CN105563851A - Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) - Google Patents
Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) Download PDFInfo
- Publication number
- CN105563851A CN105563851A CN201610080723.6A CN201610080723A CN105563851A CN 105563851 A CN105563851 A CN 105563851A CN 201610080723 A CN201610080723 A CN 201610080723A CN 105563851 A CN105563851 A CN 105563851A
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- CN
- China
- Prior art keywords
- carbon fiber
- fiber prepreg
- moulding process
- aerial vehicle
- unmanned aerial
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/06—Fibrous reinforcements only
- B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
- B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
- B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/345—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using matched moulds
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
- B29L2031/3082—Fuselages
Abstract
The invention relates to a moulding process for a fuselage of a UAV (Unmanned Aerial Vehicle). The moulding process comprises the following steps: step 1, 1-2 layers of 3K carbon fiber prepregs are attached to a preheated moulding upper mould; then 2-4 layers of 30-50 DEG C 25-60g angle carbon fiber prepregs are attached; cutting is performed for trimming; step 2, 1-2 layers of 3K carbon fiber prepregs are attached to a preheated moulding lower mould; then 2-4 layers of 30-50 DEG C 25-60g carbon fiber prepregs are attached; an insert is arranged without trimming; the moulds are closed after a 3D air duct is arranged; step 3, moulding is performed on a hot press; the temperature is set to be 130-150 DEG C; the time is set to be 30-60 min; the pressure is set to be 3-6 MPa; and the internal pressure of the air duct is set to be 0.8-1.5 MPa; step 4, after moulding is finished, machining and carving are performed; and finally the final product is obtained after environment-friendly varnish is sprayed. According to the moulding process, very high strength can be obtained at any angle of the fuselage of the UAV through the layer placement design; and interlayer strength of the fuselage of the UAV is very high due to the mould pressing and the bag moulding technology of the moulding process, and internal assembly is ensured.
Description
Technical field
The present invention relates to a kind of moulding process and make mould, being specifically related to a kind of novel pouches pressure and mold pressing and combining method making high strength, carbon fiber unmanned aerial vehicle body that quality is light.
Background technology
The utilization of unmanned plane in life gets more and more, taking photo by plane, agricultural plant protection, the fields such as mapping progressively expand, the place of the life of people can be helped to get more and more, control the weight of unmanned aerial vehicle body and ensure enough intensity, it is the problem that the sector must be considered, but be subject to the restriction of the aspect such as cost and technology, most unmanned aerial vehicle body all following shortcomings of ubiquity on the market: material is heavier, bearing capacity is little, cause unmanned plane flying power lower, by fuselage insufficient strength during the affecting of environment, greatly reduce the space that unmanned plane uses, be lost the meaning of unmanned plane exploitation, a lot of inconvenience is brought to user.
Summary of the invention
For the problems referred to above, method making high strength that main purpose of the present invention is to provide a kind of novel pouches to press and mold pressing combines, the carbon fiber unmanned aerial vehicle body that quality is light.
The present invention solves above-mentioned technical problem by following technical proposals: a kind of moulding process of unmanned aerial vehicle body, and the moulding process of described unmanned aerial vehicle body comprises the following steps:
Step 1: in shaping upper after preheat, sticks 1 ~ 2 layer of 3K carbon fiber prepreg, then sticks 25 ~ 60g angle carbon fiber prepreg of layer 2-4 30 ~ 50 °, and edging eliminates;
Step 2: in shaping counterdie after preheat, sticks 1 ~ 2 layer of 3K carbon fiber prepreg, then sticks 25 ~ 60g carbon fiber prepreg of layer 2-4 30 ~ 50 °, without chamfered edge, puts into insert, installs 3D airduct, closed die;
Step 3: upper hot press is shaping, and temperature is set in 130 ~ 150 DEG C, and the time is set in 30 ~ 60min, pressure setting, at 3 ~ 6MPa, presses 0.8 ~ 1.5MPa in airduct;
Step 4: after shaping end, proceeds to machined engraving, finally sprays light environment-friendly type paint and obtains final products.
In specific embodiment of the present invention, described insert rolls up 5-8 layer 20 ~ 50 ° of angle carbon fiber prepreg in advance.
In specific embodiment of the present invention, described angle carbon fiber prepreg is eastern beautiful T700, grammes per square metre 25 ~ 60g, and resin is epoxy resin, content 25 ~ 35%.
In specific embodiment of the present invention, the angle carbon fiber prepreg in described step (1) is eastern beautiful T700, grammes per square metre 25 ~ 60g, and resin is epoxy resin, content 25 ~ 35%.
In specific embodiment of the present invention, the 3K carbon fiber prepreg in described step (2) is eastern beautiful T300, grammes per square metre 150 ~ 200g, and resin is epoxy resin, content 35 ~ 45%.
Positive progressive effect of the present invention is: the moulding process of unmanned aerial vehicle body provided by the invention has the following advantages: patent of the present invention compared with prior art has following beneficial effect: 1, make this unmanned aerial vehicle body can obtain very high intensity in all angles through Lay up design; 2, mold pressing and bag compression technology make unmanned aerial vehicle body interlaminar strength very high, ensure mounted inside; 3, hot press forming technology makes resin content very low, greatly alleviates the weight of unmanned aerial vehicle body; 4, exterior design is elegant in appearance, and applicability is strong, has good application prospect.
