CN206218204U - Aircraft - Google Patents
Aircraft Download PDFInfo
- Publication number
- CN206218204U CN206218204U CN201621247756.7U CN201621247756U CN206218204U CN 206218204 U CN206218204 U CN 206218204U CN 201621247756 U CN201621247756 U CN 201621247756U CN 206218204 U CN206218204 U CN 206218204U
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- CN
- China
- Prior art keywords
- antenna
- horn
- aircraft
- aircraft according
- component
- 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.)
- Expired - Fee Related
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- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 22
- 230000004308 accommodation Effects 0.000 claims description 14
- 238000007789 sealing Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 description 10
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 5
- 239000000741 silica gel Substances 0.000 description 5
- 229910002027 silica gel Inorganic materials 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000001681 protective effect Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 229910052751 metal Inorganic materials 0.000 description 3
- 238000004806 packaging method and process Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000001771 impaired effect Effects 0.000 description 2
- 238000012856 packing Methods 0.000 description 2
- 241000196324 Embryophyta Species 0.000 description 1
- 235000002595 Solanum tuberosum Nutrition 0.000 description 1
- 244000061456 Solanum tuberosum Species 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
-
- 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
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U60/00—Undercarriages
- B64U60/50—Undercarriages with landing legs
Abstract
A kind of aircraft, including centre frame, antenna, and the horn component being connected with the centre frame.The horn component includes horn, and the antenna is arranged on the horn and away from the position of the centre frame.Also include the connector being arranged on the horn, the connector is used to for the antenna to be fixed on the horn.Be arranged on antenna on horn by the aircraft, and avoiding miscellaneous part away from the setting of aircraft centre frame influences the antenna performance.And the dismounting of foot stool can be facilitated.
Description
Technical field
The utility model is related to unmanned plane field, especially a kind of aircraft.
Background technology
In the prior art, aircraft can be used to taking photo by plane, survey and draw, plant protection, detecting, the industry such as the disaster relief, generally have in its structure
Centre frame, dynamical system, undercarriage etc. are constituted, and by carrying, winged control, figure are passed and other micro computer equipment carry out operation.
Wherein, data accessed in aircraft operation process, can amplify signal for example distant with ground installation by antenna
Control device, computer etc. are communicated.And antenna location layout point on board the aircraft is different, the optimum signal point of antenna can be influenceed,
And then influence the overall performance of aircraft to play.Therefore, whether rationally layout of the antenna in flight, directly affect flight
The performance of device.
Multi-rotor aerocraft is larger due to volume, and typically antenna is arranged on the centre frame of aircraft or undercarriage
Face.By Antenna Design on centre frame, equipment on centre frame is more to influence the performance of antenna.By Antenna Design in undercarriage
On, antenna has line with the key Design on centre frame, and undercarriage can be caused to be designed to Quick Release mode or Quick Release mode
Be designed to it is too complicated, in-convenience in use.
Utility model content
The utility model provides a kind of aircraft.
According to the first aspect of the utility model embodiment, there is provided a kind of aircraft, including centre frame, antenna, and with institute
State the horn component of centre frame connection；
The horn component includes horn, and the antenna is arranged on the horn and away from the position of the centre frame.
Described aircraft, also including the connector being arranged on the horn, the connector is used for the antenna
It is fixed on the horn.
Further, the connector includes the lock sleeve being adapted to the horn, and the day being connected with the lock sleeve
Line seat, the antenna pedestal is used to carry the antenna.
Further, the antenna pedestal includes body, and the body includes the accommodating sky for accommodating the antenna
Between.
Further, the body also includes the cable-through hole above the accommodation space.
Further, the lock sleeve includes the connection end being connected with the antenna pedestal, and for the lock sleeve to be consolidated
It is scheduled on the locking end on the horn.
Further, consent is provided with the connection end, the correspondence consent is provided with routing hole, the day on the horn
The connecting line of line enters in the horn through the consent and the routing hole.
Further, the elastic component for sealing the consent and the routing hole can be placed in the consent.
Further, when the horn is opened, the antenna is located at the lower section of the horn；Or
When the horn is opened, the polarised direction and horizontal plane of the antenna；Or
The polarised direction of the antenna is vertical with the bearing of trend of the horn.
