CN107434029A - A kind of anti-interference rigidity fuselage of integral frame-type - Google Patents
A kind of anti-interference rigidity fuselage of integral frame-type Download PDFInfo
- Publication number
- CN107434029A CN107434029A CN201610355486.XA CN201610355486A CN107434029A CN 107434029 A CN107434029 A CN 107434029A CN 201610355486 A CN201610355486 A CN 201610355486A CN 107434029 A CN107434029 A CN 107434029A
- Authority
- CN
- China
- Prior art keywords
- frame
- interference
- fuselage
- metal
- shell
- 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.)
- Pending
Links
- 229910052751 metal Inorganic materials 0.000 claims abstract description 23
- 239000002184 metal Substances 0.000 claims abstract description 23
- 238000009434 installation Methods 0.000 claims abstract description 6
- 230000037396 body weight Effects 0.000 abstract description 3
- 238000010276 construction Methods 0.000 abstract description 2
- 238000006263 metalation reaction Methods 0.000 abstract 1
- 230000000116 mitigating effect Effects 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 125000006850 spacer group Chemical group 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 239000010959 steel Substances 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
- B64C1/061—Frames
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Shielding Devices Or Components To Electric Or Magnetic Fields (AREA)
Abstract
The present invention relates to a kind of anti-interference rigidity fuselage of integral frame-type, including the totally enclosed shell of metal and installation metal framework in the housing.The present invention uses metal shell and frame structure form due to fuselage, interference of the extraneous signal to equipment is reduced to greatest extent, shield most interference source, equipment compartment is wrapped up in the form of metal enclosed, the stability of electrical part work is ensure that, in order to mitigate weight, supporting construction uses frame form, body weight is greatly reduced while intensity is ensured, so that the anti-interference rigidity fuselage of all-metal is achieved.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, and in particular to a kind of anti-interference rigidity machine of integral frame-type
Body.
Background technology
Unmanned plane has very big application on military and civil area, and unmanned plane generally comprises fuselage, flies control
System and power arm etc., the airframe structure of existing unmanned plane is general all very simple, primarily to mitigating machine
The weight of body, reduces the load of unmanned plane, and this simple airframe structure integral rigidity is not strong, it is impossible to full
The requirement of sufficient unmanned plane, and can not solve the problems, such as that unmanned plane signal is disturbed.
The content of the invention
A kind of entirety for unmanned plane is provided it is an object of the invention to solve above-mentioned technical problem
The anti-interference rigidity fuselage of frame-type.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of anti-interference rigidity fuselage of integral frame-type, including the totally enclosed frame of metal and installed in institute
The metal framework in shell is stated, the metal shell has the mounting plane with power arm installation.
The metal framework includes multiple main frames, and the heart intersects and outside multiple main frames in the frame
End is respectively directed to different directions and the enclosure is divided into multiple regions, each main frame
A body side frame is connected on two sides respectively；One end of each body side frame and a corresponding master
Framework is connected, the other end is connected with the inwall of the shell and forms three-legged structure.
The main frame is rectangular frame, and the body side frame is U-frame frame.
The main frame and body side frame, which intersect, to be connected.
The shell is regular polygon structure.
The anti-interference rigidity fuselage of integral frame-type of the present invention, because fuselage uses metal shell and frame structure
Form, interference of the extraneous signal to equipment is reduced to greatest extent, shields most of interference sources,
In order to mitigate weight, equipment compartment is wrapped up in the form of metal enclosed, ensure that the stability of electrical part work,
Supporting construction uses frame form, and body weight is greatly reduced while intensity is ensured, so as to
So that the anti-interference rigidity fuselage of all-metal is achieved.
Brief description of the drawings
Fig. 1 is the structural representation of the anti-interference rigidity fuselage of integral frame-type of connection power arm；
Fig. 2 is the top view of the anti-interference rigidity fuselage of integral frame-type of connection power arm.
Embodiment
Below, the substantive distinguishing features and advantage of the present invention are further described with reference to example, the present invention
Including but not limited to listed embodiment.
Referring to shown in Fig. 1-2, a kind of anti-interference rigidity fuselage of integral frame-type, including metal are totally-enclosed
Shell 100 and the metal framework in the shell 100, the metal shell has and power
The mounting plane that arm 200 is installed.
The metal framework includes multiple main frames, and the heart intersects and outside multiple main frames in the frame
End is respectively directed to different directions, and the enclosure is divided into multiple regions, each main frame
A body side frame 30 is connected on two sides respectively；One end of each body side frame and a corresponding master
Framework is connected, the other end is connected with the inwall of the shell and forms three-legged structure.
In the present invention, the main frame can include first main frame 10 and four the second main frames
Frame 20, wherein, the second main frame is connected with the first main frame, and the first main frame is equivalent to two second
Main frame, the both ends of the first main frame are connected with shell respectively.
Specifically, in the present invention, the main frame is connected with the body side frame using keeper, the side
Framework is connected with shell.
Wherein, the main frame is rectangular frame, and the body side frame is U-frame frame.
Wherein, the main frame is provided with installation keeper.Including multiple keepers on the stator of outside
11 and central spacer and interfix part, it is each provided at up and down on two end faces of main frame.The side
Framework is provided with the keeper 31 that installation connects for cap and shell bottom and the keeper fixed for shell
32, it is located at up and down on two end faces of body side frame.The quantity of the installation keeper designs as needed,
It is specific unlimited.
Wherein, the shell is regular polygon structure, hexagonal structure as shown in Figure 1, 2, also may be used
It is specific unlimited to be other shapes.
Wherein, the shell and framework can be made with steel material or aluminum alloy materials, such noise signal
Shield effectiveness is more preferable, so as to can more ensure the stabilization and security performance of flight.
The anti-interference rigidity fuselage of integral frame-type of the present invention, because fuselage uses metal shell and frame structure
Form, interference of the extraneous signal to equipment is reduced to greatest extent, most of interference sources is shielded, is
Mitigation weight, equipment compartment are wrapped up in the form of metal enclosed, ensure that the stability of electrical part work, branch
Support structure uses frame form, and body weight is greatly reduced while intensity is ensured, so that
The anti-interference rigidity fuselage of all-metal is achieved.
Described above is only the preferred embodiment of the present invention, it is noted that for the general of the art
For logical technical staff, under the premise without departing from the principles of the invention, some improvement and profit can also be made
Decorations, these improvements and modifications should be regarded as protection scope of the present invention.
Claims (5)
1. a kind of anti-interference rigidity fuselage of integral frame-type, it is characterised in that including the totally-enclosed of metal
The metal framework of shell and installation in the housing, the metal shell has to be installed with power arm
Mounting plane.
2. the anti-interference rigidity fuselage of integral frame-type according to claim 1, it is characterised in that institute
Stating metal framework includes multiple main frames, and the heart intersects and outboard end point multiple main frames in the frame
Different directions is not pointed to, and the enclosure is divided into multiple regions, the two of each main frame
A body side frame is connected on individual side respectively；One end of each body side frame and a corresponding main frame
Frame is connected, the other end is connected with the inwall of the shell and forms three-legged structure.
3. the anti-interference rigidity fuselage of integral frame-type according to claim 2, it is characterised in that institute
It is rectangular frame to state main frame, and the body side frame is U-frame frame.
4. the anti-interference rigidity fuselage of integral frame-type according to claim 3, it is characterised in that institute
State main frame and body side frame intersection is connected.
5. the anti-interference rigidity fuselage of integral frame-type according to claim 4, it is characterised in that institute
It is regular polygon structure to state shell.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355486.XA CN107434029A (en) | 2016-05-25 | 2016-05-25 | A kind of anti-interference rigidity fuselage of integral frame-type |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355486.XA CN107434029A (en) | 2016-05-25 | 2016-05-25 | A kind of anti-interference rigidity fuselage of integral frame-type |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107434029A true CN107434029A (en) | 2017-12-05 |
Family
ID=60454120
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610355486.XA Pending CN107434029A (en) | 2016-05-25 | 2016-05-25 | A kind of anti-interference rigidity fuselage of integral frame-type |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107434029A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100090061A1 (en) * | 2007-01-23 | 2010-04-15 | Airbus Deutschland Gmbh | Fuselage of an aircraft or spacecraft of crp/metal hybrid construction with a metal framework |
| CN202657241U (en) * | 2012-06-08 | 2013-01-09 | 无锡汉和航空技术有限公司 | Unmanned helicopter fuselage frame |
| CN204507259U (en) * | 2015-03-26 | 2015-07-29 | 徐知非 | The safe multi-rotor aerocraft of joinery and its construction gusseted light sheet |
| CN204527660U (en) * | 2015-02-13 | 2015-08-05 | 湖北大秀天域科技发展有限公司 | Many rotor wing unmanned aerial vehicles |
| CN204527629U (en) * | 2015-04-21 | 2015-08-05 | 刘亚敏 | A kind of four-axle aircraft with shell |
| US20160101850A1 (en) * | 2014-10-13 | 2016-04-14 | Che Min LIN | Multi-rotor frame structure |
| CN205770108U (en) * | 2016-05-25 | 2016-12-07 | 天津宏宇天翔科技有限公司 | A kind of integral frame-type anti-interference rigidity fuselage |
-
2016
- 2016-05-25 CN CN201610355486.XA patent/CN107434029A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100090061A1 (en) * | 2007-01-23 | 2010-04-15 | Airbus Deutschland Gmbh | Fuselage of an aircraft or spacecraft of crp/metal hybrid construction with a metal framework |
| CN202657241U (en) * | 2012-06-08 | 2013-01-09 | 无锡汉和航空技术有限公司 | Unmanned helicopter fuselage frame |
| US20160101850A1 (en) * | 2014-10-13 | 2016-04-14 | Che Min LIN | Multi-rotor frame structure |
| CN204527660U (en) * | 2015-02-13 | 2015-08-05 | 湖北大秀天域科技发展有限公司 | Many rotor wing unmanned aerial vehicles |
| CN204507259U (en) * | 2015-03-26 | 2015-07-29 | 徐知非 | The safe multi-rotor aerocraft of joinery and its construction gusseted light sheet |
| CN204527629U (en) * | 2015-04-21 | 2015-08-05 | 刘亚敏 | A kind of four-axle aircraft with shell |
| CN205770108U (en) * | 2016-05-25 | 2016-12-07 | 天津宏宇天翔科技有限公司 | A kind of integral frame-type anti-interference rigidity fuselage |
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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 | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20171205 |
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| WD01 | Invention patent application deemed withdrawn after publication |