CN109319086A - Unmanned aerial vehicle rack and unmanned plane - Google Patents
Unmanned aerial vehicle rack and unmanned plane Download PDFInfo
- Publication number
- CN109319086A CN109319086A CN201710648955.1A CN201710648955A CN109319086A CN 109319086 A CN109319086 A CN 109319086A CN 201710648955 A CN201710648955 A CN 201710648955A CN 109319086 A CN109319086 A CN 109319086A
- Authority
- CN
- China
- Prior art keywords
- transfer warehouse
- aerial vehicle
- unmanned aerial
- side wall
- loading plate
- 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.)
- Granted
Links
- 238000012546 transfer Methods 0.000 claims abstract description 109
- 238000007789 sealing Methods 0.000 claims abstract description 32
- 238000009434 installation Methods 0.000 claims description 47
- 210000001364 upper extremity Anatomy 0.000 claims description 40
- 238000003860 storage Methods 0.000 claims description 19
- 239000007788 liquid Substances 0.000 claims description 16
- 230000002787 reinforcement Effects 0.000 claims description 12
- 230000007306 turnover Effects 0.000 claims description 12
- 230000005611 electricity Effects 0.000 claims description 10
- 239000011148 porous material Substances 0.000 claims description 4
- 239000007921 spray Substances 0.000 claims description 4
- 239000012780 transparent material Substances 0.000 claims 1
- 238000013461 design Methods 0.000 abstract description 14
- 238000010586 diagram Methods 0.000 description 17
- 238000000034 method Methods 0.000 description 8
- 238000005086 pumping Methods 0.000 description 8
- 230000008569 process Effects 0.000 description 7
- 230000005484 gravity Effects 0.000 description 5
- 230000006698 induction Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000007613 environmental effect Effects 0.000 description 4
- 230000000007 visual effect Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 230000008878 coupling Effects 0.000 description 3
- 238000010168 coupling process Methods 0.000 description 3
- 238000005859 coupling reaction Methods 0.000 description 3
- 238000000354 decomposition reaction Methods 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 238000009429 electrical wiring Methods 0.000 description 3
- 239000000945 filler Substances 0.000 description 3
- 238000003780 insertion Methods 0.000 description 3
- 230000037431 insertion Effects 0.000 description 3
- 239000007787 solid Substances 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000003139 buffering effect Effects 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005381 potential energy Methods 0.000 description 2
- 238000000889 atomisation Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000003776 cleavage reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000011982 device technology Methods 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 230000004807 localization Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000007017 scission Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
-
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D1/00—Dropping, ejecting, releasing, or receiving articles, liquids, or the like, in flight
- B64D1/16—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting
- B64D1/18—Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting by spraying, e.g. insecticides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Forklifts And Lifting Vehicles (AREA)
- Warehouses Or Storage Devices (AREA)
Abstract
The present invention provides a kind of unmanned aerial vehicle rack and unmanned planes, wherein unmanned aerial vehicle rack includes: fuselage loading plate, and fuselage loading plate is for installing first element and second element；Transfer warehouse, transfer warehouse is installed on fuselage loading plate, transfer warehouse forms the connecting cavity with open end, transfer warehouse is equipped with through-hole, through-hole is connected with connecting cavity, wherein first element and second element are located at outside transfer warehouse, for through-hole for passing through for the connecting line of first element and the connecting line of second element, connecting cavity is used to accommodate the connecting interface of the connecting line of first element and the connecting line of second element；Transfer warehouse lid, transfer warehouse lid sealing cover are set at the open end of transfer warehouse.It applies the technical scheme of the present invention and is able to solve the technical problem that the airframe structure of unmanned plane existing in the prior art designs the unreasonable waterproof for leading to unmanned plane, protects difficulty big.
Description
Technical field
The invention belongs to aircraft devices technical fields, are to be related to a kind of unmanned aerial vehicle rack and unmanned plane more specifically.
Background technique
Unmanned plane refers to using wireless remote control device and the control sensing device cooperation of itself and is controlled not manned
Aircraft.With the development of unmanned plane during flying device technology, because there is unmanned plane during flying device maneuverability, unmanned flight, operation to want
Low advantage is sought, unmanned plane during flying device has been widely used in agricultural plant protection, photography of taking photo by plane, electric inspection process, environmental monitoring, forest
In the yards such as fire prevention and disaster inspection, the deficiency that manned aircraft carries out aerial work is effectively overcome.
It when carrying out working flight due to unmanned plane, is carried out in environment outdoor outdoors, when encountering rain, greasy weather gas,
Droplet will be collected on the fuselage of unmanned plane, the unmanned plane in agricultural plant protection is especially applied, during agricultural plant protection
Spraying operation, atomization hydrojet when sprinkling, which will result in, collects droplet on unmanned plane, and is mounted on the control on the fuselage of unmanned plane
Sensing device processed and other delicate electronic devices then need to prevent from contacting with droplet, in order to avoid damage.But existing skill
Unmanned plane during flying device in art, the design of airframe structure is unreasonable, causes to carry route, the pipeline, water route being connected on fuselage
Be laid out it is unreasonable so that the water route interface of the pipe interface and each water route of the line interface of each route, each pipeline
Waterproof, protection difficulty are big.
Summary of the invention
The purpose of the present invention is to provide a kind of unmanned aerial vehicle rack and unmanned plane, with solve it is existing in the prior art nobody
The airframe structure of machine designs the big technical problem of the unreasonable waterproof for leading to unmanned plane, protection difficulty.
To achieve the above object, the technical solution adopted by the present invention is that: provide a kind of unmanned aerial vehicle rack, comprising: fuselage is held
Support plate, fuselage loading plate is for installing first element and second element；Transfer warehouse, transfer warehouse are hermetically installed on fuselage and hold
Support plate, transfer warehouse form the connecting cavity with open end, and transfer warehouse is equipped with through-hole, and through-hole is connected with connecting cavity,
In, first element and second element are located at outside transfer warehouse, and through-hole is used for for the connecting line of first element and the company of second element
Wiring passes through, and connecting cavity is used to accommodate the connecting interface of the connecting line of first element and the connecting line of second element；Transfer warehouse lid,
Transfer warehouse lid sealing cover is set at the open end of transfer warehouse.
According to another aspect of the present invention, a kind of unmanned plane is provided.The unmanned plane includes: first element, second element
And rack, rack position unmanned aerial vehicle rack above-mentioned, the fuselage loading plate of first element and second element installation and unmanned aerial vehicle rack
On.
Assembly unmanned plane is carried out using the unmanned aerial vehicle rack, so that being formed with transfer in unmanned aerial vehicle rack after the assembly is completed
The connecting cavity of warehouse, at this point, the connecting interface of the connecting line of the route arrangement in unmanned plane is accommodated in the connection of transfer warehouse
In chamber, so that the jointing of connecting line is designed in such a way that stealth is laid, so that unmanned plane after the assembly is completed will not be by
To the in disorder influence of connecting interface of connecting line, overall appearance seems more clean and tidy, beautiful, and by transfer warehouse to connecting line
Connecting interface protected, the connecting interface for eliminating connecting line is influenced poor contact, damage etc. occur by external environmental factor
Problem.
Detailed description of the invention
It to describe the technical solutions in the embodiments of the present invention more clearly, below will be to embodiment or description of the prior art
Needed in attached drawing be briefly described, it should be apparent that, the accompanying drawings in the following description is only of the invention some
Embodiment for those of ordinary skill in the art without any creative labor, can also be according to these
Attached drawing obtains other attached drawings.
