is in relaxed state is advantageous in that: moving connector assembly in any direction after picking up connector assembly 32 convenient for user
32, it is inserted into and receives in seat 13 quickly convenient for connector assembly 32.
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 16, 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 17, 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 17, 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 16, the side being connected in above-mentioned limited block 43 with the second inclined-plane 47 is named as lateral part surface 48；Above-mentioned
Two limiting cuttings of two limited blocks 43 of two square type shells 30 respectively with above-mentioned first square type shell 10 mutually limit cooperation；Such as Figure 22
In shown in (a), 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 22 shown in (b), when limited block 43 is inserted into
When in corresponding limiting cutting, the lateral part surface 48 of limited block 43 is located in corresponding limiting cutting, and limited block 43 has first
The one end on inclined-plane 46 is pierced by corresponding limiting cutting.
As shown in Fig. 8,11, 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 18,19, the two sides of above-mentioned connector assembly 32 are symmetrically installed
There are 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
Mating reaction: 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
In first 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 receiving seat 13
In receiving channel 23.
Above-mentioned elastic bumps 25 are made of rubber material.
Above-mentioned receiving seat 13 is 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 one fixing seat 16 and receiving seat 13 are in tension, the first fixing seat 16 and 1 appearance of fuselage
Three the first electric wires 17 between face are in relaxed state, and A spring 21 is in tensional state at this time.
Removable mechanism 3: as shown in figure 13, connector assembly 32 is located at the outside of the second square type shell 30, connector assembly 32 and two gears
Plate 36 does not generate extruding；B spring 38 is not compressed by external force, and B guide block 37 enables corresponding baffle 36 that second square type shell 30 is remote
It blocks one end port from rotor mechanism 4；As shown in figure 17, limited block 43 is not affected by external force, corresponding C spring 45 not by
To compression, the slot 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
There are spacing between mouthful.
When removable mechanism 3 needs are quickly assembled to mounting mechanism 2, the process of quick assembling: user will receive seat 13
It is pulled out from the second square type shell 30, receives seat 13 that sliding panel 22 is detached from from the first fixed block 14；Sliding panel 22 is through first
Electric wire 17 pulls the first fixing seat 16 to the movement of the direction of the first fixed block 14, and A guide block 20 follows the first fixing seat 16 to move,
A spring 21 continues to be stretched.The connector assembly 32 for being located at 30 outside of the second square type shell is picked up and be inserted by user receives seat 13
Receiving channel 23 in；During being inserted into receiving channel 23 for receiving seat 13, two the first guide blocks 41 can be distinguished connector assembly 32
It is inserted 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
In the receiving channel 23 for receiving seat 13；Three metal ferrules 42 in connector assembly 32, which are inserted respectively into, receives three metals of seat 13 to connect
It receives in pipe 26；When the bottom of the close receiving channel 23 for receiving seat 13 of connector assembly 32, the first guide block 41 is in corresponding first guide groove 24
In sliding can squeeze and cross the rubber bumps in the first guide groove 24；When connector assembly 32 is located at the receiving channel 23 of receiving seat 13
When bottom, three metal ferrules 42 are completely inserted into respectively in three metal receiving tubes 26, and the first guide block 41 goes just past first
Rubber bumps in guide groove 24, rubber bumps, which can play the first guide block 41, at this time prevents the first guide block 41 from the first guide groove 24
The effect being not easily disconnected from, so that connector assembly 32 will not be detached from easily from receiving in seat 13.Then, user puts down receiving seat
13, then the reset of A spring 21 is so that A guide block 20 drives the first fixing seat 16 mobile multiple under the reset response of A spring 21
Position, the first fixing seat 16 drive sliding panel 22 through the first electric wire 17 and receive seat 13 is mobile to reset.It is connect since sliding panel 22 is separate
Receiving one end of seat 13 is wedge angle 28, then sliding panel 22 is mobile reset during, the wedge angle 28 of sliding panel 22 can make to slide
Plate 22 is automatic and is quickly inserted into the first fixed block 14；When sliding panel 22 is again completely into the first fixed block 14,
And when seat 13 being received to be bonded with the corresponding surface of the first fixed block 14, mobile reset of seat 13 is received to terminate.Receiving seat 13 entire
During mobile reset, seat 13 is received to drive insertion seat movement always.