Further, the antenna is dipole antenna.
Further, the aircraft also includes landing gear assembly, the horn component and the foldable company of the centre frame
Connect；When the horn component is in collapsed state, the antenna is located at the antenna described towards the aircraft center
Landing gear assembly and horn component inner side.
According to the second aspect of the utility model embodiment, there is provided a kind of aircraft, including centre frame, antenna and with it is described
The horn component of centre frame connection；The horn component and the foldable connection of the centre frame；
The horn component includes horn, and the antenna is arranged on the horn, and is received when the horn component is in
The antenna makes the antenna be located at the landing gear assembly and the horn component towards the aircraft center during state of rising
Inner side.
Described aircraft, also including the connector being arranged on the horn, the connector is used for the antenna
It is fixed on the horn.
Further, the connector includes the lock sleeve being adapted to the horn, and the day being connected with the lock sleeve
Line seat, the antenna pedestal is used to carry the antenna.
Further, the antenna pedestal includes body, and the body includes the accommodating sky for accommodating the antenna
Between.
Further, the body also includes the cable-through hole above the accommodation space.
Further, the lock sleeve includes the connection end being connected with the antenna pedestal, and for the lock sleeve to be consolidated
It is scheduled on the locking end on the horn.
Further, consent is provided with the connection end, the correspondence consent is provided with routing hole, the day on the horn
The connecting line of line enters in the horn through the consent and the routing hole.
Further, the elastic component for sealing the consent and the routing hole can be placed in the consent.
Further, the antenna is located at the lower section of the horn；Or
When the horn is opened, the polarised direction and horizontal plane of the antenna；Or
The polarised direction of the antenna is vertical with the bearing of trend of the horn.
Further, the antenna is dipole antenna.
The technical scheme that embodiment of the present utility model is provided can include the following benefits：The aircraft is by antenna
It is arranged on horn, is set away from aircraft centre frame and avoid the miscellaneous part influence antenna performance, and ensure foot stool side
Just dismantle.
Brief description of the drawings
Fig. 1 is a kind of schematic diagram of aircraft that the utility model implementation is exemplified.
Fig. 2 is a kind of connection diagram of the horn with connector of aircraft that the utility model implementation is exemplified.
Fig. 3 is a kind of explosive view of the horn with connector of aircraft that the utility model implementation is exemplified.
Fig. 4 is a kind of horn component collapsed state schematic diagram of aircraft that the utility model implementation is exemplified.
Specific embodiment
Here exemplary embodiment will be illustrated in detail, its example is illustrated in the accompanying drawings.Following description is related to
During accompanying drawing, unless otherwise indicated, the same numbers in different accompanying drawings represent same or analogous key element.Following exemplary embodiment
Described in implementation method do not represent all implementation methods consistent with the utility model.Conversely, they be only with such as
The example of the consistent apparatus and method of some aspects being described in detail in appended claims, of the present utility model.
In the case where not conflicting, the feature in following embodiments and embodiment can be mutually combined.
Implementation method one：
Refer to Fig. 1 to Fig. 4, a kind of aircraft 100 shown in the present embodiment, including centre frame 1, antenna 3 and with it is described
The horn component 2 of the connection of centre frame 1, wherein being provided with electrical equipment and metallic element etc. in the centre frame 1.Different
In embodiment, the horn component 2 and the foldable connection of the centre frame 1 or not foldable connection.
The horn component 2 includes horn 21, and the antenna 3 is arranged on the horn 21 and away from the centre frame 1
Position.The antenna 3 is set on the horn 21, makes the antenna 3 away from the electrical equipment and gold in the centre frame 1
Category parts etc., it is to avoid the signal of the potato masher antenna such as electric equipment and metallic element 3.In one embodiment, the antenna 3
Be arranged far from the centre frame 1, positioned at the centre of the horn 21 or the position for tending in the middle of the horn 21.
Be arranged on the antenna 3 of aircraft 100 on the horn 21 of the horn component 2 by the utility model, away from described
The position of centre frame 1, under the disturbed condition without electrical equipment and metallic element, the antenna 3 can obtain more best performance.