Fig. 1 is the first assembling structure schematic diagram of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 2 is the second assembling structure schematic diagram of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 3 is the structural schematic diagram of the first loading plate of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 4 is the structural schematic diagram of the second loading plate of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 5 is the structural schematic diagram at the first visual angle of the transfer warehouse of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 6 is the structural schematic diagram at the second visual angle of the transfer warehouse of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 7 is the structural schematic diagram of the transfer warehouse lid of the unmanned aerial vehicle rack of the embodiment of the present invention；
Fig. 8 is the assembling structure signal of the horn of the unmanned aerial vehicle rack of the embodiment of the present invention, connection lantern ring, sealing ring
Figure；
Fig. 9 is that the fixed connecting base of the unmanned aerial vehicle rack of the embodiment of the present invention is illustrated with the decomposition texture for being fixedly connected with pressure ring
Figure；
Figure 10 is the structural schematic diagram of the installing frame of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 11 is the structural schematic diagram of the seal tube of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 12 is the structural schematic diagram of the sealing ring of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 13 is the structural schematic diagram of the seal joint of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 14 is the structural schematic diagram of the front leg strut of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 15 is the structure of the rear support leg of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 16 is the decomposition texture schematic diagram of the foot prop of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 17 is the structural schematic diagram after being completed of foot prop of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 18 is that the structure of the installation condition of the foot prop of the unmanned aerial vehicle rack of the embodiment of the present invention is intended to；
Figure 19 is the decomposition texture schematic diagram of fastening assembly in the foot prop of the unmanned aerial vehicle rack of the embodiment of the present invention；
Figure 20 is the structural schematic diagram at the first visual angle of the unmanned plane of the embodiment of the present invention；
Figure 21 is the structural schematic diagram at the second visual angle of the unmanned plane of the embodiment of the present invention.
Wherein, each appended drawing reference in figure:
10, fuselage loading plate；11, the first loading plate；12, the second loading plate；111, the first matching hole；121, the second cooperation
Hole；20, transfer warehouse；211, connecting cavity；212, installation through-hole；22, bottom wall；221, the first punched out；222, the second punched out；
30, horn；40, transfer warehouse lid；41, seal groove；91, it is fixedly connected with component；911, fixed connecting base；912, it is fixedly connected with pressure
Ring；913, lantern ring is connected；9131, lug is connected；9111, limiting groove；50, installing frame；51, assembly space；52, separate cross bar；
511, the first assembly space；512, the second assembly space；513, power supply connector installation space；92, it leads and holds connection component；201,
One side wall；202, second sidewall；203, third side wall；60, outlet pot shell；93, sealing connecting component；931, seal tube；
932, sealing ring；9321, sealed connection portion；933, seal joint；9331, link slot；9311, connection bump；213, side wall
Protrusion；214, seal convexity；215, the first screw engaging lug；70, power installs sheath body；80, foot prop；110, front leg strut；130,
Rear support leg；9312, closure gasket groove；9322, the second screw engaging lug；93210, fitting projection；9332, third screw engaging lug；
01, rack；02, power device；03, flusher；04, pumping installations；05, liquid storage container；06, housing；07, power supply storage battery
Module；08, induction antenna；2031, through-hole is plugged；31, threading hole；1110, first connecting portion；1120, the first rebate；
1130, front support；1140, preceding grounding parts；1150, reinforcement part；1310, second connecting portion；1320, the second rebate；1330,
Rear support portion；1340, rear grounding parts；200, buffer shock-absorbing part；120, connection leg；11100, the first connecting hole；11400, second
Connecting hole；13100, third connecting hole；13400, the 4th connecting hole；300, fastening assembly；310, bolt is connected；320, locking screw
It is female；1210, front end connecting hole；1220, rear end connecting hole.
Specific embodiment
In order to which technical problems, technical solutions and advantages to be solved are more clearly understood, tie below
Accompanying drawings and embodiments are closed, the present invention will be described in further detail.It should be appreciated that specific embodiment described herein is only
To explain the present invention, it is not intended to limit the present invention.
It should be noted that it can be directly another when element is referred to as " being fixed on " or " being set to " another element
On one element or indirectly on another element.When an element is known as " being connected to " another element, it can
To be directly to another element or be indirectly connected on another element.
It is to be appreciated that term " length ", " width ", "upper", "lower", "front", "rear", "left", "right", "vertical",
The orientation or positional relationship of the instructions such as "horizontal", "top", "bottom", "inner", "outside" is that orientation based on the figure or position are closed
System, is merely for convenience of description of the present invention and simplification of the description, rather than the device or element of indication or suggestion meaning must have
Specific orientation is constructed and operated in a specific orientation, therefore is not considered as limiting the invention.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present invention, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
As shown in Figures 1 to 8, the unmanned aerial vehicle rack of the present embodiment includes fuselage loading plate 10, transfer warehouse 20 and transfer
Warehouse lid 40, fuselage loading plate 10 form the connection with open end for installing first element and second element, transfer warehouse 20
Chamber 211, transfer warehouse 20 are equipped with through-hole, and through-hole is connected with connecting cavity 211, and transfer warehouse 20 is sealedly attached to fuselage carrying
On plate 10,40 sealing cover of transfer warehouse lid is located at the open end of transfer warehouse 20, wherein first element and second element are located at institute
It states outside transfer warehouse 20, for passing through for the connecting line of first element and the connecting line of second element, connecting cavity 211 is used for through-hole
Accommodate the connecting interface of the connecting line of first element and the connecting line of second element.
Assembly unmanned plane is carried out using the unmanned aerial vehicle rack, so that being formed with transfer in unmanned aerial vehicle rack after the assembly is completed
The connecting cavity 211 of warehouse 20, at this point, the route arrangement in unmanned plane (can be physical cord laying, such as pipeline line；It can also be with
It is that electric wire is laid；The application is illustrated so that electrical wiring is laid as an example) the connecting interface of connecting line be accommodated in middle roll-over
In the connecting cavity 211 of body 20, so that the jointing of connecting line is designed in such a way that stealth is laid, so that unmanned plane assembles
The in disorder influence of connecting interface of connecting line is not will receive after the completion, overall appearance seems more clean and tidy, beautiful, and passes through transfer
Warehouse 20 protects the connecting interface of connecting line, and the connecting interface for eliminating connecting line is influenced to connect by external environmental factor
Touch it is bad, damage the problems such as.Moreover, first element and second element are located at outside transfer warehouse 20, transfer warehouse 20 can reduce
Volume.
The unmanned aerial vehicle rack of the present embodiment includes multiple horns 30, and each horn 30 has opposite first end and second end,
Each horn 30 has the hollow cavity of perforation first end and second end, and the first end connection end of each horn 30 is fixedly connected on fuselage
On loading plate 10, transfer warehouse 20 includes the first side wall 201 around connecting cavity, and the through-hole of transfer warehouse 20 includes being set to first
Installation through-hole 212 on side wall 201, the first end of horn 30 are sealedly attached on the first side wall 201, multiple horns 30 with it is multiple
Installation through-hole 212 corresponds, i.e. the hollow cavity and installation through-hole 212 of the connection of installation through-hole 212 horn 30, and the second of horn 30
End is used to pass through for the connecting line of second element for installing second element, hollow cavity and installation through-hole 212, and second element
Interfaces of connecting wires is located in connecting cavity 211.By application connecting cavity 211 and the hollow cavity of combination horn 30, so that not only
The connecting interface of the connecting line of the first element, second element that are only mounted on fuselage loading plate 10 is accommodated in connecting cavity,
And the connecting line of the second element on the end for being installed on horn 30 is made to carry out wearing extension by hollow cavity, then by
The interfaces of connecting wires of two element is accommodated in connecting cavity, to further realize the stealth of route arrangement after unmanned plane assembly
Effect is stored, so that unmanned aerial vehicle rack integrally seems clean and tidy, beautiful.
In this embodiment, seal convexity 214 is circumferentially on the end of the open end of transfer warehouse 20, in transfer warehouse lid 40
It is circumferentially with seal groove 41, the sealing cooperation of seal convexity 214 is in seal groove 41.In assembling process, by by transfer warehouse lid
Seal groove 41 on 40 is directed at seal convexity 214, so that the insertion of seal convexity 214 extends into seal groove 41, then utilizes spiral shell
It is fixedly connected between nail centering roll-over lid 40 and fuselage loading plate 10, thus realize the sealing of the open end of connecting cavity 211,
It is, transfer warehouse lid 40 is removably attached to transfer warehouse 20.
