CN107672778A - A kind of unmanned plane forebody structure - Google Patents
A kind of unmanned plane forebody structure Download PDFInfo
- Publication number
- CN107672778A CN107672778A CN201711103809.7A CN201711103809A CN107672778A CN 107672778 A CN107672778 A CN 107672778A CN 201711103809 A CN201711103809 A CN 201711103809A CN 107672778 A CN107672778 A CN 107672778A
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- framework
- forebody
- platform
- structure according
- unmanned plane
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- 238000004891 communication Methods 0.000 claims description 17
- 230000005622 photoelectricity Effects 0.000 claims description 12
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 230000005540 biological transmission Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 208000033999 Device damage Diseases 0.000 description 1
- 238000013473 artificial intelligence Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000002955 isolation Methods 0.000 description 1
- 208000020442 loss of weight Diseases 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 230000008054 signal transmission Effects 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
-
- 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
- B64C1/061—Frames
-
- 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
- B64D47/00—Equipment not otherwise provided for
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Position Fixing By Use Of Radio Waves (AREA)
Abstract
This application discloses a kind of unmanned plane forebody structure, belong to unmanned air vehicle technique field.Including at least two frameworks be arrangeding in parallel, each framework is provided with dividing plate, and forebody is divided into at least one cabin；At least one platform is provided between framework described in each two in the horizontal direction, each platform is used to set unmanned machine equipment；The forebody covering being connected with each framework is provided with outside the framework.The application will be divided into some by framework inside forebody, and dividing plate is installed on each framework, cabin and equipment are isolated, cook up the space in each cabin, set platform to be used for equipment installation in each cabin simultaneously, avoid influencing each other and disturbing between each equipment of ship's space.
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, unmanned plane needs to configure various advanced equipment
To meet use demand.And the increase and variation 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 above technical problem present in prior art, the application provides a kind of unmanned plane forebody structure,
Inner space advancing equipment is rationally utilized, improves space availability ratio.
The one side of the application, there is provided a kind of unmanned plane forebody structure, including at least two frameworks be arrangeding in parallel,
Each framework is provided with dividing plate, and forebody is divided into at least one cabin；It is provided with the horizontal direction between framework described in each two
At least one platform, each platform are used to set unmanned machine equipment；It is provided with what is be connected with each framework outside the framework
Forebody covering.
Optionally, the framework includes the first framework, the second framework and the 3rd framework, from the front end of forebody backward successively
Increase is set, and is provided with the first platform, second framework and the 3rd between first framework and the second framework in the horizontal direction
The second platform is provided between framework in the horizontal direction.
Optionally, it is provided with the 3rd platform in the horizontal direction below second platform.
Optionally, first platform, the second platform and the 3rd platform are arranged on framework by the crossbeam on framework.
Optionally, communication system support is provided with the front end of the first framework, Satellite Communication System passes through the communication system
Support is arranged on the first framework.
Optionally, the communication system support is arranged on first framework by the crossbeam.
Optionally, first platform is provided with GPS navigation system, identification of friend or foe, airborne computer.
Optionally, second platform is provided with battery pack, VDM virtual machines, radar altimeter.
Optionally, the lower section of the 3rd platform is photoelectric nacelle, and photoelectricity ball is provided with photoelectric nacelle, the photoelectricity ball
Lift-on/Lift-off System is Collapsible structure.
Optionally, the forebody covering includes wainscot, lower wall panels and radome fairing, the wainscot and lower wall panels difference
Simultaneously be connected with the first framework, the second framework and the 3rd framework, the radome fairing be arranged on first frame front end and with institute
State the connection of the first framework.
The another aspect of the application, there is provided a kind of unmanned plane, including the as above unmanned plane forebody knot described in any one
Structure.
The application will be divided into some by framework inside forebody, and install dividing plate on each framework, to cabin
And equipment is isolated, the space in each cabin is cooked up, while sets platform to be installed for equipment in each cabin, is avoided
Influencing each other between each equipment of ship's space and disturb.
Brief description of the drawings
, below will be to embodiment or existing in order to illustrate more clearly of the embodiment of the present application or technical scheme of the prior art
There is the required accompanying drawing used in technology description to be briefly described, it should be apparent that, drawings in the following description are only this
Some embodiments described in application, for those of ordinary skill in the art, on the premise of not paying creative work,
Other accompanying drawings can also be obtained according to these accompanying drawings.
Fig. 1 is a kind of structural representation of the embodiment of unmanned plane forebody structure one 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 framework 12, the second framework 13, the 3rd framework
14th, the first platform 15, the second platform 16, the 3rd platform 17, crossbeam
18th, dividing plate 19, communication system support
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
Embodiment
In order that those skilled in the art more fully understand application scheme, below in conjunction with the embodiment of the present application
Accompanying drawing, the technical scheme in the embodiment of the present application is clearly and completely described, it is clear that described embodiment is only this
Apply for part of the embodiment, rather than whole embodiments.Based on the embodiment in the application, those of ordinary skill in the art exist
The every other embodiment obtained under the premise of creative work is not made, belongs to the scope of the application protection.
