CN109849362A - A kind of unmanned plane winglet manufacturing method - Google Patents
A kind of unmanned plane winglet manufacturing method Download PDFInfo
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- CN109849362A CN109849362A CN201910029187.0A CN201910029187A CN109849362A CN 109849362 A CN109849362 A CN 109849362A CN 201910029187 A CN201910029187 A CN 201910029187A CN 109849362 A CN109849362 A CN 109849362A
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Abstract
The present invention discloses a kind of unmanned plane winglet manufacturing method, step 1: being stained with acetone soln with cleaning cloth will be upper, the inner cavity wiping of lower mold clears up and coats release agent, step 2: the surface of stabilization and rudder face is put into foaming agent, upper/lower die is molded, winglet mold is put into after high-temperature cabinet is heating and curing and is cooled to room temperature state, step 3: lower mold inner-cavity is filled up as stabilization foam and rudder face foam, step 4: wiping cleaning winglet mold again and smear release agent, step 5: in upper mold, lower mould inner surface spray-applied primer and finishing coat, step 6: steering engine installation site edge applies calomel mercurous chloride, step 7: being put into foam after mold cavity surfaces are laid with fabric, the clamping process of operating procedure 2 again, step 8: winglet mold being put into high-temperature cabinet and is heat-treated, step 9: be spirally connected peace at winglet mounting hole Fill steering engine and steering engine connecting rod.The beneficial effects of the present invention are: manufacturing cost is lower, the period is short, step is simple.
Description
Technical field
The present invention relates to unmanned plane manufacturing field more particularly to a kind of unmanned plane winglet manufacturing methods.
Background technique
In recent years, the temperature in China unmanned plane market is very high, there is very more applications in all trades and professions,
It is well known that aerodynamic arrangement is most important for the flying quality of unmanned plane, Flying-wing hinders ratio characteristic as a kind of rise higher
Aerodynamic arrangement is using relatively broad, and wherein winglet plays a kind of flight turning of the unmanned plane of Flying-wing extremely important
Effect, and unmanned plane enterprise is most between the rudder face and stabilization of winglet mold during manufacture winglet now
By paper hinge connection, skeleton is completed in such a way that milling foam is filled, and this method is relatively complicated, not only manufacturing time
Long, manufacturing cost is again very high.
Summary of the invention
In view of the above-mentioned problems, the present invention proposes a kind of unmanned plane winglet manufacturing method, background technique is mainly solved
Problem.
The present invention proposes a kind of unmanned plane winglet manufacturing method, triumphant using winglet mold, foaming agent, woven pattern preimpregnation
Husband draws fabric, woven pattern preimpregnation carbon fibre fabric, woven pattern preimpregnated glass fibre prepreg fabric, epoxy material priming paint, molding carbon
The composition such as silk and calomel mercurous chloride.
Step 1: winglet mold is divided into upper mold and lower mold, and when operation puts on gloves made of latex cleaning cloth and is stained with a small amount of third
Ketone solution is supreme with clean cloth smearing release agent difference after cleaning by the inner cavity of upper mold and the wiping cleaning of the inner cavity of lower mold
The inner cavity of the inner cavity of mold and lower mold；
Step 2: the inner cavity of the lower mold 1 is divided into stabilization and rudder face, in the table of the stabilization and rudder face of having smeared release agent
Face is put into the foaming agent of certain density, and upper mold and lower mold are passed through lower die positioning pin one, lower die positioning pin after being put into
Two and upper mold location hole one, two pairing of upper mold location hole, countersunk head hexagon socket head cap screw is passed through into upper mold countersunk head respectively and is installed
Kong Yi, upper mold counter sunk mounting holes two, upper mold counter sunk mounting holes three screw in lower mold bolt hole 1, lower mold bolt hole
Two, in lower mold bolt hole three, upper mold, lower mold are tightened into molding, entire inner cavity is in closed state, by entire winglet mould
Tool is put into high-temperature cabinet and is heating and curing, by natural aging treatment to room temperature state after being heating and curing；
Step 3: the winglet mold that will drop to room temperature, which is unscrewed equal fixing bolts by spanner, is beaten upper/lower die by pulling mouth 18
It opens, lower mold inner-cavity is filled up as stabilization foam and rudder face foam；
Step 4: after foam in cavity is taken away, reusing acetone and wipe cleaning winglet mold and smear release agent；
Step 5: in upper mold, lower mould inner surface spraying epoxy material priming paint and acroleic acid polyurethane face after cleaning winglet mold
Paint waits Qi Gan；
Step 6: after mould inner surface coating release agent, steering engine installation site edge applies calomel mercurous chloride, and preferably 3 layers of 3K presoak woven pattern
Carbon fibre fabric is paved on winglet mounting hole one by one, guarantees the rigidity of joint face, then by two layers of 1K high-strength braided line glass
The paved stabilization surface in upper mold and lower mold of fiber prepreg material, after wrapping up rudder face foam with one layer of 1K glass fabric
It is put into rudder face surface；
Step 7: the stabilization foam for distributing bubble being put into the mold for having spread prepreg fabric, one layer of Kevlar fabric is put into vertical
On wall, snap into the Kevlar fabric of half on stabilization foam, the other half Kevlar fabric snaps on rudder face foam, triumphant
Husband draws fabric to serve as the effect of hinge, to die slot adduction mould carbon filament, the clamping process of operating procedure 2 again；
Step 8: winglet mold being put into high-temperature cabinet or autoclave after stubborn bolt and is heat-treated, winglet mold is waited to be cooled to
Mold is struck with the hand by pulling mouth after room temperature；
Step 9: being spirally connected at winglet mounting hole and steering engine and steering engine connecting rod are installed.