As shown in Figures 1 to 4, the present embodiment middle fuselage loading plate 10 includes the first loading plate 11 and the second loading plate 12,
First loading plate 11 is oppositely arranged with the second loading plate 12, and transfer warehouse 20 is located at the first loading plate 11 and the second loading plate 12
Between.Support is formed by the first loading plate 11 and the common centering roll-over body 20 of the second loading plate 12 and multiple horns 30, from
And mechanical strength itself that increase unmanned aerial vehicle rack, also, be connected between the first loading plate 11 and the second loading plate 12
Roll-over body 20 and horn 30, not only form the connecting cavity 211 of the sealing of transfer warehouse 20, while also forming biggish exposed
Installation space, by carrying out effectively benefit to the exposed installation space formed between the first loading plate 11 and the second loading plate 12
With, remaining corresponding components being applied to required in unmanned plane assembling process can be mounted in exposed installation space, from
And the space utilization rate of unmanned aerial vehicle rack is improved (in fact, the assembly components being mounted in these exposed installation spaces
Waterproof, requirement of shelter be not high, relatively easily can realize waterproof, protection to these assembly components).In addition, the first carrying
Plate 11 is equipped with the first matching hole 111, and the second loading plate 12 is equipped with the second matching hole 121, the open end of connecting cavity 211 and the
One matching hole 111 is oppositely arranged, and transfer warehouse 20 is covered on the second matching hole 121, wherein transfer warehouse 20 further includes bottom wall
22, the first side wall 201 is extended vertically from bottom wall 22, and the through-hole of transfer warehouse 20 further includes opening up on bottom wall 22
First punched out 221 and the second punched out 222, at this point, the second matching hole 121 passes through the first punched out 221 and the second punched out
222 are connected with connecting cavity 211, and the open end of connecting cavity 211 is oppositely arranged with the first matching hole 111.In the present embodiment, first
Element includes that the electricity outside transfer warehouse 20 is adjusted, and the first punched out 221 is pierced by for the connecting line adjusted of powering, and second element is then
Motor including being installed on 30 second end of horn, the connecting line of motor pass through the hollow of corresponding installation through-hole 212 and horn 30
The interface of chamber, the connecting line of connection and motor that electricity can in this way adjusted is respectively positioned in the connecting cavity 211 of transfer warehouse 20.
The transfer warehouse 20 of the present embodiment further includes second sidewall 202, and second sidewall 202 is connected on the first side wall 201.
Transfer warehouse 20 may include there are four the first side wall 201 or including there are six the first side wall 201 or include eight the
One side wall 201 etc., accordingly, the quantity of horn 30 are four or six or eight.Preferably, the transfer warehouse 20 of the present embodiment includes
There are four the first side wall 201, the quantity of horn 30 is four, also, four the first side walls 201 are averaged low level in second sidewall 202
Two sides, the through-hole of transfer warehouse 20 further includes the intercommunicating pore in the second sidewall 202, that is, is arranged in second sidewall
The slot space of outlet pot shell 60 on 202, outlet pot shell 60 is connected with connecting cavity 211.It is assembled when assembling and completes unmanned plane machine
When after frame and the unmanned aerial vehicle rack being applied to unmanned plane machine assembly, staff is by the connecting line of flight controller from out
It is pierced by wire casing shell 60, and is electrically connected between flight controller and electricity tune, the connecting line of flight controller and electricity are adjusted at this time
Connecting interface between connecting line is located in the connecting cavity 211 of transfer warehouse 20, and by going out using waterproof washer setting
In wire casing shell 60, reliable, good sealing is carried out to realize and be pierced by intercommunicating pore to connecting line.
First element includes the liquid storage container outside transfer warehouse 20 in the present embodiment, and transfer warehouse 20 further includes
Third side wall 203, third side wall 203 are connected to the first side wall 201, and third side wall 203 is oppositely arranged with second sidewall 202, and four
A the first side wall 201 is also fifty-fifty located at the two sides of third side wall 203. simultaneously, and the through-hole of transfer warehouse 20 further includes being set to the
Through-hole 2031 is plugged on three side walls 203, this plugs connecting line of the through-hole 2031 for for liquid storage container and is pierced by, and this implementation
The second element of example further includes the spray head (i.e. flusher 03) for the second end for being installed on horn 30, the connecting line of flusher 03
Across the hollow cavity and installation through-hole 212 of horn 30, so that the connecting line of the interfaces of connecting wires of liquid storage container and flusher 03
Interface is respectively positioned in the connecting cavity 211 of transfer warehouse 20.
In conjunction with referring to shown in Fig. 1, Fig. 2, Figure 10, unmanned aerial vehicle rack further includes installing frame 50, which can apply
Power supply storage battery module 07 is connected in installation, for applying the plant protection drone in plant protection operation, i.e., the plant protection of the invention applied
Operation unmanned plane, the installing frame 50 are not only applicable to installation connection power supply storage battery module 07, are also applied to installation connection plant protection
The liquid storage container 05 of medical fluid is stored during sprinkling.In the present embodiment, the first side of installing frame 50 is fixedly connected on second and holds
On support plate 12, installing frame 50 is located between two horns 30, and installing frame 50 holds connection component 92 and be fixedly connected on phase by leading
On two adjacent horns 30, meanwhile, the first side of installing frame 50 is also fixedly connected with the third side wall 203 of transfer warehouse 20, peace
Frame up 50 second side along horizontal extension.
Specifically, as shown in Figure 10, the installing frame 50 of the present embodiment is formed with assembly space 51, and assembly space 51 is by dividing
It is separated into the first assembly space 511 and the second assembly space 512 every cross bar 52, the second assembly space 512 is far from fuselage loading plate
10, at this point, the second assembly space 512 in installing frame 50 is i.e. for installing connection power supply storage battery module 07, and the second dress
Power supply connector installation space 513 is offered on the side wall of separate fuselage loading plate 10 with space 512, power supply connector (is not schemed
Show) it is placed in the power supply connector installation space 513, and the power supply connector is electrically connected by connecting wire and flight controller
It connects, and the connecting wire between power supply connector and flight controller is laid along the frame edge of installing frame, preferably
Holding tank is opened up on frame edge, connection guiding is contained in the holding tank at frame edge.In the present embodiment, the first dress
With space 511 then for assembling liquid storage container 05.In addition, can will take photo by plane camera shooting for the unmanned plane applied to photography of taking photo by plane
The installation of the equipment such as machine is connected in the first assembly space 511, or the unmanned plane for being applied to plant protection operation, and the first assembly is empty
Between 511 for install connection liquid storage container 05.The end institute of the separate fuselage loading plate 10 of multiple horns 30 of the present embodiment
It is located in the regional scope of the first assembly space 511 in round center of circle projection, that is to say, that either just assembling assembly is completed
The position of centre of gravity of unmanned aerial vehicle rack has either completed the position of centre of gravity of the unmanned plane complete machine of assembling assembly, all position of centre of gravitys
Projection be always positioned in the regional scope of the first assembly space 511, the offset variation between actually all position of centre of gravitys
It always is the progress offset variation in the preset range for ensuring flight stability.
As shown in Figure 14 and Figure 15, provided foot prop 80 includes front leg strut 110 and rear support leg 130, wherein front leg strut
110 include front support 1130 and the first rebate 1120, and front support 1130 is connect with the first rebate 1120, and preceding
The junction of support portion 1130 and the first rebate 1120 forms the first turn turnover, separate first detour of front support 1130
The one end in portion 1120 is used to support in supporting surface, and one end of the separate front support 1130 of the first rebate 1120 is for connecting machine
Body loading plate 10, and first turn round turnover opening towards rear support leg 130.
Unmanned plane is helped to realize in normal takeoff operational and landing operation, especially descent using the foot prop 80,
Unmanned plane is hit in the recoil being instantaneously supported in face of foot prop 80 for dropping to supporting surface, if cannot effectively cut down impact force
Transmitting, will damage the accurate spare and accessory parts of unmanned plane.The front leg strut 110 of the foot prop 80 is using front support 1130 and the
The first turn turnover is formed between one rebate 1120 and makes front leg strut 110 that there is good elasticity capacity, is hit with resistance to,
The anti-force of supporting surface can be converted to the elastic potential energy of front leg strut 110, in this way, unmanned plane is suffered in descent
Anti-force effectively cut down, while also can satisfy in unmanned plane use process to the intensity requirement of foot prop 80.