The embodiment of the application unmanned plane forebody structure one includes at least two frameworks be arrangeding in parallel, is set on each framework
There is dividing plate 18, forebody is divided at least one cabin；Prolong horizontal direction between framework described in each two and be provided with least one put down
Platform, each platform are used to set unmanned machine equipment；The forebody covering being connected with each framework is provided with outside the framework.
It is understood that as shown in figure 1, the forebody of unmanned plane be unmanned plane fore-end, unmanned plane forebody
Front end be unmanned plane front end, design unmanned plane forebody when, can be set successively along above-below direction from front to back
At least two frameworks are put, the shape of framework is consistent with the cross sectional shape of unmanned plane forebody；At least two frameworks for example can be
It is arranged in parallel, here parallel is not limited to be substantially parallel, as long as being in parallel trend；Certainly, framework can also be three
It is individual or more than three, it is therefore an objective to which that forebody is divided into multiple spaces；Each framework is provided with dividing plate, for multiple spaces are complete
Separate entirely, turn into relatively independent cabin.It can be provided with front and rear horizontal direction, between each two framework at least one flat
Platform, the platform is for the various equipment needed for unmanned plane to be disposed above or below, for example, noctovisor scan
Instrument, photoelectricity ball etc., are easy to equipment to install, and improve inner space utilization rate；Due to being equipped with dividing plate on each framework, to equipment
Isolation is formed, avoids influencing each other and disturbing between each equipment of ship's space.
Fig. 1 is the structural representation of another embodiment of the application.As shown in figure 1, the framework includes the first framework 11, the
Two frameworks 12 and the 3rd framework 13, from the front end of forebody, increase is set successively backward, the framework of the first framework 11 and second
The first platform 14 is provided between 12 in the horizontal direction, is provided with the between second framework 11 and the 3rd framework 13 in the horizontal direction
Two platforms 15.It is, of course, also possible between the first framework 11 and the second framework 12, or the second framework 12 and the 3rd framework 13 it
Between more platforms can also be set according to demand that equipment is put, for example, below second platform 15 in the horizontal direction
3rd platform 16 is set.
Specifically, can set crossbeam 17 on each framework, the first platform 14, the second platform 15 and the 3rd platform 16 can
To be arranged on by the crossbeam 17 on framework on framework.
Between each framework in addition to connecting and fixing by each platform, in order to strengthen the steadiness of forebody structure,
Longeron 10 can also be set between each framework, and the setting quantity and set location of reinforcement 10 can be according to the designs of forebody
Intensity requirement and platform and the particular location of equipment determine.
It is understood that the present embodiment includes three frameworks, can be by nothing by the dividing plate 18 installed on each framework
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 increases successively, for example, framework 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 the 3rd form diameter.Between three frameworks, the present embodiment is set
Put three platforms, i.e., the first platform be provided between the first framework and the second framework, the second framework and the 3rd framework it
Between be arranged in parallel two platforms, i.e. the second platform and the 3rd platform, two platforms are by between the second framework and the 3rd framework
Space divide 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 Figure 1-2, communication can be set in the front end of the first framework 11
System frame 19, Satellite Communication System 21 are arranged on the first framework 11 by the communication system support 19.Show as one kind
Example, the communication system support 19 are arranged on the front end of first framework 11 by the crossbeam 17.
In another embodiment, as shown in Fig. 2 GPS navigation system 23, enemy can be provided with first platform 14
My identifying system 22, airborne computer 28.Certainly, the present embodiment, which is not limited on the first platform, sets several equipment above,
Can also be and rationally distributed as long as the equipment in the space does not interfere with each other according to being actually needed setting other equipment.
In another embodiment, as shown in Fig. 2 second platform 15 is provided with battery pack 25, VDM virtual machines
24th, radar altimeter 26.Certainly, the present embodiment, which is not limited on the first platform, sets several equipment above, can also basis
Setting other equipment is actually needed, if the equipment in the space does not interfere with each other, and it is rationally distributed.
In the 4th kind of embodiment, as shown in Fig. 2 the lower section of the 3rd platform 16 is photoelectric nacelle 27, photoelectricity is hung
Photoelectricity ball can be for example set in cabin 27, and the photoelectricity ball is arranged on below the 3rd platform 16 by Lift-on/Lift-off System, and the lifting system
System is provided with the motion of electric control telescoping mechanism control photoelectricity ball.Specifically, the lower section covering of photoelectric nacelle 27 is provided 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 device damage.