Further improvement lies in that: the winglet mold is using the metal winglet mold that can bear 150 DEG C of high temperature, foaming agent
HR313 foaming agent.
Further improvement lies in that: the detailed process of the step 2 are as follows: entire winglet mold is put into 150 DEG C of high-temperature cabinet
It is heating and curing 2-3 hours.
Further improvement lies in that: Clean room operation of the whole operation of the step 5 in constant temperature and humidity.
Further improvement lies in that: the detailed process of the step 8 are as follows: winglet mold is put into high-temperature cabinet or autoclave,
It is heat-treated 3 hours at 120 DEG C.
The invention has the benefit that
1, the manufacture type chamber foam by way of with the closed metal die foaming that can bear 150 DEG C, it passes through milling with other
It is lower compared to the manufacturing cost of each winglet to cut foam filling skeleton.
2, the fixed position of steering engine is carried out on mold, is installed convenient for steering engine；
3, stabilization and the integrally formed mode of rudder face have the advantages that the manufacturing cycle is short, and safely, ensure that the accuracy of manufacture.
4, manufacturing step is simple, convenient for promoting.
Detailed description of the invention
Fig. 1 is plan view of the invention；
Fig. 2 is molding perspective view up and down of the invention.
Wherein: mold under 1-, die positioning pin one under 2-, 3- upper mold location hole one, 4- upper mold, 5- upper mold countersunk head
Mounting hole one, 6- upper mold location hole two, 7- upper mold counter sunk mounting holes two, 8- upper mold counter sunk mounting holes three, mold under 9-
Bolt hole three, mold bolt hole two under 10-, 11- winglet mounting hole, die positioning pin two under 12-, mold bolt hole one under 13-,
14- stabilization, 15- steering engine installation site, 16- rudder face, 17- indulge wall, and 18- pulls mouth.
Specific embodiment
In order to deepen the understanding of the present invention, the present invention is further described below in conjunction with embodiment, the present embodiment
For explaining only the invention, it is not intended to limit the scope of the present invention..
According to Fig. 1,2, the present embodiment proposes a kind of unmanned plane winglet manufacturing method, and use can bear 150
DEG C metal winglet mold, HR313 foaming agent, woven pattern preimpregnation Kevlar fabric, woven pattern preimpregnation carbon fibre fabric, woven pattern are pre-
Soak glass fibre prepreg fabric, epoxy resin, the molding composition such as carbon filament and calomel mercurous chloride.
Step 1: winglet mold is divided into upper mold 4 and lower mold 1, and when operation puts on gloves made of latex cleaning cloth and is stained on a small quantity
Release agent difference is smeared with clean cloth after cleaning in the inner cavity of upper mold 4 and the wiping cleaning of the inner cavity of lower mold 1 by acetone soln
To the inner cavity of upper mold 4 and the inner cavity of lower mold 1；
Step 2: the inner cavity of the lower mold 1 is divided into stabilization 14 and rudder face 16, in the stabilization 14 and rudder for having smeared release agent
The surface in face 16 is put into certain density HR313 foaming agent, and upper mold 4 and lower mold 1 are passed through lower die positioning pin one after being put into
2, lower die positioning pin 2 12 and upper mold location hole 1,26 pairing of upper mold location hole, countersunk head hexagon socket head cap screw is distinguished
Lower diebolt is screwed in by upper mold counter sunk mounting holes 1, upper mold counter sunk mounting holes 27, upper mold counter sunk mounting holes 38
Upper mold 4, lower mold 1 in lower mold bolt hole 39, are tightened molding, entire inner cavity by hole 1, lower mold bolt hole 2 10
In closed state, the high-temperature cabinet that entire winglet mold is put into 150 DEG C is heating and curing 2-3 hours；By certainly after being heating and curing
Right ageing treatment is to room temperature state；
Step 3: the winglet mold that will drop to room temperature, which is unscrewed equal fixing bolts by spanner, is beaten upper/lower die by pulling mouth 18
It opens, lower mold inner-cavity is filled up as stabilization foam and rudder face foam；
Step 4: after foam in cavity is taken away, reusing acetone and wipe cleaning winglet mold and smear release agent；
Step 5: in upper mold 4,1 inner surface of lower mold spraying epoxy material priming paint and acroleic acid polyurethane after cleaning winglet mold
Finishing coat waits Qi Gan, Clean room operation of the whole operation in constant temperature and humidity；
Step 6: after mould inner surface coating release agent, 15 edge of steering engine installation site applies calomel mercurous chloride, preferably 3 layers of 3K preimpregnation braiding
Line carbon fibre fabric is paved on winglet mounting hole 11 one by one, guarantees the rigidity of joint face, then by two layers of 1K high-strength braided line