During actual installation assembles unmanned plane, phase is can be selected in two front leg struts and two rear support legs of foot prop 80
Same structure type, such as all select and form foot prop 80 as above-mentioned front leg strut 110 carries out installation；It can also be in unmanned plane
Front end select above-mentioned front leg strut 110 to be installed, and rear support leg 130 then selects other can satisfy in the prior art to rise and fall
The supporting leg form that flight requires is installed；Or above-mentioned front leg strut 110 is selected to design in two rear support legs of unmanned plane
Form is as rear support leg 130, and front leg strut 110 then selects other prior arts to can satisfy the supporting leg form that flight of rising and falling requires
Supporting leg.
Following in the application illustrates in record that front leg strut 110 is pacified from rear support leg 130 using different structure type
Dress forms foot prop 80, to illustrate the structure design of foot prop 80 of the invention.
As shown in figure 15, rear support leg 130 includes rear support portion 1330 and the second rebate 1320, rear support portion 1330 and the
The connection of two rebate 1320, and form the second turn in rear support portion 1330 and the junction of the second rebate 1320 and transfer,
Rear support portion 1330 is used to support far from one end of the second rebate 1320 in supporting surface, the second rebate 1320 far from after
One end of support portion 1330 is for being connected to installing frame, and second turns round the opening transferred towards front leg strut 110, further
Ground, using supporting surface as reference plane, then the second inflection point for turning round turnover is turned round relative to the height distance of supporting surface less than first
Height distance of the inflection point of turnover relative to supporting surface.In the same manner as front leg strut 110, the rear support portion 1330 of rear support leg 130 with
Second is formed between second rebate 1320 turns round turnover so that rear support leg 130 has good elastic deformation ability, thus resistance to
By the impact force that supporting surface generates it, the anti-force of supporting surface can be converted to the elastic potential energy of rear support leg 130, so that
Unmanned plane anti-force suffered in descent is effectively cut down, while also can satisfy unmanned plane use process
To the intensity requirement of foot prop 80.
Due in unmanned plane during flying descent, since supporting surface acts on anti-force caused by foot prop 80 at first
One end for being supported in supporting surface of front leg strut 110 and one end for being supported in supporting surface of rear support leg 130, and anti-force is instantaneous
Effect causes front support 1130 and rear support portion 1330 to cause violent deformation, and then impact force is along front leg strut 110 with after
Supporting leg 130 is transmitted to fuselage loading plate 10 and installing frame, in order to enable front leg strut 110 and rear support leg 130 meeting support
Under the premise of intensity, by the first rebate 1120 and front support 1130 of front leg strut 110 by fuselage loading plate 10 to supporting surface
Direction in successively reduce setting, and by the second rebate 1320 of rear support leg 130 and rear support portion 1330 by installing frame extremely
The direction of supporting surface is in setting is successively reduced, in this way, making in front support 1130 and rear support portion 1330 closer to supporting surface
Part bending deformability it is stronger, impact force dissolved by the flexible deformation of itself when bearing instantaneous impact effect
Damage capability.
Front leg strut 110 of the invention further includes first connecting portion 1110 and preceding grounding parts 1140, and rear support leg 130 further includes
Two interconnecting pieces 1310 and rear grounding parts 1340.The first end of first connecting portion 1110 is connected in the first rebate 1120, first
The second end of interconnecting piece 1110 extends horizontally, and first connecting portion 1110 is connected on the bottom of fuselage loading plate 10, such as Figure 14
Shown, front leg strut 110 is fastenedly connected using screw in machine by the first connecting hole 11100 opened up in first connecting portion 1110
On the bottom of body loading plate 10, and first connecting portion 1110 and the bottom surface of fuselage loading plate 10 are the horizontal plane way of contact
Connection.The first end of preceding grounding parts 1140 is connected to be used to support on the support surface on front support 1130, preceding grounding parts
1140 second end extends horizontally towards rear support leg 130.The first end of second connecting portion 1310 is connected to the second rebate
On 1320, the second end of second connecting portion 1310 extends along the vertical direction, and second connecting portion 1310 is connected to the avris of installing frame
On, as shown in figure 15, rear support leg 130 is connected by the third connecting hole 13100 being provided in second connecting portion 1310 using screw
It connects on the side wall of the rear end of fuselage loading plate 10, i.e. contact between second connecting portion 1310 and the side wall of fuselage loading plate 10
Face is the surface that vertical direction extends.The first end of grounding parts 1340 is connected in rear support portion 1330 and is being propped up with being used to support afterwards
On support face, the second end of rear grounding parts 1340 extends horizontally towards front leg strut 110.
In order to further increase the support strength of front leg strut 110 and rear support leg 130, as shown in figure 14, front leg strut 110 is also wrapped
Reinforcement part 1150 is included, reinforcement part 1150 is arranged in the first rebate 1120, and reinforcement part 1150, which turns round to transfer along first, to be extended
To front support 1130, and reinforcement part 1150 also extends in first connecting portion 1110 simultaneously, in this way, front leg strut 110
Mechanical strength is effectively enhanced, as shown in figure 15, the cross-section profile shape perpendicular to center axis thereof of the second rebate 1320
To be triangular shaped, and the second rebate 1320 is equipped with hollow cavity, and filled with support filler in hollow cavity, to reduce
The manufacture material of rear support leg 130 consumes, while can also be formed to rear support portion 1330 in manufacturing process using support filler
It supports and is unlikely to 1330 collapse-deformation of rear support portion with hollow cavity.Certainly, the rear support portion 1330 of cylindrical form can also
It is straight interior using the hollow cavity of the design form of solid cylinder or rear support portion 1330 and to be not filled with any support filler
Connect reservation hollow form.
During the landing of practical operation unmanned plane, due to first connecting portion 1110, the first rebate 1120, Yi Jiyu
Enhancing Mechanical Strength Design is carried out by reinforcement part 1150 on part front support 1130 similar in first rebate 1120, then is dropped
When falling on the anti-force for being instantaneously supported face effect of supporting surface, force localization acts on not having for front support 1130
It is strengthened on the part of the enhancing of portion 1150 intensity.It thus, has been more than front leg strut when suffered anti-force is instantaneously excessive
The flexible deformation that 110 front support 1130 is able to bear, the at this time increasing of portion 1150 that do not strengthened of front support 1130
Latent part will be broken by force, and reasonable design is then passed through in the position being broken, so that fracture position is apart from machine
The position of body loading plate 10 is farthest, to the minimum of damaged condition caused by unmanned plane.For rear support leg 130, intensity is smaller
Rear support portion 1330 be equally the most weak position of stress-bearing capability, bear instantaneous impact be more than its bearing capacity when it is then first
Fracture first occurs in rear support portion 1330 and offsets impact force.
Due to having carried out reasonably optimizing to the design of the intensity distribution of front leg strut 110 in the present invention, i.e., first connecting portion 1110,
First rebate 1120, front support 1130, preceding grounding parts 1140 and reinforcement part 1150 are in setting is successively reduced, in this way, logical
Intensity distribution design after crossing reinforcement part 1150 and optimization combines, it can be ensured that each forced breakage to be respectively positioned on first circuitous
It returns between portion 1120 and preceding grounding parts 1140 far from fuselage loading plate 10.Similarly, the intensity distribution design of rear support leg 130
Reasonably optimizing is carried out, i.e. second connecting portion 1310, the second rebate 1320, rear support portion 1330 and rear grounding parts 1340 are in
Setting is successively reduced, so that being respectively positioned on rear support portion 1330 and rear grounding parts in the position that being broken occurs in rear support leg 130 every time
Between 1340, it is ensured that forced breakage point is far from fuselage loading plate 10 and installing frame, by the damage to fuselage loading plate 10 and installing frame
Bad degree is minimized.
Since each supporting leg of foot prop 80 is to be obliquely installed after installation is fixed along the lateral direction of unmanned plane, it is
Beautyization of the Mechanical Strength Design and front leg strut 110 that meet front leg strut 110 simultaneously designs, as shown in figure 14, reinforcement part
1150 outsides that first connecting portion 1110, front support 1130 and the first rebate of part 1120 is arranged in form bound edge.In this way,
While realizing enhances mechanical strength, the design form of side bound edge can make the appearance of front leg strut 110 seem full thick and heavy, mention
Rise the external texture of foot prop 80.
