CN113120253A - Integrated processing technology for carbon fiber casing of unmanned aerial vehicle - Google Patents
Integrated processing technology for carbon fiber casing of unmanned aerial vehicle Download PDFInfo
- Publication number
- CN113120253A CN113120253A CN201911415699.7A CN201911415699A CN113120253A CN 113120253 A CN113120253 A CN 113120253A CN 201911415699 A CN201911415699 A CN 201911415699A CN 113120253 A CN113120253 A CN 113120253A
- Authority
- CN
- China
- Prior art keywords
- carbon fiber
- air bag
- silicon rubber
- rubber air
- aerial vehicle
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- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
-
- 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
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Transportation (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses an integrated processing technology of an unmanned aerial vehicle carbon fiber casing, which comprises the following steps: (1) modeling an unmanned aerial vehicle shell; (2) preparing an upper die, a lower die and a silicon rubber air bag; (3) inflating the silicon rubber air bag; (4) coating demolding wax; (5) laying carbon fiber cloth on the outer surface of the silicon rubber air bag, and coating resin on the carbon fiber cloth; (6) repeating the step (3) for a plurality of times; (7) placing the silicon rubber air bag into the lower die, and vertically combining the upper die and the lower die and fixing the upper die and the lower die through a fixture; (8) the silicon rubber air bag is inflated for the second time; (9) the silicon rubber air bag is deflated after being cured at normal temperature; (10) and taking out the silicon rubber air bag and the formed carbon fiber shell. The integrated processing technology for the carbon fiber casing of the unmanned aerial vehicle, provided by the invention, is simple to operate, no demolding wax is needed during demolding of the silicon rubber air bag, the technology is simple, the processing cost is low, the strength and the toughness are higher, the prepared casing is integrally formed, the strength is higher, and the weight is lighter.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicle shell machining, in particular to an integrated machining process for an unmanned aerial vehicle carbon fiber shell.
Background
An unmanned plane, called unmanned plane for short, is a new concept aircraft in rapid development, and has the characteristics of flexibility, high reaction speed, no need of manual driving, low operation requirement, capability of carrying various small-sized devices or articles and the like, so that the unmanned plane is widely applied at present, the application range of the unmanned plane is expanded to various fields of civil use, scientific research, even military use, national defense and the like, particularly the unmanned plane is widely applied in the aspects of power communication, weather, agriculture, ocean, exploration, photography, disaster prevention and reduction, drug and smudge enforcement, border patrol, security and counter terrorism and the like, the functions of real-time image transmission and real-time field detection in high-risk areas are powerful supplements to satellite remote sensing and traditional aerial remote sensing, the existing unmanned plane shell is manufactured by separately manufacturing the upper part and the lower part of the shell in the production process and then is bonded, the strength is lower and the unmanned plane is not beautiful, and the weight of casing can be increased in the bonding process, has both increased manufacturing cost, has also reduced unmanned aerial vehicle flight time.
Disclosure of Invention
The invention aims to solve the problems and provides an integrated processing technology of an unmanned aerial vehicle carbon fiber casing.
In order to achieve the purpose, the invention adopts the following technical scheme:
the integrated processing technology for the carbon fiber shell of the unmanned aerial vehicle comprises the following steps:
(1) modeling an unmanned aerial vehicle shell, and deriving a processing drawing;
(2) preparing an upper die and a lower die which can be folded up and down according to the processing drawing in the step (1), preparing a silicon rubber air bag which can be inflated according to the shape and the size of an inner cavity of the unmanned aerial vehicle shell, wherein an inflation/deflation port is arranged at the top of the silicon rubber air bag;
(3) inflating the silicon rubber air bag, wherein the inflation pressure is 0.4-0.6 Mpa;
(4) coating demolding wax in the upper mold and the lower mold;
(5) carbon fiber cloth is laid on the outer surface of the silicon rubber air bag, and resin is uniformly coated on the outer surface of the carbon fiber cloth, so that the carbon fiber cloth is ensured to be uniformly soaked by the resin;
(6) repeating the operation step of the step (3) for multiple times to enable the outer surface of the silicon rubber air bag to be coated with multiple layers of the carbon fiber cloth;
(7) placing the silicon rubber air bag into the lower die, and vertically combining the upper die and the lower die and fixing the upper die and the lower die through a fixture;
(8) the silicone rubber air bag is inflated for the second time, and the inflation pressure is 2-2.5 Mpa;
(9) curing at normal temperature for 24 hours, and deflating the silicon rubber air bag through the inflation/deflation port after the curing is finished;
(10) taking out the silicon rubber air bag, separating the upper die and the lower die and taking out the formed carbon fiber shell;
(11) removing redundant burrs at the edge of the carbon fiber shell, and cleaning the carbon fiber unmanned aerial vehicle shell by using wax removing water;
(12) carbon fiber unmanned aerial vehicle casing surface sprays paint the stoving back casing and obtains carbon fiber unmanned aerial vehicle casing finished product.
Furthermore, the upper die and the lower die are made of one of metal and glass fiber reinforced plastic.
Furthermore, in the step (4), the number of layers and the thickness of the carbon fiber cloth which meet the requirements of drawings and process design are required according to the stress direction of the unmanned aerial vehicle shell.
The invention has the beneficial effects that: the method has the advantages of simple operation, no need of demoulding wax during demoulding of the silicon rubber air bag, simple process, low processing cost, higher strength and toughness, longer service life, integrated forming of the prepared casing, higher strength and lighter weight.
Detailed Description
The following examples are presented to enable those skilled in the art to more fully understand the present invention and are not intended to limit the invention in any way.
The integrated processing technology for the carbon fiber shell of the unmanned aerial vehicle comprises the following steps:
(1) modeling an unmanned aerial vehicle shell, and deriving a processing drawing;
(2) preparing an upper die and a lower die which are made of metal materials and can be folded up and down according to the processing drawing in the step (1), preparing a silicon rubber air bag which can be inflated according to the shape and the size of an inner cavity of the unmanned aerial vehicle shell, wherein an inflation/deflation port is formed in the top of the silicon rubber air bag;
(3) inflating the silicon rubber air bag, wherein the inflation pressure is 0.5 Mpa;
(4) coating demolding wax in the upper mold and the lower mold;
(5) carbon fiber cloth is laid on the outer surface of the silicon rubber air bag, and resin is uniformly coated on the outer surface of the carbon fiber cloth, so that the carbon fiber cloth is ensured to be uniformly soaked by the resin;
(6) repeating the operation step of the step (3) for multiple times to enable the outer surface of the silicon rubber air bag to be coated with multiple layers of the carbon fiber cloth, wherein the number and the thickness of the carbon fiber cloth meet the drawing and process design requirements according to the stress direction of the unmanned aerial vehicle shell in the operation process;
(7) placing the silicon rubber air bag into the lower die, and vertically combining the upper die and the lower die and fixing the upper die and the lower die through a fixture;
(8) the silicon rubber air bag is inflated for the second time, and the inflation pressure is 2.5 Mpa;
(9) curing at normal temperature for 24 hours, and deflating the silicon rubber air bag through the inflation/deflation port after the curing is finished;
(10) taking out the silicon rubber air bag, separating the upper die and the lower die and taking out the formed carbon fiber shell;
(11) removing redundant burrs at the edge of the carbon fiber shell, and cleaning the carbon fiber unmanned aerial vehicle shell by using wax removing water;
(12) carbon fiber unmanned aerial vehicle casing surface sprays paint the stoving back casing and obtains carbon fiber unmanned aerial vehicle casing finished product.
Those skilled in the art will appreciate that the above embodiments are merely exemplary embodiments and that various changes, substitutions, and alterations can be made without departing from the spirit and scope of the invention.
Claims (3)
1. The integrated processing technology for the carbon fiber shell of the unmanned aerial vehicle is characterized by comprising the following steps of:
(1) modeling an unmanned aerial vehicle shell, and deriving a processing drawing;
(2) preparing an upper die and a lower die which can be folded up and down according to the processing drawing in the step (1), preparing a silicon rubber air bag which can be inflated according to the shape and the size of an inner cavity of the unmanned aerial vehicle shell, wherein an inflation/deflation port is arranged at the top of the silicon rubber air bag;
(3) inflating the silicon rubber air bag, wherein the inflation pressure is 0.4-0.6 Mpa;
(4) coating demolding wax in the upper mold and the lower mold;
(5) carbon fiber cloth is laid on the outer surface of the silicon rubber air bag, and resin is uniformly coated on the outer surface of the carbon fiber cloth, so that the carbon fiber cloth is ensured to be uniformly soaked by the resin;
(6) repeating the operation step of the step (3) for multiple times to enable the outer surface of the silicon rubber air bag to be coated with multiple layers of the carbon fiber cloth;
(7) placing the silicon rubber air bag into the lower die, and vertically combining the upper die and the lower die and fixing the upper die and the lower die through a fixture;
(8) the silicone rubber air bag is inflated for the second time, and the inflation pressure is 2-2.5 Mpa;
(9) curing at normal temperature for 24 hours, and deflating the silicon rubber air bag through the inflation/deflation port after the curing is finished;
(10) taking out the silicon rubber air bag, separating the upper die and the lower die and taking out the formed carbon fiber shell;
(11) removing redundant burrs at the edge of the carbon fiber shell, and cleaning the carbon fiber unmanned aerial vehicle shell by using wax removing water;
(12) carbon fiber unmanned aerial vehicle casing surface sprays paint the stoving back casing and obtains carbon fiber unmanned aerial vehicle casing finished product.
2. The integrated processing technology of the carbon fiber casing of the unmanned aerial vehicle as claimed in claim 1, wherein the upper die and the lower die are made of one of metal and glass fiber reinforced plastic.
3. The integrated processing technology for the carbon fiber shell of the unmanned aerial vehicle as claimed in claim 1, wherein in the step (4), the number of layers and the thickness of the carbon fiber cloth meeting the requirements of drawings and process design are achieved according to the stress direction of the shell of the unmanned aerial vehicle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911415699.7A CN113120253A (en) | 2019-12-31 | 2019-12-31 | Integrated processing technology for carbon fiber casing of unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911415699.7A CN113120253A (en) | 2019-12-31 | 2019-12-31 | Integrated processing technology for carbon fiber casing of unmanned aerial vehicle |
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| Publication Number | Publication Date |
|---|---|
| CN113120253A true CN113120253A (en) | 2021-07-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201911415699.7A Pending CN113120253A (en) | 2019-12-31 | 2019-12-31 | Integrated processing technology for carbon fiber casing of unmanned aerial vehicle |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113681865A (en) * | 2021-08-19 | 2021-11-23 | 深圳碳吉科技有限公司 | Integrally formed guitar and production process thereof |
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| CN86105307A (en) * | 1985-08-22 | 1987-04-01 | 布德公司 | Hollow fiber reinforced structure and preparation method thereof |
| JP2003181935A (en) * | 2001-12-20 | 2003-07-03 | Fuji Heavy Ind Ltd | Method for manufacturing structure having closed space |
| US20030156944A1 (en) * | 2002-02-20 | 2003-08-21 | Jim Rust | Composite propeller blade with unitary metal ferrule and method of manufacture |
| US20040043196A1 (en) * | 2002-08-30 | 2004-03-04 | Willden Kurtis S. | Forming method for composites |
| US20080290214A1 (en) * | 2007-05-24 | 2008-11-27 | Guzman Juan C | Shaped composite stringers and methods of making |
| CN103407173A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integrally-forming method of wing made of fiber reinforced resin matrix composites |
| CN105523165A (en) * | 2016-01-29 | 2016-04-27 | 上海翔鸿无人飞行器导航控制技术有限公司 | Integrally molded unmanned aerial vehicle carbon fiber arm and preparation method thereof |
| CN110193957A (en) * | 2019-07-03 | 2019-09-03 | 西安爱生技术集团公司 | A kind of small drone composite aileron moulding technique |
| US20190315451A1 (en) * | 2018-04-17 | 2019-10-17 | Ratier-Figeac Sas | Propeller blade spar |
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2019
- 2019-12-31 CN CN201911415699.7A patent/CN113120253A/en active Pending
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| JP2003181935A (en) * | 2001-12-20 | 2003-07-03 | Fuji Heavy Ind Ltd | Method for manufacturing structure having closed space |
| US20030156944A1 (en) * | 2002-02-20 | 2003-08-21 | Jim Rust | Composite propeller blade with unitary metal ferrule and method of manufacture |
| US20040043196A1 (en) * | 2002-08-30 | 2004-03-04 | Willden Kurtis S. | Forming method for composites |
| US20080290214A1 (en) * | 2007-05-24 | 2008-11-27 | Guzman Juan C | Shaped composite stringers and methods of making |
| CN103407173A (en) * | 2013-07-30 | 2013-11-27 | 北京航空航天大学 | Integrally-forming method of wing made of fiber reinforced resin matrix composites |
| CN105523165A (en) * | 2016-01-29 | 2016-04-27 | 上海翔鸿无人飞行器导航控制技术有限公司 | Integrally molded unmanned aerial vehicle carbon fiber arm and preparation method thereof |
| US20190315451A1 (en) * | 2018-04-17 | 2019-10-17 | Ratier-Figeac Sas | Propeller blade spar |
| CN110193957A (en) * | 2019-07-03 | 2019-09-03 | 西安爱生技术集团公司 | A kind of small drone composite aileron moulding technique |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113681865A (en) * | 2021-08-19 | 2021-11-23 | 深圳碳吉科技有限公司 | Integrally formed guitar and production process thereof |
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Application publication date: 20210716 |