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, in Figure 22 shown in (a), first one end of square type shell 10 far from fuselage 1 can squeeze the first inclined-plane of limited block 43
46, the first inclined-plane 46 enables limited block 43 to be extruded in the first square type slot 29 of the first square type shell 10, and C guide block 44 follows limit
Position block 43 moves, and C spring 45 is compressed；Limited block 43 is expressed in the first square type slot 29, guarantees the second square type shell 30 far from rotation
One end of wing mechanism 4 can continue to be successfully inserted in first one end of square type shell 10 far from fuselage 1.When the second square type shell 30 is separate
The one of rotor mechanism 4 corrects when being in contact with the first fixed block 14, in Figure 22 shown in (b), the limit of the second square type shell 30
Block 43 is placed exactly at the corresponding limiting cutting of the first square type shell 10, then under the reset response of C spring 45, C spring 45
It resets so that C guide block 44 drives limited block 43 to fast move reset, limited block 43 is inserted into corresponding limiting cutting, limited block
43 lateral part surface 48 is located in corresponding limiting cutting, and there is limited block 43 one end on the first inclined-plane 46 to be pierced by corresponding limit
Notch.The lateral part surface 48 of limited block 43 is located at corresponding limiting cutting, and such limited block 43 can generate the first square type shell 10
Limit, and then the first square type shell 10 and the second square type shell 30 are limited block 43 and all limit, it is therefore prevented that the second square type shell 30 from first
It is detached from 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 can squeeze baffle 36 positioned at the connector assembly 32 received in seat 13, and baffle 36 is mobile to the direction of the second fixed block, leads in B
Block 37 follows in 36 motion process of baffle, and B spring 38 is compressed；Receive seat 13 and connector assembly 32 that can be inserted into the second square type shell 30
In.After the second square type shell 30 is completely inserted into the one end of the first square type shell 10 far from fuselage 1 far from one end of rotor mechanism 4,
Receive seat 13 and connector assembly 32 can be completely into 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
48 are 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.
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, limit
Block 43 follows the second square type shell 30 to move, then the second inclined-plane 47 of limited block 43 will receive and accordingly limit in the first square type shell 10
The side of notch squeezes, and limited block 43 is expressed to completely again in corresponding second sliding groove 34, guarantees the second square type shell 30
One end far from rotor mechanism 4 can smoothly be pulled out from first one end of square type shell 10 far from fuselage 1.It is remote 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 external force extruding for one end from rotor mechanism 4
Effect, 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,
B spring 38 gradually resets, and the reset of B spring 38 is so that B guide block 37 drives the first fixing seat 16 is gradually mobile to reset.When the second square
After one end pull-out of the first square type shell 10 far from fuselage 1, the reset of B spring 38 makes for the one end of shell 30 far from rotor mechanism 4
Obtaining B guide block 37 drives mobile reset of the first fixing seat 16 to complete.Then, user manually pulls out connector assembly 32 from receiving seat 13
Out.