As shown in fig. 16 and fig. 19, which further includes buffer shock-absorbing part 200, the preceding grounding parts 1140 of front leg strut 110
It is upper that buffer shock-absorbing part 200 is connected with by fastening assembly 300, pass through fastening assembly 300 on rear grounding parts 1340 and is connected with buffering
Vibration-damped component 200, in this way, abatement impact force can be further realized by buffer shock-absorbing part 200 in unmanned plane descent,
Impact force is reduced to be transmitted to 10 direction of fuselage loading plate.The perforation that grafting grounding parts are opened up on buffer shock-absorbing part 200 is inserted
Hole is connect, is in addition opening up the receiving hole for accommodating connection bolt 310.By 200 assembly connection of buffer shock-absorbing part corresponding
During the grounding parts of supporting leg, such as before buffer shock-absorbing part 200 is connected on grounding parts 1140, assembly work personnel will before
In the insertion perforation spliced eye of grounding parts 1140, and make the second connecting hole 11400 and receiving hole phase of grounding parts 1140 before being opened in
To setting, then by locking nut 320 be placed on before grounding parts 1140 lower section, then will connection bolt 310 pass through receiving hole and
It is connected on locking nut 320 after second connecting hole 11400, is locked at preceding grounding parts 1140 compression by locking nut 320
It penetrates through the hole wall of spliced eye and is connected and fixed.Similarly, receiving hole and the 4th connecting hole 13400 are passed through using connection bolt 310
After be connected on locking nut 320, by locking nut 320 by rear grounding parts 1340 compress be locked at perforation spliced eye hole wall
And it is connected and fixed.
During unmanned plane landing, when foot prop 80 is instantaneous by what is impacted, four supporting legs of foot prop 80 can occur
Extend out deformation, when extend out deflection it is excessive when, then will lead at the link position of the first connecting portion 1110 of front leg strut 110 with
And acted at the link position of the second connecting portion 1310 of rear support leg 130 by concentrated stress, so just lead to first connecting portion
1110 also belong to easy fracture position with second connecting portion 1310.When being hit in order to avoid foot prop 80 first connecting portion 1110 with
It is broken at second connecting portion 1310, therefore, foot prop 80 further includes connection leg 120, the first end of connection leg 120 and preceding ground connection
Buffer shock-absorbing part 200 in portion 1140 connects, the buffer shock-absorbing part 200 in the second end of connection leg 120 and rear grounding parts 1340
Connection.As shown in figure 16, it is provided with front end connecting hole 1210 in the front end of connection leg 120, is provided with rear end in rear end and connects
Connect hole 1220.During the buffer shock-absorbing part 200 of assembly connection front leg strut 110 and connection leg 120, by connection leg 120
Front end is inserted into the perforation spliced eye of buffer shock-absorbing part 200, and the front end of connection leg 120 and preceding grounding parts 1140 are folded
It sets, the second connecting hole 11400 and 1210 face of front end connecting hole, locking nut 320 is located at the front end of connection leg 120 and passes through
Between the hole wall of logical spliced eye, connection bolt 310 is then connected into locking nut 320, locking nut 320 is by preceding grounding parts 1140
It is pressed on the front end of connection leg 120 on the hole wall of perforation spliced eye.Similarly, it is connected by the rear end of connection leg 120
During on the buffer shock-absorbing part 200 of rear support leg 130, by passing through for the rear end insertion buffer shock-absorbing part 200 of connection leg 120
In logical spliced eye, and the rear end of connection leg 120 and rear grounding parts 1340 are stacked, and the 4th connecting hole 13400 connects with rear end
1220 face of hole is connect, locking nut 320 is located at the rear end of connection leg 120 and penetrates through between the hole wall of spliced eye, then will even
Connecting bolt 310 connects locking nut 320, and the rear end of rear grounding parts 1340 and connection leg 120 is pressed on and passes through by locking nut 320
On the hole wall of logical spliced eye, foot prop 80 after the assembly is completed is referring to shown in Figure 17 and Figure 18.During landing, pass through connection
Leg 120 is drawn between front leg strut 110 and rear support leg 130, to eliminate extending out for front leg strut 110 and rear support leg 130
Trend, it is ensured that the first connecting portion 1110 of front leg strut 110 and the second connecting portion 1310 of rear support leg 130 will not become cleavage
It sets.
As shown in Figure 8 and Figure 9, unmanned plane is being formed to connection between horn 30 and fuselage loading plate 10, transfer warehouse 20
During the basic boom of rack, the connecting pin of each horn 30 is connect by being fixedly connected with component 91 with fuselage loading plate 10,
Component 91 is fixedly connected between the first loading plate 11 and the second loading plate 12, in actual assembled connection, each horn 30
Connection end on be all made of two of interval and be fixedly connected with component 91 horn 30 is fixed on fuselage loading plate 10.Wherein,
Component 91 is fixedly connected with to include fixed connecting base 911, be fixedly connected with pressure ring 912 and connection lantern ring 913.Fixed connecting base 911 is solid
Surely be connected on the second loading plate 12, be fixedly connected with pressure ring 912 and be connected on fixed connecting base 911, be fixedly connected pressure ring 912 with
Clamping space is formed between fixed connecting base 911, horn 30 is assemblied in clamping space, and the first loading plate 11 is fixedly connected on
It is fixedly connected on pressure ring 912, also, connects lantern ring 913 and be set on horn 30, connection lantern ring 913 is equipped with connection lug
9131, specifically connecting on lantern ring 913 is in a 180 degree symmetrically company of being equipped with connection lug 9131, the inside of fixed connecting base 911
It equipped with limiting groove 9111, connects lug 9131 and extends into limiting groove 9111, and connect lantern ring 913 and be clamped in clamping space.
Horn 30 by connection lantern ring 913 and fixed connecting base 911, be fixedly connected between pressure ring 912 and connect, horn 30 can be made opposite
There is the ability of certain damping, buffering in fuselage loading plate 10, to realize horn 30 and fuselage loading plate to a certain extent
Flexible assembly connection between 10.
In other possible embodiments, it is circular that transfer warehouse 20, which can be and surround Formation cross-section chamfered shape by side wall,
Cylindrical structure.
Further, two the first side walls 201 far from second sidewall 202 are the curved surface for concaving towards 211 inside of connecting cavity
Wall, e.g. arc surface side wall or turnover curved surface sidewall.Preferably, two the first side walls 201 are by two small straight walls by turning
Folding connection and the side wall (i.e. turnover curved surface sidewall) that is formed to 211 indent of connecting cavity, and installation through-hole 212 be located at it is two small
In the small straight wall of separate third side wall 203 in straight wall.In this way, the installation through-hole 212 opened up in the two small straight walls is corresponding
Horn 30 is drawn close to the center axis of symmetry of unmanned aerial vehicle rack, that is, the folder being connected between the horn 30 in the two small straight walls
Angle is less than the angle between the horn 30 being connected on two the first side walls 201 of second sidewall 202, thus by unmanned plane
The whole extending direction along installing frame 50 of the position of centre of gravity of rack or unmanned plane deviates, so that the assembly space of installing frame 50
It is bigger, it flies to meet unmanned plane and can carry more articles (or carrying more medical fluids).
Junction between two neighboring side wall is equipped with the first screw engaging lug 215, and transfer warehouse 20 is matched by screw
It closes corresponding first screw engaging lug 215 to be fixedly connected on the second loading plate 12, then the first loading plate 11 is worn by screw
It is cooperatively connected on corresponding first screw engaging lug 215 after crossing the first loading plate 11 to achieve a fixed connection.
