CN207565824U - A kind of unmanned plane forebody structure - Google Patents
A kind of unmanned plane forebody structure Download PDFInfo
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- CN207565824U CN207565824U CN201721493851.XU CN201721493851U CN207565824U CN 207565824 U CN207565824 U CN 207565824U CN 201721493851 U CN201721493851 U CN 201721493851U CN 207565824 U CN207565824 U CN 207565824U
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Abstract
This application discloses a kind of unmanned plane forebody structures, belong to unmanned air vehicle technique field.The frame being arranged in parallel including at least two, each frame are equipped with partition board, forebody are divided at least one cabin；At least one platform is equipped between frame described in each two in the horizontal direction, each platform is used to set unmanned machine equipment；The forebody covering being connect with each frame is equipped with outside the frame.The application will be divided into multiple portions by frame inside forebody, and partition board is installed on each frame, cabin and equipment are isolated, cook up the space in each cabin, simultaneously influencing each other and interfering between each equipment of ship's space is avoided for equipment installation in each cabin setting platform.
Description
Technical field
The application belongs to field of artificial intelligence, more particularly to a kind of unmanned plane forebody structure.
Background technology
With the development that unmanned plane is applied, the continuous expansion of application range, unmanned plane needs to configure various advanced equipment
To satisfy the use demand.And the increase and diversification of internal installation equipment, as photoelectricity ball, noctovisor scan instrument, radar altimeter,
Airborne computer etc., how the structure of reasonable Arrangement forebody becomes particularly important.
Apply for content
In order to solve Yi Shang technical problem in the prior art, the application provides a kind of unmanned plane forebody structure,
Rationally using inner space advancing equipment, space availability ratio is improved.
The one side of the application, provides a kind of unmanned plane forebody structure, the frame being arranged in parallel including at least two,
Each frame is equipped with partition board, and forebody is divided at least one cabin；It is equipped in the horizontal direction between frame described in each two
At least one platform, each platform are used to set unmanned machine equipment；It is equipped with what is connect with each frame outside the frame
Forebody covering.
Optionally, the frame includes the first frame, the second frame and third frame, from the front end of forebody backward successively
Increase setting, is equipped with the first platform, second frame and third in the horizontal direction between first frame and the second frame
The second platform is equipped between frame in the horizontal direction.
Optionally, it is equipped with third platform in the horizontal direction below second platform.
Optionally, first platform, the second platform and third platform are arranged on by the crossbeam on frame on frame.
Optionally, communication system stent is equipped in the front end of the first frame, Satellite Communication System passes through the communication system
Stent is mounted on the first frame.
Optionally, the communication system stent is mounted on by the crossbeam on first frame.
Optionally, first platform is equipped with GPS navigation system, identification of friend or foe, airborne computer.
Optionally, second platform is equipped with battery pack, VDM virtual machines, radar altimeter.
Optionally, the lower section of the third platform is photoelectric nacelle, and photoelectricity ball is equipped in photoelectric nacelle, the photoelectricity ball
Lift-on/Lift-off System is retractable structure.
Optionally, the forebody covering includes wainscot, lower wall panels and radome fairing, the wainscot and lower wall panels difference
Simultaneously connect with the first frame, the second frame and third frame, the radome fairing be arranged on first frame front end and with institute
State the connection of the first frame.
The another aspect of the application provides a kind of unmanned plane, including as above any one of them unmanned plane forebody knot
Structure.
The application will be divided into multiple portions by frame inside forebody, and install partition board on each frame, to cabin
And equipment is isolated, and is cooked up the space in each cabin, while platform is set to be installed for equipment in each cabin, is avoided
It influencing each other between each equipment of ship's space and interferes.
Description of the drawings
In order to illustrate the technical solutions in the embodiments of the present application or in the prior art more clearly, to embodiment or it will show below
There is attached drawing needed in technology description to be briefly described, it should be apparent that, the accompanying drawings in the following description is only this
Some embodiments described in application, for those of ordinary skill in the art, without creative efforts,
It can also be obtained according to these attached drawings other attached drawings.