It should be noted that Satellite Communication System is arranged in front fuselage by the present embodiment, it is easy to 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
Using demountable structure, it is connected by bolt with crossbeam, is easy to 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 framework connection simultaneously respectively of lower wall panels 33, example
It can be such as connected with the first framework 11, the second framework 12 and the 3rd framework 13, the radome fairing 32 is arranged on first framework
11 front ends and it is connected with first framework 11.Wainscot 31 and lower wall panels 33 can specifically use existing connected mode as glued
Connect or the equivalent framework of bolt connection connects, will not be repeated here.
Specifically, the radome fairing 32 is arranged 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, increase assembling
Workload, it is unfavorable for fuselage loss of weight.And the present embodiment, in the case where not influenceing assembling, covering is divided on covering piecemeal
Radome fairing, wainscot, lower wall panels three parts, simplify partitioned mode, improve the globality and intensity of covering, reduce the work of assembling
Measure, reduce fuselage weight coefficient, improve fuel load and voyage.
Certainly, unmanned plane forebody structure described in example is performed as described above except 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.
It is described above, only it is the application preferred embodiment, not makees any formal limitation to the application.Although
The application is disclosed above with preferred embodiment, but 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 scheme content, the technical spirit according to the application is to any simple modification made for any of the above embodiments, equivalent variations
And modification, still fall within technical scheme protection in the range of.
Claims (10)
1. a kind of unmanned plane forebody structure, it is characterised in that including at least two frameworks be arrangeding in parallel, set on each framework
There is dividing plate (18), forebody is divided at least one cabin；It is provided with the horizontal direction between framework described in each two at least one
Platform, each platform are used to set unmanned machine equipment；The forebody being connected with each framework is provided with outside the framework to cover
Skin.
2. forebody structure according to claim 1, it is characterised in that the framework includes the first framework (11), second
Framework (12) and the 3rd framework (13), from the front end of forebody, increase is set successively backward, first framework (11) and second
The first platform (14) is provided between framework (12) in the horizontal direction, along water between second framework (11) and the 3rd framework (13)
Square to provided with the second platform (15).
3. forebody structure according to claim 2, it is characterised in that in second platform (15) below along level side
To provided with the 3rd platform (16).
4. forebody structure according to claim 3, it is characterised in that first platform (14), the second platform (15)
And the 3rd platform (16) be arranged on by the crossbeam (17) on framework on framework.
5. forebody structure according to claim 2, it is characterised in that being provided with communication in the front end of the first framework (11) is
System support (19), Satellite Communication System (21) are arranged on the first framework (11) by the communication system support (19).
6. forebody structure according to claim 5, it is characterised in that the communication system support (19) passes through the horizontal stroke
Beam (17) is arranged on first framework (11).
7. forebody structure according to claim 2, it is characterised in that first platform (14) is provided with GPS navigation
System (23), identification of friend or foe (22), airborne computer (28).
8. forebody structure according to claim 2, it is characterised in that second platform (15) is provided with battery pack
(25), VDM virtual machines (24), radar altimeter (26).
9. forebody structure according to claim 3, it is characterised in that hung for photoelectricity the lower section of the 3rd platform (16)
Cabin (27), photoelectric nacelle (27) is interior to be provided with photoelectricity ball, and the Lift-on/Lift-off System of the photoelectricity ball is Collapsible structure.
10. according to the forebody structure described in claim any one of 2-9, it is characterised in that the forebody covering includes upper
Wallboard (31), lower wall panels (33) and radome fairing (32), the wainscot (31) and lower wall panels (33) respectively simultaneously with the first framework
(11), the second framework (12) and the connection of the 3rd framework (13), the radome fairing (32) are arranged on the first framework (11) front end
And it is connected with first framework (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711103809.7A CN107672778A (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 |
|---|---|---|---|
| CN201711103809.7A CN107672778A (en) | 2017-11-10 | 2017-11-10 | A kind of unmanned plane forebody structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107672778A true CN107672778A (en) | 2018-02-09 |
Family
ID=61146685
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711103809.7A Pending CN107672778A (en) | 2017-11-10 | 2017-11-10 | A kind of unmanned plane forebody structure |
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| Country | Link |
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| CN (1) | CN107672778A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112093041A (en) * | 2020-10-30 | 2020-12-18 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and fairing assembly thereof |
| CN112478126A (en) * | 2020-12-02 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned aerial vehicle fuselage cabin section |
| RU229488U1 (en) * | 2024-06-11 | 2024-10-08 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | NOSE COMPARTMENT OF THE FUSELAGE WITH BRACKETS FOR FASTENING THE OUTBOARD UNIT |
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Cited By (7)
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| CN112093041A (en) * | 2020-10-30 | 2020-12-18 | 北京清航紫荆装备科技有限公司 | Cross double-rotor unmanned helicopter and fairing assembly thereof |
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| RU229488U1 (en) * | 2024-06-11 | 2024-10-08 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | NOSE COMPARTMENT OF THE FUSELAGE WITH BRACKETS FOR FASTENING THE OUTBOARD UNIT |
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