In order to further realize the stable leakproofness between horn 30 and the first side wall 201, therefore the of horn 30
It is tightly connected between one end and the first side wall 201 by sealing connecting component 93.As shown in Fig. 1, Figure 11 to Figure 13, it is tightly connected
Component 93 includes seal tube 931, sealing ring 932 and seal joint 933.Seal tube 931 can be bellows, seal soft
The first end of pipe 931 and the connection end of horn 30 are tightly connected, and the second end and the first side wall 201 of seal tube 931 seal
Connection, the sealing of sealing ring 932 are socketed in the first end of horn 30, extend sealed connection on the end of sealing ring 932
Portion 9321, sealed connection portion 9321 is far from horn 30, the first end sealed connection in sealed connection portion 9321 and seal tube 931
(specifically, the circumferential wall in sealed connection portion 9321 is equipped with fitting projection 93210, and at the same time the first of seal tube 931
The inner sidewall at end is equipped with closure gasket groove 9312, when sealed connection portion 9321 is inserted into the first end of seal tube 931, cooperates convex
Play 93210 and cooperatively form sealing structure with closure gasket groove 9312), the inside of seal joint 933 is equipped with link slot 9331, and close
It seals and is equipped with connection bump 9311 on the outside of the second end of hose 931, connection bump 9311 is only butted in link slot 9331, sealing pressure
Ring 933 is connected on the first side wall 201 the sealing of the second end of seal tube 931 to be pressed against on the first side wall 201, specifically
Ground is circumferentially provided with multiple third screw engaging lugs 9332 on seal joint 933, and each third screw engaging lug 9332 passes through
Screw is fixedly connected on the first side wall 201.In conjunction with shown in referring to figs. 5 and 6, the first side wall 201 is equipped with projected side wall
213, projected side wall 213 is arranged around installation through-hole 212, and projected side wall 213 extends into the second end of seal tube 931, and
The outside wall surface of projected side wall 213 is in contact with the inner wall of seal tube 931, so that seal tube 931 and the first side wall
Leakproofness between 201 is relatively reliable, stable.
Meanwhile the side wall of sealing ring 932 is equipped with the second screw engaging lug 9322, passes through the second screw engaging lug 9322
With fixed connecting base 911, be fixedly connected with pressure ring 912 and be cooperatively connected, to make not only the consolidating by two intervals of horn 30
Determine connection component 91 to be fixedly connected on fuselage loading plate 10, while also by sealing ring 932 and fixed connecting base 911, solid
Surely connection pressure ring 912 is fixedly connected on fuselage loading plate 10.
According to another aspect of the present invention, as shown in Figure 14 and Figure 15, a kind of unmanned plane is provided, is particularly applied to plant
Protect the plant protection drone of operation.The unmanned plane of the present embodiment includes first element, second element, unmanned aerial vehicle rack 01, wherein nothing
Man-machine rack 01 includes fuselage loading plate 10, transfer warehouse 20 and transfer warehouse lid 40, and transfer warehouse 20 is installed on fuselage loading plate
10, transfer warehouse 20 forms the connecting cavity 211 with open end, and transfer warehouse 20 is equipped with through-hole, through-hole and 211 phase of connecting cavity
Connection, transfer warehouse lid 40 are covered on transfer warehouse 20 to be tightly connected chamber, and first element is equipped with connecting line, sets in second element
There is connecting line, first element and second element are installed on fuselage loading plate 10 and are located at outside transfer warehouse 20, the company of first element
The connecting line of wiring and second element passes through through-hole, and the connecting interface of the connecting line of the connecting line and second element of first element is received
It is dissolved in the connecting cavity 211 of transfer warehouse 20.
After the completion unmanned plane is assembled in assembling, assembled using unmanned aerial vehicle rack provided by the present invention as each section
The installation connection framework platform of components, so that the electrical wiring in unmanned plane is laid in unmanned plane assembling assembling process
The connecting interface of connecting line be accommodated in the connecting cavity 211 of transfer warehouse 20 so that the jointing of connecting line is with stealth
The mode of laying is designed, so that unmanned plane not will receive the in disorder influence of connecting interface of connecting line after the assembly is completed, it is whole
Appearance seems more clean and tidy, beautiful, and is protected by connecting interface of the transfer warehouse 20 to connecting line, eliminates connecting line
Connecting interface the problems such as being influenced to occur poor contact, damage by external environmental factor.
In the unmanned plane of the present embodiment, unmanned aerial vehicle rack 01 goes back the multiple horns 30 of what be cool, and horn has opposite
First end and second end, horn 30 have the hollow cavity of perforation first end and second end, and the first end of each horn 30 is fixedly connected
In fuselage loading plate 10, the first end of each horn 30 is corresponded with through-hole corresponding on transfer warehouse 20, and the of each horn 30
Two ends are for installing second element, and hollow cavity and through-hole are used to pass through for the connecting line of second element, and the connection of second element
Line interface is located in connecting cavity.
Specifically, during assembling assembly unmanned plane, in the hollow cavity of horn 30 and the connecting cavity of transfer warehouse 20
The connecting line of first element, second element and the second element laid in 211 includes the first wire segment, the second electricity
The second end of line segment and third wire segment, the first wire segment is equipped with the first connection terminal, and the second wire segment is located at connecting cavity 211
Interior, one end end of the second wire segment is equipped with second connection end, and the first end of third wire segment is electrically connected to first element, the
The second end of two element, second element, third wire segment is equipped with third connection terminal, and the first end of the first wire segment is equipped with
4th connection terminal, wherein the first wire segment is threaded through in the hollow cavity of horn 30, the first connection terminal and second connection end
It is placed in connecting cavity 211 after grafting coupling, second connection end is placed in connecting cavity after coupling with the 4th connection terminal grafting
In 211, in this way, the connection type of the connecting line of unmanned plane uses portable, quick grafting coupled modes, carried out to unmanned plane
When maintenance, staff can will also facilitate, be easy to carry out disassembly, installation.In fact, connection electric wire can be only
It only include the first wire segment and the second wire segment, the first end and first element of the first wire segment, second element, second element electricity
The second end of connection, the first wire segment is equipped with the first connection terminal, and the second wire segment is located in connecting cavity 211, the second wire segment
One end end be equipped with second connection end, the first connection terminal is placed in connecting cavity after coupling with the sub- grafting of second connection end
In 211, wherein the first wire segment is threaded through in hollow cavity.
When flight controller and others need assembly components of the assembly connection on fuselage loading plate 10 to be respectively mounted
After completion, then protected by the assembly components the cover of housing 06 by fuselage loading plate 10 and thereon.
In conjunction with referring to shown in Fig. 8, Figure 14 and Figure 15, power device 02 is mounted on the separate fuselage loading plate 10 of horn 30
On end, in assembling assembling process, firstly, be fixedly attached upper power installation sheath body 70 on the end of horn 30, using dynamic
Power installation sheath body 70 is sealed the opening of the end of horn 30, and opens up power device 02 on power installation sheath body 70
The interspersed interspersed mouth of connection electric wire.Then, then by power device 02 using bolt, nut cooperation lock to power and install
On sheath body 70.
Laying compared to electrical wiring is installed, and in the present embodiment, unmanned plane further includes flusher 03, pumping installations
04 and liquid storage container 05, flusher 03 be fixedly mounted on horn 30, pumping installations 04 is fixedly connected on unmanned aerial vehicle rack
On the bottom surface of fuselage loading plate 10, liquid storage container 05 is removably attached in unmanned aerial vehicle rack, pumping installations 04 and winged control mould
Block electrical connection, flusher 03 are connect with pumping installations 04 by the first delivery pipe, and the first delivery pipe is laid in hollow cavity and company
Connect intracavitary, pumping installations 04 is connect with liquid storage container 05 by the second delivery pipe, specifically, in connecting cavity 211 or second
On any position of loading plate 12, assembly connection has flowmeter, which is electrically connected with control module is flown, and the flowmeter is set
It sets in the second delivery pipe between connection pumping installations 04 and liquid storage container 05, is pumped up device so as to know in real time
04 is delivered to flusher 03 and the liquid capacity that is sprayed.
Specifically, the first delivery pipe includes the first pipeline section, the second pipeline section and jointing, wherein the of unmanned aerial vehicle rack
Three side walls 203 are equipped with and plug through-hole 2031, and jointing, which is sealingly disposed in, to be plugged in through-hole 2031, the both ends point of the first pipeline section
Be not connected to the first end of pumping installations and jointing, the both ends of the second pipeline section be connected to the second end of jointing with
Flusher.