Further, as shown in Fig. 2 the aircraft 100 also includes the connector 4 being arranged on the horn 21, institute
Connector 4 is stated for the antenna 3 to be fixed on into the horn 21.Be can be understood as with reference to above-mentioned implementation method：The day
Line 3 can be directly anchored on the horn 21, for example, antenna 3 is glued on the horn 21；Can also connect by described in one
Be fixed on the antenna 3 on the horn 21 by fitting 4.
Refer to Fig. 2 and Fig. 3, the connector 4 includes the lock sleeve 41 being adapted to the horn 21, and with the locking
The antenna pedestal 42 of the connection of set 41.The antenna pedestal 42 is used to carry the antenna 3.In one embodiment, the lock sleeve 41 with
The horn 21 is to be detachably connected or non-dismountable connection.Such as described lock sleeve 41 with the horn 21 for clamping is connected,
The lock sleeve 41 can be also fixedly connected with the horn 21 by bolt or screw.
Fig. 3 is referred to, the antenna pedestal 42 includes body 421, and the body 421 is included for accommodating the antenna
3 accommodation space 423.The accommodation space 423 is set in the antenna pedestal 42 to be used to carry the antenna 3.It is real one
Apply in example, the antenna 3 can be also directly placed in the accommodation space 423, and a baffle plate is set on the body 412
424, for the antenna 3 to be fixed in the accommodation space 423.The baffle plate 424 may be disposed at the accommodation space 423
Top.In other embodiments, the antenna 3 can be also embedded in the accommodation space 423.
Further, the body 421 also includes the cable-through hole 422 positioned at the top of the accommodation space 423, and this crosses line
Hole 422 is available for the connecting line 31 of the antenna 3 to pass through.
Fig. 3 is referred to, the lock sleeve 41 includes the connection end 412 being connected with the antenna pedestal 42, and for by described in
Lock sleeve 41 is fixed on the locking end 411 on the horn 21.In one embodiment, the locking end 411 can be incited somebody to action by screw 6
The lock sleeve 41 is fixed on the horn 21.Screw hole for example is offered in institute's locking end 411, screw 6 is passed through into institute
State screw hole and lock the locking end 411.
Consent 413 is provided with the connection end 412, the correspondence consent 413 is provided with routing hole and (does not show on the horn 21
Go out).In one embodiment, the connecting line 31 of the antenna 3 enters the horn 21 through the consent 413 and the routing hole
It is interior.The connecting line 31 of the antenna 3 is placed in the horn 21, the connecting line 31 can be protected without damage, it is to avoid wiring
The outward appearance of in disorder influence aircraft is beautiful.Really, in other embodiments, the connecting line 31 also can directly be bundled in the horn
On 21, or the connecting line 31 is fixed on the horn 21 using fixture.
Please continue to refer to Fig. 3, the bullet for sealing the consent 413 and the routing hole can be placed in the consent 413
Property part 43.The elastic component 43 can select silica gel plug, and the connecting line 31 of the antenna 3 may pass through the silica gel plug.I.e. described connection
Line 31 enters in the horn 21 through the silica gel plug, and the silica gel plug is placed in the consent 413 and the routing hole.
The silica gel plug has further protected the connecting line 31.
Further, in one embodiment, when the horn 21 is opened, the antenna 3 is located at the lower section of the horn 21.
The antenna 3 selects two or more than two using number, and is separately positioned on different horns 21.In another embodiment
The polarised direction and horizontal plane of the antenna 3 are set, positioned at the lower section of the horn 21.
The antenna 3 is arranged on the lower section of horn 21, it is ensured that when the horn component 2 is folded to be packed up, antenna 3 is towards whole
The center of individual aircraft 100, the horn component 2 in outside antenna 3 can be played a protective role and make antenna 3 from collision etc., from
And be easy to pack, carry, move.The performance reached when the polarised direction of the antenna 3 is with horizontal plane is optimal.This implementation
In mode, the bearing of trend of the antenna 3 overlaps with the polarised direction of the antenna 3, therefore in present embodiment, is arranged at described
The bearing of trend of the antenna 3 on horn 21 is perpendicular to the ground.
It is appreciated that when the horn component 2 is opened, the antenna 3 may be alternatively located at the top of the horn 21, work as institute
State horn component 3 to fold when packing up, the antenna 3 is folded or be rotated such that it towards the center of the aircraft 100 i.e.
Can, it is to avoid stay in the outside of horn 21 impaired.
Further, in other embodiments, the polarised direction of the antenna 3 is hung down with the bearing of trend of the horn 21
Directly., so as to be arranged at horn 21 on and with the horn 21 vertical day almost parallel with horizontal plane when horn 21 launches
The angle of line 3 and horizontal plane is also close to 90 degree.And it is vertical with the bearing of trend of the horn 21 in the polarised direction of antenna 3
Set, easily calibrated when the antenna 3 is installed, also beautified the outward appearance of aircraft 100.Really, the horn component 2 and institute
When stating centre frame 1 for not foldable connection, the polarised direction of the antenna 3, also close to 90 degree, also has with the angle of horizontal plane
There is the effect above.In present embodiment, the bearing of trend of the antenna 3 overlaps with the polarised direction of the antenna 3, therefore this implementation
In mode, the bearing of trend of the antenna 3 is vertical with horn 21.
Fig. 4 is referred to, the aircraft 100 also includes landing gear assembly 5, the horn component 2 and centre frame of aircraft 100
1 foldable connection.After the horn 21 is folded down, the volume of whole aircraft 100 reduces.The antenna 3 is then located at institute
Landing gear assembly 5 and the inner side of the horn component 2 are stated, the landing gear assembly 5 and the horn component 2 can be played to antenna 3
Protective effect, can prevent the antenna 3 to be damaged.I.e. described horn component 2 and the foldable connection of the centre frame 1, work as institute
Stating the antenna 3 when horn component 2 is in collapsed state, towards the center of the aircraft 100, is located at the antenna 3 described
Landing gear assembly 5 and the inner side of the horn component 2 are protecting antenna 3 to be not damaged by.
In one embodiment, the antenna is dipole antenna, can also be such as IFA (Inverted F-shaped
Antenna, inverse-F antenna), PIFA (Planar Inverted F-shaped Antenna, planar inverted-F antenna), loop aerial,
Slot antenna etc..The loop aerial is that a plain conductor is coiled into definite shape, such as circular, square, triangle, to lead
Body two ends as output end structure.
In one embodiment, the aircraft 100 be multi-rotor aerocraft 100, including quadrotor, six rotors fly
One kind in row device or eight-rotary wing aircraft.
Implementation method two：
Refer to Fig. 1 to Fig. 4.A kind of aircraft 100 is provided below by another implementation method to the utility model to do
Further illustrate.The aircraft 100 includes centre frame 1, antenna 3 and the horn component 2 being connected with the centre frame 1.Institute
Horn component 2 is stated with the foldable connection of the centre frame 1.The horn component 2 includes horn 21, and the antenna 3 is arranged at institute
State on horn 21, and the antenna, towards the aircraft center, makes the day when the horn component 2 is in collapsed state
Line 3 is located at the landing gear assembly 5 and the inner side of the horn component 2.
I.e. the horn component 2 of aircraft 100 can open or pack up relative to the centre frame 1, antenna 3 is arranged on described
On horn 21, the antenna 3 can be packed up with the horn 21, and the antenna 3 when the horn component 2 is in collapsed state
Positioned at the landing gear assembly 5 and the inner side of the horn component 2.Because there is the He of the landing gear assembly 5 in the outside of the antenna 3
The horn component 2, when transporting or packing aircraft 100, the landing gear assembly 5 and the horn component 2 can be to antennas 3
Play a protective role and make antenna 3 from collision etc., reduce infringement of the external force to antenna 3.Due to antenna 3 is arranged on into horn 21
On, then landing gear assembly can be designed to quick-disassembly structure, the packaging volume of aircraft is further reduced, it is more beneficial for movement and removes
Fortune.
In one embodiment, when the horn 21 is opened, the antenna 3 is located at the lower section of the horn 21, when the machine
The antenna 3 tends to the aircraft center towards the aircraft center or direction when arm component 2 is in collapsed state.Outside
Horn component 2 antenna 3 can be played a protective role and make antenna 3 from collision etc., consequently facilitating packaging, carry, it is mobile.
In another embodiment, when the horn 21 is opened, the polarised direction and horizontal plane of the antenna 3 are set,
Now the performance for reaching of antenna 3 is optimal.It is appreciated that when the horn component 2 is opened, the antenna 3 may be alternatively located at institute
The top of horn 21 is stated, when the horn component 3 is folded to be packed up, the antenna 3 it is folded or be rotated such that towards institute
State the center of aircraft 100, it is to avoid stay in the outside of horn 21 impaired.
In other embodiments, for example the polarised direction of described antenna 3 is vertical with the bearing of trend of the horn 21.Work as institute
When stating the polarised direction of antenna 3 with horizontal plane, the performance that the antenna 3 reaches is optimal.Therefore the antenna 3 in present embodiment
Set-up mode protect antenna 3 while make the performance of the antenna 3 optimal.Substantially put down with horizontal plane when horn 21 launches
OK, so as to be arranged on horn 21 and the antenna 3 vertical with the horn 21 and horizontal plane angle also close to 90 degree.
And it is vertically arranged with the bearing of trend of the horn 21 in the polarised direction of antenna 3, the easy school when the antenna 3 is installed
Standard, has also beautified the outward appearance of aircraft 100.
Aircraft 100 in the present embodiment also includes following technical characteristic, and techniques described below feature is implemented with upper one
Technical characteristic in example is same or similar, and acquired technique effect is also same or similar, belongs to same inventive concept.Below only
Describe relation between the technical characteristic and technical characteristic of the aircraft 100, repeat no more its specific effect or technical characteristic it
Between effect, specifically refer to description of the above to the embodiment of the aircraft 100.
The aircraft 100 also includes：
The connector 4 on the horn 21 is arranged on, the connector 4 is used to for the antenna 3 to be fixed on the horn
On 21.
The connector 4 includes the lock sleeve 41 being adapted to the horn 21, and the antenna being connected with the lock sleeve 41
Seat 42, the antenna pedestal 42 is used to carry the antenna 3.
The antenna pedestal 42 includes body 421, and the body 421 includes the accommodating sky for accommodating the antenna 3
Between 423.
The body 421 also includes the cable-through hole 422 positioned at the top of the accommodation space 423.
The lock sleeve 41 includes the connection end 412 being connected with the antenna pedestal 42, and for the lock sleeve 41 to be consolidated
It is scheduled on the locking end 411 on the horn 21.
Consent 413 is provided with the connection end 412, the correspondence consent 413 is provided with routing hole on the horn 21, described
The connecting line 31 of antenna 3 enters in the horn 21 through the consent 413 and the routing hole.
The elastic component 43 for sealing the consent 413 and the routing hole can be placed in the consent 413.
The antenna is dipole antenna.
The aircraft 100 is multi-rotor aerocraft 100, including quadrotor, six rotorcraft or eight rotors
One kind in aircraft.
From embodiment of above, be arranged on antenna 3 on horn 21 by the aircraft 100, solves interference problem,
The more impact of performance on frame more centrally disposed than antenna 31 can be obtained.Antenna is arranged on horn lower section, foldable machine is being applied to
When on the aircraft of arm component, antenna can be avoided from damaging.Some aircraft with operation of landing gear component 5, are set using antenna 3
Count the scheme on horn 21, it is possible to operation of landing gear component is designed to quick-disassembly structure, aircraft can be further reduced
Packaging volume, is more beneficial for moving carrying.
Preferred embodiment of the present utility model is the foregoing is only, is not used to limit the utility model, it is all at this
Within the spirit and principle of utility model, any modification, equivalent substitution and improvements done etc. should be included in the utility model
Within the scope of protection.
This patent document disclosure includes material protected by copyright.The copyright is all for copyright holder.Copyright
Owner does not oppose that anyone replicates the patent document in the presence of the proce's-verbal of Patent＆Trademark Office and archives or is somebody's turn to do
Patent is disclosed.
Claims (21)
1. a kind of aircraft, it is characterised in that including centre frame, antenna, and the horn component being connected with the centre frame；
The horn component includes horn, and the antenna is arranged on the horn and away from the position of the centre frame.
2. aircraft according to claim 1, it is characterised in that also including the connector being arranged on the horn, institute
Connector is stated for the antenna to be fixed on into the horn.
3. aircraft according to claim 2, it is characterised in that the connector includes the locking being adapted to the horn
Set, and the antenna pedestal being connected with the lock sleeve, the antenna pedestal are used to carry the antenna.
4. aircraft according to claim 3, it is characterised in that the antenna pedestal includes body, the body bag
Include the accommodation space for accommodating the antenna.
5. aircraft according to claim 4, it is characterised in that the body also includes being located on the accommodation space
The cable-through hole of side.
6. aircraft according to claim 3, it is characterised in that the lock sleeve includes the company being connected with the antenna pedestal
Connect end, and the locking end for the lock sleeve being fixed on the horn.
7. aircraft according to claim 6, it is characterised in that consent is provided with the connection end, it is right on the horn
The consent is answered to be provided with routing hole, the connecting line of the antenna enters in the horn through the consent and the routing hole.
8. aircraft according to claim 7, it is characterised in that can be placed in the consent for seal the consent and
The elastic component of the routing hole.
9. aircraft according to claim 1, it is characterised in that when the horn is opened, the antenna is located at the machine
The lower section of arm；Or
When the horn is opened, the polarised direction and horizontal plane of the antenna；Or
The polarised direction of the antenna is vertical with the bearing of trend of the horn.
10. aircraft according to claim 1, it is characterised in that the antenna is dipole antenna.
11. aircraft according to any one of claim 1 to 10, it is characterised in that the aircraft also includes undercarriage
Component, the horn component and the foldable connection of the centre frame；The antenna when the horn component is in collapsed state
Towards the aircraft center, the antenna is set to be located at the landing gear assembly and horn component inner side.
12. a kind of aircraft, it is characterised in that including centre frame, antenna and the horn component being connected with the centre frame；It is described
Horn component and the foldable connection of the centre frame；
The horn component includes horn, and the antenna is arranged on the horn, and packs up shape when the horn component is in
The antenna makes the antenna be located in the landing gear assembly and the horn component towards the aircraft center during state
Side.
13. aircraft according to claim 12, it is characterised in that also including the connector being arranged on the horn,
The connector is used to for the antenna to be fixed on the horn.
14. aircraft according to claim 13, it is characterised in that the connector includes the lock being adapted to the horn
Tight set, and the antenna pedestal being connected with the lock sleeve, the antenna pedestal are used to carry the antenna.
15. aircraft according to claim 14, it is characterised in that the antenna pedestal includes body, the body
Including the accommodation space for accommodating the antenna.
16. aircraft according to claim 15, it is characterised in that the body also includes being located at the accommodation space
The cable-through hole of top.
17. aircraft according to claim 14, it is characterised in that the lock sleeve includes what is be connected with the antenna pedestal
Connection end, and the locking end for being fixed on the lock sleeve on the horn.
18. aircraft according to claim 17, it is characterised in that consent is provided with the connection end, on the horn
The correspondence consent is provided with routing hole, and the connecting line of the antenna enters the horn through the consent and the routing hole
It is interior.
19. aircraft according to claim 18, it is characterised in that can be placed for sealing the consent in the consent
With the elastic component of the routing hole.
20. aircraft according to claim 12, it is characterised in that the antenna is located at the lower section of the horn；Or
When the horn is opened, the polarised direction and horizontal plane of the antenna；Or
The polarised direction of the antenna is vertical with the bearing of trend of the horn.
21. aircraft according to claim 12, it is characterised in that the antenna is dipole antenna.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621247756.7U CN206218204U (en) | 2016-11-18 | 2016-11-18 | Aircraft |
| CN201680088323.8A CN109562821A (en) | 2016-11-18 | 2016-12-24 | Aircraft |
| PCT/CN2016/111920 WO2018090435A1 (en) | 2016-11-18 | 2016-12-24 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621247756.7U CN206218204U (en) | 2016-11-18 | 2016-11-18 | Aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206218204U true CN206218204U (en) | 2017-06-06 |
Family
ID=58791648
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621247756.7U Expired - Fee Related CN206218204U (en) | 2016-11-18 | 2016-11-18 | Aircraft |
| CN201680088323.8A Pending CN109562821A (en) | 2016-11-18 | 2016-12-24 | Aircraft |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680088323.8A Pending CN109562821A (en) | 2016-11-18 | 2016-12-24 | Aircraft |
Country Status (2)
| Country | Link |
|---|---|
| CN (2) | CN206218204U (en) |
| WO (1) | WO2018090435A1 (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107512391A (en) * | 2017-08-23 | 2017-12-26 | 长春长光精密仪器集团有限公司 | Based on the rotor unmanned aircraft for being tethered at cable power supply |
| EP3453615A4 (en) * | 2017-07-10 | 2019-03-20 | Autel Robotics Co., Ltd. | Antenna and unmanned aerial vehicle |
| WO2019104724A1 (en) * | 2017-12-01 | 2019-06-06 | 深圳市大疆灵眸科技有限公司 | Connecting assembly and photographing apparatus |
| US10707572B2 (en) | 2017-07-10 | 2020-07-07 | Autel Robotics Co., Ltd. | Antenna and unmanned aerial vehicle |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109774948A (en) * | 2019-02-13 | 2019-05-21 | 山东蜂巢航空科技有限公司 | It is a kind of can a variety of load of carry oil electricity mixing multi-rotor unmanned aerial vehicle |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2455374B (en) * | 2008-06-16 | 2009-11-04 | Middlesex University Higher Ed | Unmanned aerial vehicle comprising a triangular array of rotors |
| US9731811B2 (en) * | 2013-12-13 | 2017-08-15 | Aai Corporation | Payload shroud for air vehicle |
| JP6232148B2 (en) * | 2014-06-26 | 2017-11-15 | エスゼット ディージェイアイ テクノロジー カンパニー リミテッドＳｚ Ｄｊｉ Ｔｅｃｈｎｏｌｏｇｙ Ｃｏ．，Ｌｔｄ | Airplane and its signal line protection assembly |
| CN204660021U (en) * | 2015-03-12 | 2015-09-23 | 上海良相智能化工程有限公司 | The unmanned reconnaissance helicopter system of a kind of six rotor |
| CN204776013U (en) * | 2015-06-04 | 2015-11-18 | 东莞中寰智能航空科技有限公司 | Six unmanned aerial vehicle |
| CN205186516U (en) * | 2015-10-26 | 2016-04-27 | 贵州斯凯威科技有限公司 | Unmanned aerial vehicle with transportation function |
| CN105752340B (en) * | 2016-04-07 | 2017-09-01 | 广州极飞科技有限公司 | Unmanned vehicle |
| CN205652331U (en) * | 2016-04-14 | 2016-10-19 | 深圳市大疆创新科技有限公司 | Unmanned vehicles's frame and many rotors unmanned vehicles |
-
2016
- 2016-11-18 CN CN201621247756.7U patent/CN206218204U/en not_active Expired - Fee Related
- 2016-12-24 CN CN201680088323.8A patent/CN109562821A/en active Pending
- 2016-12-24 WO PCT/CN2016/111920 patent/WO2018090435A1/en active Application Filing
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3453615A4 (en) * | 2017-07-10 | 2019-03-20 | Autel Robotics Co., Ltd. | Antenna and unmanned aerial vehicle |
| US10707572B2 (en) | 2017-07-10 | 2020-07-07 | Autel Robotics Co., Ltd. | Antenna and unmanned aerial vehicle |
| CN107512391A (en) * | 2017-08-23 | 2017-12-26 | 长春长光精密仪器集团有限公司 | Based on the rotor unmanned aircraft for being tethered at cable power supply |
| WO2019104724A1 (en) * | 2017-12-01 | 2019-06-06 | 深圳市大疆灵眸科技有限公司 | Connecting assembly and photographing apparatus |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2018090435A1 (en) | 2018-05-24 |
| CN109562821A (en) | 2019-04-02 |
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