In conclusion main beneficial effect of the invention is: when being quickly equipped with mounting mechanism and removable mechanism, needing to insert
It is remote that second square type shell could be inserted into the first square type shell far from one end of rotor mechanism after being properly inserted into receiving seat by headstock
Disembark in one end of body, otherwise the second square type shell, which can not be successfully, is inserted into the first square type shell, ensure that with mounting mechanism with it is removable
After mechanism is quickly equipped with, the first electric wire and the second electric wire can be powered well；To eliminate the secondary trouble dismantled and checked.This hair
Bright structure 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, sliding panel, the receiving seat with receiving channel, metal receiving tube, wherein one end of the first square type shell is fixedly mounted on
On fuselage side；First fixed block is fixedly mounted in the first square type shell, and one end of sliding panel has wedge angle, and the other end is equipped with
Receive seat；Sliding panel is mounted in the first sliding groove of the first fixed block by way of being slidably matched；Seat is received to cannot be introduced into
Into the first sliding groove, and the one end of seat far from sliding panel is received to be flush with the first square type shell far from one end of fuselage；Three
Metal receiving tube is uniformly mounted in the receiving channel for receiving seat；One end of three the first electric wires from receive seat without receiving channel one
Side enters to be connected with three metal receiving tubes respectively, and the other end passes through fuselage and connects with being electrically connected in fuselage；
Above-mentioned first square type shell also has the A spring for generating pulling force to the first square type shell center position to receiving seat；
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, wherein one end of the second square type shell is connected with above-mentioned rotor mechanism, the other end and first one end of square type shell far from fuselage
Form insertion cooperation；Three metal ferrules are uniformly mounted in the plug slot of connector assembly；One end of three the second electric wires from insert
Headstock enters without the side of plug slot and is connected respectively with three metal ferrules, and the other end passes through the second square type slot and above-mentioned gyroplane
Motor in structure is mutually electrically connected；
Three metal ferrules of three metal receiving tubes and connector assembly in above-mentioned receiving seat are mutually inserted into cooperation；
There is the baffle that slides in the second square type shell in above-mentioned second square type shell, and baffle to the second square type shell far from gyroplane
One end port of structure forms and blocks；When baffle is not by external force, the B spring in the second square type shell can guarantee baffle
It is always positioned at one end port of the second square type shell far from rotor mechanism；When connector assembly is not affected by external force, connector assembly is being kept off
The effect of blocking of plate is lower and cannot be introduced into the second square type shell；When the second square type shell is inserted into far from one end of rotor mechanism
After one square type shell is far from one end of fuselage, connector assembly is entered in the second square type shell by squeezing baffle；
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. the removable quadrotor drone of one kind according to claim 1, it is characterised in that: above-mentioned rotor mechanism further includes
Drive shaft and set casing, wherein one end of above-mentioned second square type shell is fixedly connected with set casing；Motor is fixedly mounted in set casing；
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 mounted on
Drive shaft is pierced by one end periphery of 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. the removable quadrotor drone of one kind according to claim 1, it is characterised in that: above-mentioned to further include with mounting mechanism
A guide rail, A guide block, the first fixing seat, limited mouth, two of them A guide rail are symmetrically and fixedly mounted to the first of above-mentioned first square type shell
On the two sides groove face of square type slot；A guide rail is located at the first square type shell phase and is connected between one end of fuselage and above-mentioned first fixed block；The
The two sides of one fixing seat are symmetrically installed there are two A guide block；Two A guide blocks are separately mounted to two A by way of being slidably matched
In guide rail；One end of two above-mentioned A springs is separately mounted on two A guide blocks, and the other end is separately mounted to the interior of two A guide rails
On wall surface；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 sliding panel and is connected respectively with three metal receiving tubes on seat are received；
When receive seat outer bottom seat surface and the first fixed block respective surfaces fit when, the first fixing seat and receiving seat between three
A first electric wire is in tension, and three the first electric wires between the first fixing seat and fuselage outer surface are in relaxed state,
A spring is in tensional state at this time.