In the unmanned plane of the present embodiment, and induction antenna 08 (it can be communication induction antenna, it can also be with course line induction antenna
Deng) be fixedly mounted on horn 30, wherein horn 30 is equipped with threading hole 31, and induction antenna 08 is electrically connected with connection line plate
Connecting line sealingly extend through threading hole 31.
The foregoing is merely illustrative of the preferred embodiments of the present invention, is not intended to limit the invention, all in essence of the invention
Made any modifications, equivalent replacements, and improvements etc., should all be included in the protection scope of the present invention within mind and principle.
Claims (20)
1. a kind of unmanned aerial vehicle rack characterized by comprising
Fuselage loading plate (10), the fuselage loading plate (10) is for installing first element and second element；
Transfer warehouse (20), the transfer warehouse (20) are installed on the fuselage loading plate (10), transfer warehouse (20) shape
At the connecting cavity (211) with open end, the transfer warehouse (20) is equipped with through-hole, the through-hole and the connecting cavity
(211) it is connected, wherein the first element and second element are located at the transfer warehouse (20) outside, and the through-hole is for supplying
The connecting line of the first element and the connecting line of the second element pass through, and the connecting cavity (211) is for accommodating described the
The connecting interface of the connecting line of one element and the connecting line of the second element；
Transfer warehouse lid (40), transfer warehouse lid (40) sealing cover are set at the open end of the transfer warehouse (20).
2. unmanned aerial vehicle rack as described in claim 1, which is characterized in that be extended on the fuselage loading plate (10) organic
Arm (30), the horn (30) have an opposite first end and second end, the horn (30) have penetrate through the first end and
The hollow cavity of second end, the transfer warehouse (20) include the first side wall of the connecting cavity around the transfer warehouse (20)
(201), the through-hole of the transfer warehouse (20) includes the installation through-hole (212) on the first side wall (201), the machine
The first end of arm (30) is sealedly attached to the first side wall (201) of the transfer warehouse (20), installation through-hole (212) connection
The hollow cavity of the horn (30) and the connecting cavity (211) of the transfer warehouse (20), the second end of the horn (30) are used for
The second element is installed, the hollow cavity and the installation through-hole (212) are used to pass through for the connecting line of the second element.
3. unmanned aerial vehicle rack as claimed in claim 2, which is characterized in that the horn (30) has four or six or eight, corresponds to
Ground, the first side wall have four or six or eight.
4. unmanned aerial vehicle rack as claimed in claim 3, which is characterized in that the first element includes being located at the transfer warehouse
(20) electricity outside is adjusted, and the transfer warehouse (20) further includes bottom wall (22), and the first side wall (201) is hung down from the bottom wall (22)
Directly extend, the through-hole of the transfer warehouse (20) further includes the first punched out (221) on the bottom wall (22), institute
The first punched out (221) are stated for being pierced by for the connecting line adjusted of the electricity, the second element is including being installed on the horn
(30) motor of second end, the connecting line of the motor pass through the hollow of the installation through-hole (212) and the horn (30)
The connecting interface of chamber, the connecting line of connecting line and the motor that the electricity is adjusted is located at the connecting cavity of the transfer warehouse (20)
It is interior.
5. unmanned aerial vehicle rack as claimed in claim 4, which is characterized in that the transfer warehouse (20) further includes second sidewall
(202), the second sidewall (202) is connected to the first side wall (201), four or six or eight the first side walls (201)
The two sides of the second sidewall (202) are evenly distributed within, the through-hole of the transfer warehouse (20) further includes being set to described second
Intercommunicating pore on side wall (202), the intercommunicating pore are used to be pierced by for the connecting line of flight controller, the company of the flight controller
The connecting interface between connecting line that wiring and the electricity are adjusted is located in the connecting cavity of the transfer warehouse (20).
6. unmanned aerial vehicle rack as claimed in claim 5, which is characterized in that the first element includes being located at the transfer warehouse
(20) liquid storage container outside, the transfer warehouse (20) further include third side wall (203), and the third side wall (203) is connected to
The first side wall (201), the third side wall (203) are oppositely arranged with the second sidewall (202), four or six or eight institutes
The two sides that the first side wall (201) is fifty-fifty located at the third side wall (203) are stated, the through-hole of the transfer warehouse (20) further includes
Through-hole is plugged on the third side wall, and the through-hole that plugs is described for being pierced by for the connecting line of the liquid storage container
Second element further includes the spray head for being installed on the second end of the horn (30), and the connecting line of the spray head passes through the horn
(30) connection of the connecting line of hollow cavity and the installation through-hole (212), the connecting line of the liquid storage container and the spray head
Interface is located in the connecting cavity of the transfer warehouse (20).
7. unmanned aerial vehicle rack as claimed in claim 3, which is characterized in that the first end and the middle roll-over of the horn (30)
It is tightly connected between the first side wall (201) of body (20) by sealing connecting component (93), sealing connecting component (93) packet
It includes seal tube (931), the first end of the seal tube (931) is fixedly connected with the first end of the horn (30), described
The second end of seal tube (931) is fixedly connected with the transfer warehouse (20).
8. unmanned aerial vehicle rack as claimed in claim 7, which is characterized in that the sealing connecting component (93) further includes sealing shroud
Ring (932), sealing ring (932) sealing are socketed on the connection end of the horn (30), the sealing ring (932)
The end far from the horn (30) on extend sealed connection portion (9321), the sealed connection portion (9321) is protruded into described
In the first end of seal tube (931), the circumferential wall of the sealed connection portion (9321) is equipped with fitting projection (93210), institute
The inner sidewall for stating the first end of seal tube (931) is equipped with the closure gasket groove for being sticked in the fitting projection (93210)
(9312)。
9. unmanned aerial vehicle rack as claimed in claim 7, which is characterized in that the sealing connecting component further include be sheathed on it is described
The second end outside of the seal joint (933) of seal tube (931), the seal tube (931) is equipped with connection bump
(9311), the seal joint (933) is fixedly connected on the first side wall (201) with by the seal tube (931)
Connection bump (9311) sealing of second end is pressed against on the first side wall (201).
10. unmanned aerial vehicle rack as claimed in claim 9, which is characterized in that the inside of the seal joint (933) is equipped with connection
Slot (9331), the connection bump (9311) are only butted in the link slot (9331).
11. unmanned aerial vehicle rack as claimed in claim 9, which is characterized in that the first side wall (201) is equipped with projected side wall
(213), the projected side wall (213) surrounds the installation through-hole (212), and the projected side wall (213) extends into the sealing
In the second end of hose (931), and the inner wall phase of the outside wall surface of the projected side wall (213) and the seal tube (931)
Contact.
12. unmanned aerial vehicle rack as claimed in claim 6, which is characterized in that the unmanned aerial vehicle rack further includes installing frame, described
The end of installing frame is fixedly connected on the third side wall (203) of the transfer warehouse (20), and the installing frame is described for installing
Liquid storage container.
13. unmanned aerial vehicle rack as claimed in claim 12, which is characterized in that the unmanned rack further includes foot prop (80), institute
Stating foot prop (80) includes front leg strut (110) for being connected to the front end of fuselage loading plate (10) and for being connected to the installation
The rear support leg (130) of the rear end of frame, wherein the front leg strut (110) includes front support (1130) and the first rebate
(1120), the front support (1130) connect with first rebate (1120), and forms first in the junction of the two
It turns round and transfers, one end far from first rebate (1120) of the front support (1130) is used to support in supporting surface,
One end far from the front support (1130) of first rebate (1120) is used to connect the fuselage loading plate (10),
And described first turn round turnover opening towards the rear support leg (130).
14. unmanned aerial vehicle rack as claimed in claim 13, which is characterized in that the rear support leg (130) includes rear support portion
(1330) it is connect with the second rebate (1320), the rear support portion (1330) with second rebate (1320), and two
The junction of person forms the second turn turnover, one end far from second rebate (1320) of the rear support portion (1330)
It is used to support in the supporting surface, one end far from the rear support portion (1330) of second rebate (1320) is for connecting
Connect the installing frame, and described second turn round turnover opening towards the front leg strut (110).