Fig. 1 is a kind of structure diagram of one embodiment of unmanned plane forebody structure of the application；
Fig. 2 is a kind of interior layout schematic diagram of another embodiment of unmanned plane forebody structure of the application；
Fig. 3 is a kind of forebody stressed-skin construction schematic diagram of unmanned plane forebody structure another embodiment of the application.
In figure：
10th, longeron 11, the first frame 12, the second frame 13, third frame
14th, the first platform 15, the second platform 16, third platform 17, crossbeam
18th, partition board 19, communication system stent
21st, Satellite Communication System 22, identification of friend or foe 23, GPS navigation system
24th, VDM virtual machines 25, battery pack 26, radar altimeter
27th, photoelectric nacelle 28, airborne computer
31st, wainscot 32, radome 33, lower wall panels
Specific embodiment
In order to which those skilled in the art is made to more fully understand application scheme, below in conjunction in the embodiment of the present application
The technical solution in the embodiment of the present application is clearly and completely described in attached drawing, it is clear that described embodiment is only this
Apply for part of the embodiment, instead of all the embodiments.Based on the embodiment in the application, those of ordinary skill in the art exist
All other embodiments obtained under the premise of creative work are not made, shall fall in the protection scope of this application.
One embodiment of the application unmanned plane forebody structure includes at least two frames being arranged in parallel, and is set on each frame
There is partition board 18, forebody is divided at least one cabin；Prolong horizontal direction between frame described in each two and be equipped at least one put down
Platform, each platform are used to set unmanned machine equipment；The forebody covering being connect with each frame is equipped with outside the frame.
It is understood that as shown in Figure 1, fore-end of the forebody of unmanned plane for unmanned plane, unmanned plane forebody
Front end be unmanned plane front end, design unmanned plane forebody when, can be set successively along upper and lower directions from front to back
At least two frames are put, the shape of frame is consistent with the cross sectional shape of unmanned plane forebody；At least two frames for example can be
It is arranged in parallel, here parallel is not limited to be substantially parallel, as long as in parallel trend；Certainly, frame can also be three
It is a or three or more, it is therefore an objective to which that forebody is divided into multiple spaces；Each frame is equipped with partition board, for multiple spaces are complete
It separates entirely, becomes relatively independent cabin.It can be equipped in front and rear horizontal direction, between each two frame at least one flat
Platform, the various equipment needed for unmanned plane for being disposed above or below by the platform, for example, infrared scanning
Instrument, photoelectricity ball etc. are installed convenient for equipment, improve inner space utilization rate；Due to being equipped with partition board on each frame, to equipment
Isolation is formed, avoids influencing each other and interfering between each equipment of ship's space.
Fig. 1 is the structure diagram of another embodiment of the application.As shown in Figure 1, the frame includes the first frame 11, the
Two frames 12 and third frame 13 are sequentially increased setting, 11 and second frame of the first frame backward from the front end of forebody
The first platform 14 is equipped between 12 in the horizontal direction, is equipped with the between second frame 11 and third frame 13 in the horizontal direction
Two platforms 15.It is, of course, also possible between the first frame 11 and the second frame 12 or the second frame 12 and third frame 13 it
Between can also more platforms be set according to demand that equipment is put, for example, below second platform 15 in the horizontal direction
Third platform 16 is set.
Specifically, can set crossbeam 17 on each frame, the first platform 14, the second platform 15 and third platform 16 can
To be arranged on frame by the crossbeam 17 on frame.
It connects and fixes outside except through each platform between each frame, in order to strengthen the stability of forebody structure,
Longeron 10 can also be set between each frame, and the setting quantity of reinforcing rib 10 and installation position can be according to the designs of forebody
Intensity requirement and platform and the specific location of equipment determine.
It is understood that the present embodiment includes three frames, it can be by nothing by the partition board 18 installed on each frame
Man-machine forebody is separated into two independent cabins, according to the shape and design feature of unmanned plane, the frame of forebody from front to back
Frame is sequentially increased, for example, frame is circular, then form diameter from front to back is gradually incremental, i.e. the first frame
Frame diameter is less than the second form diameter, and the second form diameter is less than third form diameter.Between three frames, the present embodiment is set
Put three platforms, i.e., the first platform be provided between the first frame and the second frame, the second frame and third frame it
Between two platforms, i.e. the second platform and third platform have been arranged in parallel, which will be between the second frame and third frame
Space be divided into three cabins of upper, middle and lower, equipment needed for unmanned plane can be arranged by these three platforms.
In an embodiment of the present embodiment, as shown in Figs. 1-2, communication can be set in the front end of the first frame 11
System frame 19, Satellite Communication System 21 are mounted on by the communication system stent 19 on the first frame 11.Show as one kind
Example, the communication system stent 19 are mounted on the front end of first frame 11 by the crossbeam 17.
In another embodiment, as shown in Fig. 2, GPS navigation system 23, enemy can be equipped on first platform 14
My identifying system 22, airborne computer 28.Certainly, the present embodiment, which is not limited on the first platform, sets above several equipment,
Other equipment can also be set according to actual needs, as long as the equipment in the space does not interfere with each other, and rationally distributed.
In another embodiment, as shown in Fig. 2, second platform 15 is equipped with battery pack 25, VDM virtual machines
24th, radar altimeter 26.Certainly, the present embodiment, which is not limited on the first platform, sets above several equipment, can also basis
Actual needs setting other equipment, as long as the equipment in the space does not interfere with each other, and rationally distributed.
In the 4th kind of embodiment, as shown in Fig. 2, the lower section of the third platform 16 is photoelectric nacelle 27, photoelectricity is hung
Photoelectricity ball can be for example set in cabin 27, which is mounted on third platform 16 in the following, and the lifting system by Lift-on/Lift-off System
System is equipped with the movement of electric control telescoping mechanism control photoelectricity ball.Specifically, the 27 lower section covering of photoelectric nacelle is equipped with hatch door, hatch door
Photoelectricity ball can stretch out out of my cabin after opening, and carry out investigations work, withdraw in cabin during off working state, avoid equipment damage.
It should be noted that Satellite Communication System is arranged in front fuselage by the present embodiment, convenient for the transmission of signal；Preceding
Fuselage interior sets three platforms to be installed for equipment, and equipment platform is installed by the crossbeam on fuselage ring, landing slab
It using detachable structure, is connect by bolt with crossbeam, convenient for the dismounting and maintenance of later equipment.
Fig. 3 is the forebody stressed-skin construction schematic diagram of the application another embodiment.As shown in figure 3, the forebody covering
Including wainscot 31, lower wall panels 33 and radome fairing 32, the wainscot 31 and each frame connection simultaneously respectively of lower wall panels 33, example
It can such as be connect with the first frame 11, the second frame 12 and third frame 13, the radome fairing 32 is arranged on first frame
It 11 front ends and is connect with first frame 11.Existing connection mode specifically may be used as glued in wainscot 31 and lower wall panels 33
Equivalent frame connection is connect or is bolted, details are not described herein.
Specifically, the radome fairing 32 is mounted on the outside of Satellite Communication System 21.For the ease of the transmission of communication signal
With reception, radome fairing 32 can select the preferable glass fibre entity laminate structure of wave transmission rate.
Existing unmanned plane covering is generally divided into wainscot, left/right sidewall paneling, lower wall panels, and covering piecemeal is complicated, increases assembling
Workload is unfavorable for fuselage loss of weight.And the present embodiment on covering piecemeal in the case where not influencing assembling, covering is divided into
Radome fairing, wainscot, lower wall panels three parts, simplify partitioned mode, improve the globality and intensity of covering, reduce the work of assembling
It measures, reduces fuselage weight coefficient, improve fuel load and voyage.
Certainly, unmanned plane forebody structure described in example is performed as described above in addition to providing in the application, additionally provide it is a kind of nobody
Machine, the unmanned plane include any unmanned plane forebody structure as described above.
The above is only the application preferred embodiment, not makees limitation in any form to the application.Although
The application is disclosed above with preferred embodiment, however is not limited to the application.Any those skilled in the art,
In the case where not departing from technical scheme ambit, all using the methods and technical content of the disclosure above to present techniques
Scheme makes many possible changes and modifications or is revised as the equivalent embodiment of equivalent variations.Therefore, it is every without departing from this Shen
Please technical solution content, according to technical spirit any simple modification made to the above embodiment of the application, equivalent variations
And modification, still fall within technical scheme protection in the range of.
Claims (10)
1. a kind of unmanned plane forebody structure, which is characterized in that the frame being arranged in parallel including at least two is set on each frame
There is partition board（18）, forebody is divided at least one cabin；It is equipped in the horizontal direction between frame described in each two at least one
Platform, each platform are used to set unmanned machine equipment；The forebody connecting with each frame is equipped with outside the frame to cover
Skin.
2. forebody structure according to claim 1, which is characterized in that the frame includes the first frame（11）, second
Frame（12）And third frame（13）, it is sequentially increased setting, first frame backward from the front end of forebody（11）With second
Frame（12）Between in the horizontal direction be equipped with the first platform（14）, second frame（11）With third frame（13）Between along water
Square to equipped with the second platform（15）.
3. forebody structure according to claim 2, which is characterized in that in second platform（15）Below along level side
To equipped with third platform（16）.
4. forebody structure according to claim 3, which is characterized in that first platform（14）, the second platform（15）
And third platform（16）Pass through the crossbeam on frame（17）It is arranged on frame.
5. forebody structure according to claim 2, which is characterized in that in the first frame（11）Front end be equipped with communication be
System stent（19）, Satellite Communication System（21）Pass through the communication system stent（19）Mounted on the first frame（11）On.
6. forebody structure according to claim 5, which is characterized in that the communication system stent（19）Pass through crossbeam
（17）Mounted on first frame（11）On.
7. forebody structure according to claim 2, which is characterized in that first platform（14）It is equipped with GPS navigation
System（23）, identification of friend or foe（22）, airborne computer（28）.
8. forebody structure according to claim 2, which is characterized in that second platform（15）It is equipped with battery pack
（25）, VDM virtual machines（24）, radar altimeter（26）.
9. forebody structure according to claim 3, which is characterized in that the third platform（16）Lower section hung for photoelectricity
Cabin（27）, photoelectric nacelle（27）Interior to be equipped with photoelectricity ball, the Lift-on/Lift-off System of the photoelectricity ball is retractable structure.
10. according to claim 2-9 any one of them forebody structures, which is characterized in that the forebody covering includes upper
Siding（31）, lower wall panels（33）And radome fairing（32）, the wainscot（31）And lower wall panels（33）Respectively simultaneously with the first frame
（11）, the second frame（12）And third frame（13）Connection, the radome fairing（32）It is arranged on first frame（11）Front end
And with first frame（11）Connection.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721493851.XU CN207565824U (en) | 2017-11-10 | 2017-11-10 | A kind of unmanned plane forebody structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721493851.XU CN207565824U (en) | 2017-11-10 | 2017-11-10 | A kind of unmanned plane forebody structure |
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| Publication Number | Publication Date |
|---|---|
| CN207565824U true CN207565824U (en) | 2018-07-03 |
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ID=62694188
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| Application Number | Title | Priority Date | Filing Date |
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| CN201721493851.XU Active CN207565824U (en) | 2017-11-10 | 2017-11-10 | A kind of unmanned plane forebody structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672778A (en) * | 2017-11-10 | 2018-02-09 | 江苏美龙航空部件有限公司 | A kind of unmanned plane forebody structure |
| CN109606612A (en) * | 2018-12-28 | 2019-04-12 | 中国电子科技集团公司电子科学研究院 | Extraordinary unmanned plane structure-function integration bay section and extraordinary unmanned plane |
| CN111928092A (en) * | 2020-07-17 | 2020-11-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Mounting bracket and have its mounting structure |
-
2017
- 2017-11-10 CN CN201721493851.XU patent/CN207565824U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672778A (en) * | 2017-11-10 | 2018-02-09 | 江苏美龙航空部件有限公司 | A kind of unmanned plane forebody structure |
| CN109606612A (en) * | 2018-12-28 | 2019-04-12 | 中国电子科技集团公司电子科学研究院 | Extraordinary unmanned plane structure-function integration bay section and extraordinary unmanned plane |
| CN111928092A (en) * | 2020-07-17 | 2020-11-13 | 中国航空工业集团公司沈阳飞机设计研究所 | Mounting bracket and have its mounting structure |
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