4. the removable quadrotor drone of one kind according to claim 1, it is characterised in that: above-mentioned removable mechanism further includes
B guide groove, B guide block, the second sliding groove, C guide groove, limited block, C guide block, C spring, the second fixing seat, wherein above-mentioned second square type shell
Possessed structure is identical on the two sides groove face of the second square type slot at one end far from rotor mechanism；For the second square type slot
Any one side channel face: open that there are two B guide grooves on the side channel face of the second square type slot in a manner of symmetrical up and down；The side of second square type slot
It is provided with the second sliding groove of perforation on groove face, the two sides of the second sliding groove symmetrically open that there are two C guide grooves；Second sliding groove is located at two
Between a B guide groove；
There are two above-mentioned baffle tools；Two baffles are mounted on the second square type slot of the second square type shell by way of being slidably matched
In, and two baffles are distributed in a manner of symmetrical up and down；The two sides of each baffle are symmetrically installed there are two B guide block；It is right up and down
Claim that there is spacing between two baffles of distribution；
For the two sides groove face of the second square type slot: institute's mounting structure and two B for being located at downside on two B guide grooves of upside
Institute's mounting structure is identical on guide groove, and for being located at two B guide grooves of upside: two B guide blocks positioned at the baffle of upside pass through cunning
The mode of dynamic cooperation is separately mounted in two B guide grooves, and one end of two B springs is separately mounted on two B guide blocks, the other end
It is separately mounted on the side channel face of two B guide grooves, two B springs are located in two B guide grooves；
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 B
Guide groove；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；It is mutually electric with the motor in rotor mechanism that the same end of three the second electric wires passes through the second square type shell
Gas connection, spacing of the same end across two baffles in addition are connected with three metal ferrules on above-mentioned connector assembly；
When B spring is not compressed by external force, B guide block enables one end end of the corresponding baffle by the second square type shell far from rotor mechanism
Mouth blocks；When connector assembly is located at the outside of the second square type shell, connector assembly is generated with two baffles amplexiforms touching and connector assembly does not squeeze
When pressing two baffles, three the second electric wires between connector assembly and the second fixing seat are in relaxed state；
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. the removable quadrotor drone of one kind according to claim 4, it is characterised in that: above-mentioned C spring is compression bullet
Spring；When limited block is not affected by external force, corresponding C spring is not affected by compression, and limited block is arrived far from the one end on the first inclined-plane
There are spacing between corresponding second sliding groove and the notch of the second square type slot connecting place.
6. the removable quadrotor drone of one kind according to claim 3 or 4, it is characterised in that: in above-mentioned limited block with
The connected side in 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 shell
Two limiting cuttings mutually limit cooperation；When the second square type shell is inserted into the first square type shell far from machine far from one end of rotor mechanism
During one end of body, 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
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, limit
The lateral part surface of position 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. the removable quadrotor drone of one kind according to claim 1, it is characterised in that: the receiving channel of above-mentioned receiving seat
Two sides symmetrically open there are two the first guide groove；One elastic bumps is installed on the side channel face of each guide groove；Above-mentioned connector assembly
Two sides be 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
First guide block respectively with the elastic bumps phase extrusion fit in two the first guide grooves.
8. the removable quadrotor drone of one kind according to claim 7, it is characterised in that: above-mentioned elastic bumps are by rubber
Material is made.
9. the removable quadrotor drone of one kind according to claim 1, it is characterised in that: above-mentioned receiving seat is by insulation material
Material is made；Above-mentioned metal receiving tube is made of copper product.
10. the removable quadrotor drone of one kind according to claim 1, it is characterised in that: above-mentioned connector assembly is by insulating
Material is made；Above-mentioned metal ferrule is made of copper product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811523543.6A CN110001940A (en) | 2018-12-13 | 2018-12-13 | A kind of removable quadrotor drone |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811523543.6A CN110001940A (en) | 2018-12-13 | 2018-12-13 | A kind of removable quadrotor drone |
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| Publication Number | Publication Date |
|---|---|
| CN110001940A true CN110001940A (en) | 2019-07-12 |
Family
ID=67165119
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811523543.6A Withdrawn CN110001940A (en) | 2018-12-13 | 2018-12-13 | A kind of removable quadrotor drone |
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| CN (1) | CN110001940A (en) |
Citations (19)
| 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 |
-
2018
- 2018-12-13 CN CN201811523543.6A patent/CN110001940A/en not_active Withdrawn
Patent Citations (19)
| 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 |
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