15. unmanned aerial vehicle rack as claimed in claim 14, which is characterized in that first rebate (1120) and the preceding branch
Support part (1130) is arranged by the direction of the fuselage loading plate (10) to the supporting surface in successively diminution, second rebate
(1320) it is arranged by the installing frame to the direction of the supporting surface in successively diminution with the rear support portion (1330).
16. unmanned aerial vehicle rack as claimed in claim 15, which is characterized in that the front leg strut (110) further includes reinforcement part
(1150), the reinforcement part (115) is arranged on first rebate (1120), and the reinforcement part (1150) is along described
First turn turnover extends on the front support (1130).
17. the unmanned aerial vehicle rack as described in any one of claims 1 to 16, which is characterized in that the transfer warehouse lid (40) can
Releasably it is connected to the transfer warehouse (20).
18. the unmanned aerial vehicle rack as described in any one of claims 1 to 16, which is characterized in that the fuselage loading plate (10)
Including the first loading plate (11) and the second loading plate (12), first loading plate (11) and second loading plate (12) are opposite
Setting, and the transfer warehouse (20) is between first loading plate (11) and second loading plate (12), described the
One loading plate (11) is equipped with the first matching hole (111), the open end of the connecting cavity (211) and first matching hole
(111) it is oppositely arranged.
19. the unmanned aerial vehicle rack as described in any one of claims 1 to 16, which is characterized in that the transfer warehouse lid (40)
At least part is made of transparent material.
20. a kind of unmanned plane characterized by comprising first element, second element and rack, the rack are claim 1
To unmanned aerial vehicle rack described in any one of 19, the first element and the second element are installed on the unmanned aerial vehicle rack
On fuselage loading plate (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710648955.1A CN109319086B (en) | 2017-08-01 | 2017-08-01 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710648955.1A CN109319086B (en) | 2017-08-01 | 2017-08-01 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109319086A true CN109319086A (en) | 2019-02-12 |
| CN109319086B CN109319086B (en) | 2024-05-28 |
Family
ID=65245880
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710648955.1A Active CN109319086B (en) | 2017-08-01 | 2017-08-01 | Unmanned aerial vehicle frame and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109319086B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110683053A (en) * | 2019-09-09 | 2020-01-14 | 苏州臻迪智能科技有限公司 | Intelligent equipment, floating and unmanned aerial vehicle |
| CN112977792A (en) * | 2021-03-26 | 2021-06-18 | 安阳全丰航空植保科技股份有限公司 | Novel unmanned aerial vehicle frame and assembling method thereof |
| CN114537653A (en) * | 2022-04-24 | 2022-05-27 | 北京玮航科技有限公司 | Fixing mechanism and unmanned aerial vehicle of duct installation roof beam |
| CN116995475A (en) * | 2023-09-26 | 2023-11-03 | 中飞艾维航空科技(苏州)有限公司 | Unmanned aerial vehicle's termination |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204998774U (en) * | 2015-07-15 | 2016-01-27 | 广州天翔航空科技有限公司 | Many rotors plant protection unmanned aerial vehicle of shallow design |
| CN105966595A (en) * | 2016-05-13 | 2016-09-28 | 深圳市斯威普科技有限公司 | Waterproof structure of unmanned aerial vehicle |
| CN205872434U (en) * | 2016-08-15 | 2017-01-11 | 江苏天频植保科技有限公司 | Unmanned aerial vehicle fuselage protector |
| US20170183074A1 (en) * | 2015-12-29 | 2017-06-29 | Qualcomm Incorporated | Unmanned aerial vehicle structures and methods |
| CN207060378U (en) * | 2017-08-01 | 2018-03-02 | 广州极飞科技有限公司 | Unmanned plane frame and unmanned plane |
-
2017
- 2017-08-01 CN CN201710648955.1A patent/CN109319086B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN204998774U (en) * | 2015-07-15 | 2016-01-27 | 广州天翔航空科技有限公司 | Many rotors plant protection unmanned aerial vehicle of shallow design |
| WO2017008707A1 (en) * | 2015-07-15 | 2017-01-19 | 广州天翔航空科技有限公司 | Multi-rotor plant protection unmanned aerial vehicle of trolley design |
| US20170183074A1 (en) * | 2015-12-29 | 2017-06-29 | Qualcomm Incorporated | Unmanned aerial vehicle structures and methods |
| CN105966595A (en) * | 2016-05-13 | 2016-09-28 | 深圳市斯威普科技有限公司 | Waterproof structure of unmanned aerial vehicle |
| CN205872434U (en) * | 2016-08-15 | 2017-01-11 | 江苏天频植保科技有限公司 | Unmanned aerial vehicle fuselage protector |
| CN207060378U (en) * | 2017-08-01 | 2018-03-02 | 广州极飞科技有限公司 | Unmanned plane frame and unmanned plane |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110683053A (en) * | 2019-09-09 | 2020-01-14 | 苏州臻迪智能科技有限公司 | Intelligent equipment, floating and unmanned aerial vehicle |
| CN112977792A (en) * | 2021-03-26 | 2021-06-18 | 安阳全丰航空植保科技股份有限公司 | Novel unmanned aerial vehicle frame and assembling method thereof |
| CN112977792B (en) * | 2021-03-26 | 2022-08-26 | 安阳全丰航空植保科技股份有限公司 | Novel unmanned aerial vehicle frame and assembling method thereof |
| CN114537653A (en) * | 2022-04-24 | 2022-05-27 | 北京玮航科技有限公司 | Fixing mechanism and unmanned aerial vehicle of duct installation roof beam |
| CN116995475A (en) * | 2023-09-26 | 2023-11-03 | 中飞艾维航空科技(苏州)有限公司 | Unmanned aerial vehicle's termination |
| CN116995475B (en) * | 2023-09-26 | 2023-12-08 | 中飞艾维航空科技(苏州)有限公司 | Unmanned aerial vehicle's termination |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109319086B (en) | 2024-05-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109319086A (en) | Unmanned aerial vehicle rack and unmanned plane | |
| CN207060378U (en) | Unmanned plane frame and unmanned plane | |
| CN207225666U (en) | A kind of more rotor plant protection unmanned planes | |
| CN203661863U (en) | Soft liquid pesticide box | |
| CN105818985A (en) | Unmanned aerial vehicle for plant protection | |
| CN105691605B (en) | A kind of dismountable unmanned plane of horn | |
| CN206871370U (en) | Flusher and unmanned plane | |
| CN207475168U (en) | Cable sealing module and cable crossing firewall | |
| CN207559039U (en) | Connection component, antenna module, unmanned plane | |
| CN209396050U (en) | A kind of plant protection drone medicine-chest and unmanned plane | |
| CN205633062U (en) | Unmanned aerial vehicle pesticide sprinkling system | |
| CN205738110U (en) | Unmanned plane medicine-chest | |
| CN209169371U (en) | The antenna modules and unmanned plane of unmanned plane | |
| CN214593802U (en) | Plant protection flies to prevent spouting and spills equipment | |
| CN209455004U (en) | A kind of medicine-chest fixed frame and the unmanned plane using it | |
| CN207822335U (en) | A kind of fire main special purpose interface | |
| CN219373590U (en) | A charge device for plant protection unmanned aerial vehicle | |
| AU2017426557B2 (en) | Unmanned aerial vehicle frame and unmanned aerial vehicle | |
| CN213443102U (en) | Unmanned aerial vehicle sprinkling system reaches unmanned aerial vehicle who contains it | |
| CN206116595U (en) | Fixing device , antenna module and unmanned aerial vehicle | |
| CN209396049U (en) | A kind of plant protection drone | |
| CN208272400U (en) | Cable sealing device and power distribution cabinet for power distribution cabinet | |
| CN213473525U (en) | Pesticide sprays protection device for unmanned aerial vehicle | |
| CN207060375U (en) | A kind of unmanned plane | |
| CN212313882U (en) | A unmanned aerial vehicle for pesticide sprays |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information | ||
| CB02 | Change of applicant information |
Address after: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Applicant after: XAG Co., Ltd. Address before: 510000 Guangdong Guangzhou Gaotang Tianhe District Software Park 1 3A01 Applicant before: Guangzhou Xaircraft Technology Co.,Ltd. |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |