CN107434028A - A kind of fuselage of full open type unmanned plane - Google Patents
A kind of fuselage of full open type unmanned plane Download PDFInfo
- Publication number
- CN107434028A CN107434028A CN201610355488.9A CN201610355488A CN107434028A CN 107434028 A CN107434028 A CN 107434028A CN 201610355488 A CN201610355488 A CN 201610355488A CN 107434028 A CN107434028 A CN 107434028A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- shell
- frame
- open type
- unmanned plane
- 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 20
- 239000002184 metal Substances 0.000 claims abstract description 20
- 238000009434 installation Methods 0.000 claims abstract description 4
- 238000012423 maintenance Methods 0.000 abstract description 5
- 238000000354 decomposition reaction Methods 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
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000037396 body weight Effects 0.000 description 1
- 238000005034 decoration Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 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
- 230000002093 peripheral effect Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 238000003786 synthesis reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- 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
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The present invention relates to a kind of fuselage of full open type unmanned plane, including integral type makes the detachable cap of the metal shell to be formed and the upper end open-mouth installed in the shell, and the metal shell has the mounting plane with power arm installation.The invention enables assembling, maintenance, maintenance to become extremely simple, and framework effectively improves fuselage stressing conditions, so that full open type fuselage is achieved with the mounting means being integrally combined.Improve integral body intensity.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, and in particular to a kind of fuselage of full open type unmanned plane.
Background technology
Unmanned plane has very big application on military and civil area, and unmanned plane generally comprises fuselage, flies control
System and dynamical system etc., the airframe structure of existing unmanned plane are usually double-layer plate frame structure, fuselage
Using integral disassembly, assembly form, or open on shell it is multiple safeguard lid, internal unit is safeguarded complicated, difficult
Degree is big.Full open type airframe structure, using fast disassembly type body cap so that maintenance becomes simple, fuselage
Intensity is ensured, the synthesis performance of unmanned plane is greatly improved.
The content of the invention
There is provided a kind of for the complete spacious of unmanned plane it is an object of the invention to solve above-mentioned technical problem
Open type fuselage.
To achieve the above object, the present invention adopts the following technical scheme that：
A kind of full open type unmanned aerial vehicle body, including integral type make the metal shell to be formed and are arranged on
The detachable cap of shell upper end open-mouth, the metal shell have and power arm installation
Mounting plane.
Metal support frame is installed in the shell, the metal support frame includes multiple main frames,
The heart intersects multiple main frames in the frame, and outboard end is respectively directed to different directions, by described in
Enclosure is divided into multiple regions, and two sides of each main frame connect a body side frame respectively；
One end of each body side frame is connected with a corresponding main frame, the other end and the shell
Inwall is connected and forms three-legged structure.
The main frame is rectangular frame, and the body side frame is U-frame frame.
The cap is connected with metal support frame by keeper.
The shell is polygonized structure.
Full open type unmanned aerial vehicle body of the invention, using metal shell, shield to greatest extent external dry
Interference of the source to equipment is disturbed, and ensure that the intensity of fuselage to greatest extent so that assemble, repair,
Maintenance becomes extremely simple, the mounting means being located by connecting, effectively improves fuselage stressing conditions,
So as to improve fuselage bulk strength.
Brief description of the drawings
Fig. 1 is the decomposition texture schematic diagram of the fuselage of full open type unmanned plane；
Fig. 2 is the decomposition side view of the fuselage of full open type unmanned plane.
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 fuselage of full open type unmanned plane, including integral type make what is formed
Metal shell 10 and the detachable cap 20 at shell upper end opening 12, the gold
Belonging to shell has the mounting plane installed with power arm.
Full open type unmanned aerial vehicle body of the invention, using metal shell, shield to greatest extent external dry
Interference of the source to equipment is disturbed, and ensure that the intensity of fuselage to greatest extent so that assemble, repair,
Maintenance becomes extremely simple, the mounting means being located by connecting, effectively improves fuselage stressing conditions,
So as to improve fuselage bulk strength.
Metal support frame 11 is installed in the shell 10, more effectively to strengthen the intensity of fuselage.
The metal support frame includes multiple main frames, and the heart intersects multiple main frames in the frame,
Outboard end is respectively directed to different directions, and the enclosure is divided into multiple regions, each main frame
Two sides of frame connect a body side frame 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 and four the second main frames,
Wherein, the second main frame is connected with the first main frame, equivalent to two the second main frames of the first main frame,
The both ends of first main frame are connected with shell respectively.
In the present invention, the main frame is connected with the body side frame using keeper, the body side frame with it is outer
Shell is equally connected using keeper.
The main frame is rectangular frame, and the body side frame is U-frame frame.
The main frame be provided with multiple positioning holes 13 on mounting-positioning holes, including outside stator with
And center and interfix hole, the body side frame are provided with the positioning for being used for being connected with cap and shell bottom, with
And the positioning fixed for shell, the installation positioning quantity design as needed.
The cap is provided with corresponding positioning hole, such as peripheral positioning holes 21, center positioning hole 23 and
Middle positioning hole 22, the positioning hole corresponded respectively on framework.
The cap 20 has the non-rim of the mouth 25 surrounded entirely, is fixed with the outer wall of shell.Enhance cap
With the stability of cage connection.
The cap 20 is provided with battery positioning hole 24, installs more Battery packs in shell, is placed in frame
In frame.
The shell is polygonized structure, hexagonal structure as shown in Figure 1 or other shapes,
It is specific unlimited.
The shell and framework can be that steel material or aluminum alloy materials make, the shielding of such noise signal
Effect is more preferable, so as to can more ensure the stability of flight.
The fuselage of full open type unmanned plane of the invention, because fuselage uses metal shell and frame structure shape
Formula, interference of the external interference source to equipment, equipment compartment bag in the form of metal enclosed are shielded to greatest extent
Wrap up in, ensure that the stability of electrical part work, support uses frame structure, big while intensity is ensured
Amplitude alleviates body weight, 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 fuselage of full open type unmanned plane, it is characterised in that make what is formed including integral type
Metal shell, and the detachable cap installed in shell upper end open-mouth, outside the metal
Shell has the mounting plane with power arm installation.
2. the fuselage of full open type unmanned plane according to claim 1, it is characterised in that described outer
Metal framework is installed, the metal framework includes multiple main frames, and multiple main frames exist in shell
Frame center intersects, and outboard end is respectively directed to different directions, and the enclosure is divided into multiple areas
Domain, a body side frame is each connected respectively on two sides of the main frame；Each body side frame
One end be connected with a corresponding main frame, the other end is connected and shape with the inwall of the shell
Into three-legged structure.
3. the fuselage of full open type unmanned plane according to claim 2, it is characterised in that the master
Framework is rectangular frame, and the body side frame is U-frame frame.
4. the fuselage of full open type unmanned plane according to claim 3, it is characterised in that the shell
Lid is connected with metal framework by keeper.
5. the fuselage of full open type unmanned plane according to claim 4, it is characterised in that described outer
Shell is polygonized structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355488.9A CN107434028A (en) | 2016-05-25 | 2016-05-25 | A kind of fuselage of full open type unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610355488.9A CN107434028A (en) | 2016-05-25 | 2016-05-25 | A kind of fuselage of full open type unmanned plane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107434028A true CN107434028A (en) | 2017-12-05 |
Family
ID=60453320
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610355488.9A Pending CN107434028A (en) | 2016-05-25 | 2016-05-25 | A kind of fuselage of full open type unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107434028A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB127943A (en) * | 1918-06-03 | 1919-06-04 | Dermot Joseph Mooney | Improvements in the Construction of Fuselages and the like for Aviation. |
| CN102481972A (en) * | 2009-07-16 | 2012-05-30 | 空中客车德国运营有限责任公司 | Shell segment for producing a fuselage cell section for a fuselage cell of an airplane |
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| 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 |
| CN205770104U (en) * | 2016-05-25 | 2016-12-07 | 天津宏宇天翔科技有限公司 | A kind of fuselage of full open type unmanned plane |
-
2016
- 2016-05-25 CN CN201610355488.9A patent/CN107434028A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB127943A (en) * | 1918-06-03 | 1919-06-04 | Dermot Joseph Mooney | Improvements in the Construction of Fuselages and the like for Aviation. |
| CN102481972A (en) * | 2009-07-16 | 2012-05-30 | 空中客车德国运营有限责任公司 | Shell segment for producing a fuselage cell section for a fuselage cell of an airplane |
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
| US20160101850A1 (en) * | 2014-10-13 | 2016-04-14 | Che Min LIN | Multi-rotor frame structure |
| CN104401508A (en) * | 2014-10-27 | 2015-03-11 | 北京空间飞行器总体设计部 | Cross bracing main structure for spacecraft |
| CN204527629U (en) * | 2015-04-21 | 2015-08-05 | 刘亚敏 | A kind of four-axle aircraft with shell |
| CN205770104U (en) * | 2016-05-25 | 2016-12-07 | 天津宏宇天翔科技有限公司 | A kind of fuselage of full open type unmanned plane |
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| Date | Code | Title | Description |
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| 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 |