Rudder is wrapped up with one layer of 1K glass fabric in paved 14 surface of stabilization in upper mold 4 and lower mold of glass fibre prepreg
16 surface of rudder face is put into after papula foam；
Step 7: the stabilization foam for distributing bubble being put into the mold for having spread prepreg fabric, one layer of Kevlar fabric is put into vertical
On wall 17, snap into the Kevlar fabric of half on stabilization foam, the other half Kevlar fabric snaps on rudder face foam,
Kevlar fabric serves as the effect of hinge, to die slot adduction mould carbon filament, the clamping process of operating procedure 2 again；
Step 8: winglet mold being put into high-temperature cabinet or autoclave after twisting bolt, is heat-treated 3 hours at 120 DEG C, is waited small
Wing mold by pulling mouth 18 strikes mold with the hand after being cooled to room temperature；
Step 9: being spirally connected at winglet mounting hole 11 and steering engine and steering engine connecting rod are installed.
Embodiment described above is only that embodiments of the present invention are described, not to design of the invention and
Range is defined.Without departing from the design concept of the invention, ordinary people in the field is to technical solution of the present invention
The all variations and modifications made should all drop into protection scope of the present invention.
Claims (6)
1. a kind of unmanned plane winglet manufacturing method, it is characterised in that: triumphant using winglet mold, foaming agent, woven pattern preimpregnation
Husband draws fabric, woven pattern preimpregnation carbon fibre fabric, woven pattern preimpregnated glass fibre prepreg fabric, epoxy material priming paint, molding carbon
The composition such as silk and calomel mercurous chloride.
2. step 1: winglet mold is divided into upper mold and lower mold, and when operation puts on gloves made of latex cleaning cloth and is stained with a small amount of acetone
Release agent is smeared respectively to upper mold with clean cloth after cleaning in the inner cavity of upper mold and the wiping cleaning of the inner cavity of lower mold by solution
The inner cavity of the inner cavity of tool and lower mold；
Step 2: the inner cavity of the lower mold is divided into stabilization and rudder face, on the surface of the stabilization and rudder face of having smeared release agent
It is put into the foaming agent of certain density, upper mold and lower mold are passed through into lower die positioning pin one, lower die positioning pin two after being put into
With upper mold location hole one, two pairing of upper mold location hole, countersunk head hexagon socket head cap screw is passed through into upper mold counter sunk mounting holes respectively
One, upper mold counter sunk mounting holes two, upper mold counter sunk mounting holes three screw in lower mold bolt hole one, lower mold bolt hole two, under
Upper mold, lower mold are tightened molding by diebolt Kong Sanzhong, and entire inner cavity is in closed state, and entire winglet mold is put
Enter high-temperature cabinet to be heating and curing, by natural aging treatment to room temperature state after being heating and curing；
Step 3: the winglet mold that will drop to room temperature, which is unscrewed equal fixing bolts by spanner, is opened upper/lower die by pulling mouth,
Lower mold inner-cavity is filled up as stabilization foam and rudder face foam；
Step 4: after foam in cavity is taken away, reusing acetone and wipe cleaning winglet mold and smear release agent；
Step 5: in upper mold, lower mould inner surface spraying epoxy material priming paint and acroleic acid polyurethane face after cleaning winglet mold
Paint waits Qi Gan；
Step 6: after mould inner surface coating release agent, steering engine installation site edge applies calomel mercurous chloride, and preferably 3 layers of 3K presoak woven pattern
Carbon fibre fabric is paved on winglet mounting hole one by one, guarantees the rigidity of joint face, then by two layers of 1K high-strength braided line glass
The paved stabilization surface in upper mold and lower mold of fiber prepreg material, after wrapping up rudder face foam with one layer of 1K glass fabric
It is put into rudder face surface；
Step 7: the stabilization foam for distributing bubble being put into the mold for having spread prepreg fabric, one layer of Kevlar fabric is put into vertical
On wall, snap into the Kevlar fabric of half on stabilization foam, the other half Kevlar fabric snaps on rudder face foam, triumphant
Husband draws fabric to serve as the effect of hinge, to die slot adduction mould carbon filament, the clamping process of operating procedure 2 again；
Step 8: winglet mold being put into high-temperature cabinet or autoclave after stubborn bolt and is heat-treated, winglet mold is waited to be cooled to
Mold is struck with the hand by pulling mouth after room temperature；
Step 9: being spirally connected at winglet mounting hole and steering engine and steering engine connecting rod are installed.