Accompanying drawing explanation
Fig. 1 is upper mould figure of the present invention.
Fig. 2 is lower mould figure of the present invention.
Fig. 3 is the schematic diagram front view of insert of the present invention.
Fig. 4 is the stereogram of the schematic diagram of insert of the present invention.
Fig. 5 is 3D airduct schematic diagram of the present invention.
Detailed description of the invention
Present pre-ferred embodiments is provided, to describe technical scheme of the present invention in detail below in conjunction with accompanying drawing.
Embodiment one: in shaping upper (as Fig. 1) after preheat, stick 1 layer of 3K carbon fiber prepreg, then stick the 27.5g angle carbon fiber prepreg of 2 layers 40 °, edging eliminates, secondly in shaping counterdie after preheat, stick 1 layer of 3K carbon fiber prepreg, stick the 27.5g carbon fiber prepreg of 2 layers 40 ° again, without chamfered edge, built-in insert is put in mold pressing district, insert rolls up 5 layers of 40 ° of angle carbon fiber prepreg in advance, again 3D airduct (Fig. 5) is put into an actor's rendering of an operatic tune according to the cavity shape of lower mould (as Fig. 2), six mouths of six corresponding moulds of mouth, put insert (as Fig. 3 and 4), be loaded on air charging inlet, last closed die, upper hot press is shaping, temperature is set in 130 DEG C, time is set in 40min, pressure setting is at 3MPa, pressure 0.8MPa in airduct, after shaping end, proceed to machined engraving, finally spray light environment-friendly type paint and obtain final products, final weight is 121.5g.
Embodiment two: in shaping upper (as Fig. 1) after preheat, stick 1 layer of 3K carbon fiber prepreg, then stick the 55g angle carbon fiber prepreg of 1 layer 45 °, edging eliminates, secondly in shaping counterdie after preheat, stick 1 layer of 3K carbon fiber prepreg, stick the 55g carbon fiber prepreg of 1 layer 45 ° again, without chamfered edge, built-in insert is put in mold pressing district, insert rolls up 5 layers of 45° angle degree carbon fiber prepreg in advance, again 3D airduct (Fig. 5) is put into an actor's rendering of an operatic tune according to the cavity shape of lower mould (as Fig. 2), six mouths of six corresponding moulds of mouth, put insert (as Fig. 3 and 4), be loaded on air charging inlet, last closed die, upper hot press is shaping, temperature is set in 135 DEG C, time is set in 35min, pressure setting is at 4MPa, pressure 0.9MPa in airduct, after shaping end, proceed to machined engraving, finally spray light environment-friendly type paint and obtain final products, final weight is 118g.
Embodiment three: in shaping upper (as Fig. 1) after preheat, stick 1 layer of 3K carbon fiber prepreg, then stick the 55g angle carbon fiber prepreg of 2 layers 45 °, edging eliminates, secondly in shaping counterdie after preheat, stick 1 layer of 3K carbon fiber prepreg, stick the 55g carbon fiber prepreg of 2 layers 45 ° again, without chamfered edge, built-in insert is put in mold pressing district, insert rolls up 5 layers of 45° angle degree carbon fiber prepreg in advance, again 3D airduct (Fig. 5) is put into an actor's rendering of an operatic tune according to the cavity shape of lower mould (as Fig. 2), six mouths of six corresponding moulds of mouth, put insert (as Fig. 3 and 4), be loaded on air charging inlet, last closed die, upper hot press is shaping, temperature is set in 145 DEG C, time is set in 30min, pressure setting is at 4MPa, pressure 1MPa in airduct, after shaping end, proceed to machined engraving, finally spray light environment-friendly type paint and obtain final products, final weight is 135.2g.
In above-mentioned three examples of implementation, angle carbon fiber prepreg is the material that eastern beautiful T700 or intensity are suitable, and grammes per square metre 25 ~ 60g, resin is epoxy resin, content 25 ~ 35%.
3K carbon fiber prepreg is the material that eastern beautiful T300 or intensity are suitable, and grammes per square metre 150 ~ 200g, resin is epoxy resin, content 35 ~ 45%.
More than show and describe general principle of the present invention and principal character and advantage of the present invention.The technical staff of the industry should understand; the present invention is not restricted to the described embodiments; what describe in above-described embodiment and description just illustrates principle of the present invention; without departing from the spirit and scope of the present invention; the present invention also has various changes and modifications; these changes and improvements all fall in the claimed scope of the invention, and application claims protection domain is defined by appending claims and equivalent thereof.
Claims (5)
1. a moulding process for unmanned aerial vehicle body, is characterized in that: the moulding process of described unmanned aerial vehicle body comprises the following steps:
Step 1: in shaping upper after preheat, sticks 1 ~ 2 layer of 3K carbon fiber prepreg, then sticks 25 ~ 60g angle carbon fiber prepreg of layer 2-4 30 ~ 50 °, and edging eliminates;
Step 2: in shaping counterdie after preheat, sticks 1 ~ 2 layer of 3K carbon fiber prepreg, then sticks 25 ~ 60g carbon fiber prepreg of layer 2-4 30 ~ 50 °, without chamfered edge, puts into insert, installs 3D airduct, closed die;
Step 3: upper hot press is shaping, and temperature is set in 130 ~ 150 DEG C, and the time is set in 30 ~ 60min, pressure setting, at 3 ~ 6MPa, presses 0.8 ~ 1.5MPa in airduct;
Step 4: after shaping end, proceeds to machined engraving, finally sprays light environment-friendly type paint and obtains final products.
2. the moulding process of unmanned aerial vehicle body according to claim 1, is characterized in that: described insert rolls up 5-8 layer 20 ~ 50 ° of angle carbon fiber prepreg in advance.
3. the moulding process of unmanned aerial vehicle body according to claim 2, is characterized in that: described angle carbon fiber prepreg is eastern beautiful T700, grammes per square metre 25 ~ 60g, and resin is epoxy resin, content 25 ~ 35%.
4. the moulding process of unmanned aerial vehicle body according to claim 1, is characterized in that: the angle carbon fiber prepreg in described step (1) is eastern beautiful T700, grammes per square metre 25 ~ 60g, and resin is epoxy resin, content 25 ~ 35%.
5. the moulding process of unmanned aerial vehicle body according to claim 1, is characterized in that: the 3K carbon fiber prepreg in described step (2) is eastern beautiful T300, grammes per square metre 150 ~ 200g, and resin is epoxy resin, content 35 ~ 45%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610080723.6A CN105563851A (en) | 2016-02-04 | 2016-02-04 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610080723.6A CN105563851A (en) | 2016-02-04 | 2016-02-04 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
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| Publication Number | Publication Date |
|---|---|
| CN105563851A true CN105563851A (en) | 2016-05-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610080723.6A Pending CN105563851A (en) | 2016-02-04 | 2016-02-04 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
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| CN (1) | CN105563851A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275375A (en) * | 2016-10-17 | 2017-01-04 | 中航通飞华南飞机工业有限公司 | Four axle unmanned plane main body and manufacture methods of integration molding |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
| CN109501060A (en) * | 2018-12-07 | 2019-03-22 | 北京航空航天大学 | For making the method and mold of unmanned aerial vehicle body shell |
| CN109703056A (en) * | 2018-12-04 | 2019-05-03 | 深圳市科卫泰实业发展有限公司 | A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft |
| CN111002603A (en) * | 2019-12-12 | 2020-04-14 | 江苏亨睿碳纤维科技有限公司 | Manufacturing method of integrally formed automobile rear wing |
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| CN103935042A (en) * | 2013-01-23 | 2014-07-23 | 佛山市安尔康姆航拍科技有限公司 | Manufacturing method for hollow rotor of unmanned aerial vehicle and hollow rotor |
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2016
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| CN1058168A (en) * | 1990-07-02 | 1992-01-29 | 胡迪森产品公司 | Make the method for fan blade |
| CN103935042A (en) * | 2013-01-23 | 2014-07-23 | 佛山市安尔康姆航拍科技有限公司 | Manufacturing method for hollow rotor of unmanned aerial vehicle and hollow rotor |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106275375A (en) * | 2016-10-17 | 2017-01-04 | 中航通飞华南飞机工业有限公司 | Four axle unmanned plane main body and manufacture methods of integration molding |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
| CN109703056A (en) * | 2018-12-04 | 2019-05-03 | 深圳市科卫泰实业发展有限公司 | A kind of production method of the sandwich sandwich structure device hatchcover of multi-rotor aerocraft |
| CN109501060A (en) * | 2018-12-07 | 2019-03-22 | 北京航空航天大学 | For making the method and mold of unmanned aerial vehicle body shell |
| CN111002603A (en) * | 2019-12-12 | 2020-04-14 | 江苏亨睿碳纤维科技有限公司 | Manufacturing method of integrally formed automobile rear wing |
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| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| CB02 | Change of applicant information |
Address after: 201306 Shanghai, Nanhui, new town, Hong Kong Road, No. 1758, A - room 1, room Applicant after: Shanghai Jin Feixin Polytron Technologies Inc. Address before: 201306 Shanghai, Nanhui, new town, Hong Kong Road, No. 1758, A - room 1, room Applicant before: SHANGHAI CEDAR COMPOSITES TECHNOLOGY CO. LTD. |
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| CB02 | Change of applicant information | ||
| CI02 | Correction of invention patent application |
Correction item: Applicant|Address Correct: Shanghai Jin Fei Polytron Technologies Inc.|201306 A 1 - 503, No. 1758, Lu Chao Gang Road, new town, Nanhui, Pudong New Area, Shanghai False: Shanghai Jin Feixin Polytron Technologies Inc.|201306 A 1 - 503, No. 1758, Lu Chao Gang Road, new town, Nanhui, Pudong New Area, Shanghai Number: 15 Volume: 33 |
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| CI02 | Correction of invention patent application | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20160511 |
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| RJ01 | Rejection of invention patent application after publication |