3. a kind of unmanned plane winglet manufacturing method as described in claim 1, it is characterised in that: the winglet mold uses
The metal winglet mold of 150 DEG C of high temperature can be born, foaming agent is HR313 foaming agent.
4. a kind of unmanned plane winglet manufacturing method as described in claim 1, it is characterised in that: the step 2 it is specific
Process are as follows: the high-temperature cabinet that entire winglet mold is put into 150 DEG C is heating and curing 2-3 hours.
5. a kind of unmanned plane winglet manufacturing method as described in claim 1, it is characterised in that: the step 5 it is entire
Operate the Clean room operation in constant temperature and humidity.
6. a kind of unmanned plane winglet manufacturing method as described in claim 1, it is characterised in that: the step 8 it is specific
Process are as follows: winglet mold is put into high-temperature cabinet or autoclave, is heat-treated 3 hours at 120 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201910029187.0A CN109849362A (en) | 2019-01-12 | 2019-01-12 | A kind of unmanned plane winglet manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910029187.0A CN109849362A (en) | 2019-01-12 | 2019-01-12 | A kind of unmanned plane winglet manufacturing method |
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| CN109849362A true CN109849362A (en) | 2019-06-07 |
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| CN201910029187.0A Pending CN109849362A (en) | 2019-01-12 | 2019-01-12 | A kind of unmanned plane winglet manufacturing method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112847986A (en) * | 2020-12-21 | 2021-05-28 | 中电科芜湖钻石飞机制造有限公司 | Primer transfer method, composite material part and preparation method thereof |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104626605A (en) * | 2014-12-16 | 2015-05-20 | 西安爱生技术集团公司 | Composite material wing integral molding technological method and composite material wing integral molding tool |
| US20160257427A1 (en) * | 2015-03-04 | 2016-09-08 | The Boeing Company | Co-curing process for the joining of composite structures |
| CN106182801A (en) * | 2016-07-15 | 2016-12-07 | 西北工业大学 | A kind of aircraft foam core filled composite material rudder face forming method |
| CN107738457A (en) * | 2017-11-02 | 2018-02-27 | 中广核俊尔新材料有限公司 | A kind of integrated forming technique of unmanned aerial vehicle body |
| CN108146652A (en) * | 2016-12-06 | 2018-06-12 | 成都凯迪精工科技有限责任公司 | A kind of aspect ratio is more than 9 times of rudder face manufacturing method |
| CN108995246A (en) * | 2018-06-20 | 2018-12-14 | 西北工业大学 | A kind of small-sized wing integrally forming mould and forming method based on VARTM |
| CN109016562A (en) * | 2018-07-12 | 2018-12-18 | 江苏新扬新材料股份有限公司 | A kind of preparation method of winglet |
-
2019
- 2019-01-12 CN CN201910029187.0A patent/CN109849362A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104626605A (en) * | 2014-12-16 | 2015-05-20 | 西安爱生技术集团公司 | Composite material wing integral molding technological method and composite material wing integral molding tool |
| US20160257427A1 (en) * | 2015-03-04 | 2016-09-08 | The Boeing Company | Co-curing process for the joining of composite structures |
| CN106182801A (en) * | 2016-07-15 | 2016-12-07 | 西北工业大学 | A kind of aircraft foam core filled composite material rudder face forming method |
| CN108146652A (en) * | 2016-12-06 | 2018-06-12 | 成都凯迪精工科技有限责任公司 | A kind of aspect ratio is more than 9 times of rudder face manufacturing method |
| CN107738457A (en) * | 2017-11-02 | 2018-02-27 | 中广核俊尔新材料有限公司 | A kind of integrated forming technique of unmanned aerial vehicle body |
| CN108995246A (en) * | 2018-06-20 | 2018-12-14 | 西北工业大学 | A kind of small-sized wing integrally forming mould and forming method based on VARTM |
| CN109016562A (en) * | 2018-07-12 | 2018-12-18 | 江苏新扬新材料股份有限公司 | A kind of preparation method of winglet |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112847986A (en) * | 2020-12-21 | 2021-05-28 | 中电科芜湖钻石飞机制造有限公司 | Primer transfer method, composite material part and preparation method thereof |
| CN112847986B (en) * | 2020-12-21 | 2023-02-21 | 中电科芜湖钻石飞机制造有限公司 | Primer transfer method, composite material part and preparation method thereof |
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Application publication date: 20190607 |
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