CN109016562A - A kind of preparation method of winglet - Google Patents
A kind of preparation method of winglet Download PDFInfo
- Publication number
- CN109016562A CN109016562A CN201810762989.8A CN201810762989A CN109016562A CN 109016562 A CN109016562 A CN 109016562A CN 201810762989 A CN201810762989 A CN 201810762989A CN 109016562 A CN109016562 A CN 109016562A
- Authority
- CN
- China
- Prior art keywords
- foam
- prepreg
- winglet
- die cavity
- mold
- 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.)
- Granted
Links
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
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
- B29C70/542—Placing or positioning the reinforcement in a covering or packaging element before or during moulding, e.g. drawing in a sleeve
-
- 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
- B29L2031/3085—Wings
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a kind of preparation methods of winglet in technical field of aerospace, the mold used includes the falsework with die cavity, there is working face identical with winglet shape on the falsework, working face is in die cavity, winglet can be just fitted on working face, in the longitudinal direction, the side of working face is placed with several limited blocks one, the other side of working face is equipped with limited block two, limited block one and limited block two are detachably connected with falsework, limited block one and limited block two are used to the position of fixed foam, falsework on the outside of die cavity is equipped with positioning mould, positioning mould is equipped with the positioning rank for positioning finished product surplus, winglet is prepared to include the following steps, (1) Foam machining；(2) foam dehumidifies；(3) splicing of foam；(4) prepreg blanking；(5) preparation of mold；(6) prepreg paving；(7) solidify；(8) it demoulds；(9) post-production；Preparation cost of the invention is low, winglet light weight.
Description
Technical field
The invention belongs to pressed-disc technique field, in particular to a kind of preparation method of winglet.
Background technique
Awing, the higher-pressure region air-flow of wing lower aerofoil can flow to top airfoil around wingtip to aircraft, form strong rotation
Vortex air flow, and along stretching very long a distance after slave flapwise, they have taken away energy, increase induced drag, and winglet
Exactly it is used to slacken this resistance.
When air-flow flows through two surfaces up and down of wing, generated draught head can generate upward lift in wing,
When this power is greater than the weight of aircraft, aircraft just can fly on high.But the at this moment higher-pressure region air-flow meeting of wing lower surface
Flow to top airfoil around wingtip, form strong swirling air stream, when aircraft fly it is faster, it is generated vortex it is also stronger, in this way
It will increase the consumption of the resistance and fuel when flight.
Tip vortex is readjusted in the design for installing winglet additional, hinders the air of upper and lower surface to stream, to reduce whirlpool
The intensity of stream effectively reduces resistance and fuel consumption when flight, and its angle can also generate simultaneously upwardly and forwardly
Component increase the thrust and lift of aircraft.
Currently, the winglet that large-scale pulvis uses is metal structure, the winglet weight manufactured is big, aircraft
Oil consumption increases, and manufacturing cost is high, and the flexibility of flight is poor.
Summary of the invention
For the defects in the prior art, it is an object of the invention to overcome the deficiencies in the prior art described above place, solution
The technical problem that the product weight certainly manufactured in the prior art is big, manufacturing cost is high provides a kind of preparation of winglet
Method, manufacturing cost of the invention is low, and the winglet weight manufactured using the present invention is low, reduces aircraft oil consumption.
The object of the present invention is achieved like this: a kind of preparation method of winglet prepares the mould that winglet uses
Tool includes the falsework with die cavity, has working face identical with winglet shape on the falsework, working face is in mould
Intracavitary, winglet can be just fitted on working face, and in the longitudinal direction, the side of working face is placed with several limited blocks
One, the other side of working face is equipped with limited block two, and limited block one and limited block two are detachably connected with falsework, limited block
One and limited block two be used to the position of fixed foam, the falsework on the outside of die cavity is equipped with positioning mould, and positioning mould is equipped with and is used for
The positioning rank for positioning finished product surplus, prepares winglet and includes the following steps,
(1) Foam machining: foam one and foam two are processed according to product model, one end of foam one can be with one end of foam two
It fits together；
(2) foam dehumidify: the foam processed is wrapped up using airfelt, is put into baking oven, 120 DEG C drying 2 hours, with removing
The moisture that foam surface absorbs, dries the foam core finished and takes out from baking oven, is put into the polybag of sealing and stores with spare；
(3) splicing of foam: one layer of epoxy construction glue film is respectively pasted into one end that foam one and foam two can fit together, will be steeped
The splicing of foam one faces the splicing face of quasi- foam two, to be glued together foam one and foam two, the foam that will be glued together
One and foam two be placed on the working face of falsework, limited block one and limited block two be installed, fixed foam one and foam two
Position pastes vacuum bag on mold and wraps foam one and foam two, vacuum bag is evacuated to vacuum, and mold feeding baking oven is consolidated
Change, be cooled to room temperature after the completion of solidification, take out mold, open vacuum bag, foam one and foam two after solidifying is taken out, after solidification
Foam one and foam two in hereafter referred to collectively as foam core；
(4) prepreg blanking: simulating the shape of each layer of blanking figure using three-dimensional artificial software, enables its shape bedding in winglet
Outer surface keeps the tablet deflection during laying minimum, blanking figure is imported into the operating system of automatic blanking machine, will be pre-
Leaching material is put on automatic blanking machine bracket, according to the every block piece of program tailoring, and with label paper identifier number；
(5) preparation of mold: cleaning mold inner-cavity residue has been cleared up after residue using clean strap dipping acetone to mould
Tool inner cavity is wiped, and the residue for influencing product is washed, and wipes mold inner-cavity with clean strap dip striping compound after drying,
Release agent wipes release agent again after drying, repeat to wipe again after being spaced 15 minutes between wiping release agent 5 times, every twice, wipe
After complete last time release agent, mold is sent into oven drying, dries and is taken out after being cooled to room temperature spare；
(6) prepreg paving: according to ply stacking-sequence, by the working face in prepreg paving to die cavity, the area of prepreg
Greater than the area of die cavity, the part beyond die cavity is successively separated using isolation film, until all prepreg pavings are completed, will be limited
Position block one and limited block two are installed on mold, and after wrapping up one layer of epoxy construction glue film outside foam core, foam core is put into paving
It posts in the die cavity of prepreg, turns over prepreg, prepreg is made to wrap foam core；
(7) solidify: pasting vacuum bag outside die cavity, prepreg is compacted on the surface of foam core, by mould by bag vacuum
Tool is sent into baking oven, is solidified according to curing process；
(8) it demoulds: after solidification, closing baking oven, after mold temperature is cooled to room temperature, takes out mold, remove preliminary product；
(9) post-production: the positioning rank in control positioning mould obtains into after cutting the outside surplus of positioning rank using cutting machine
Product.
Preparation cost of the invention is low, and the winglet light weight prepared, specific strength is big, and specific modulus is high, and performance is steady
It is fixed；It can be applied in the work for preparing unmanned plane winglet.
In order to further increase the anti-bending strength of winglet, in the step (6), laying method is specifically, by step (4)
In cut out four layers of prepreg alignment position line, successively paving is on working face, first layer prepreg to the 4th layer of prepreg
Laying angle be followed successively by: 45 °, 0 °, -45 °, 90 °, during paving, part use of the non-paving of prepreg on mold every
Successively keep apart from film, after the completion of first layer paving, in die cavity outer package vacuum bag, vacuum bag is evacuated to vacuum, utilizes vacuum
Pressure compaction prepreg, keep vacuum 15min, remove vacuum bag, continue next layer of paving, after the completion of whole pavings,
Vacuum bag is evacuated to vacuum by die cavity outer package vacuum bag, and vacuum all prepregs of pressure compaction keep each layer prepreg tight
Closely connected conjunction vacuumizes compacting 4h.
It is further comprising the steps of in the step (6): in foam wicking surface in order to improve the compactness of glue film and foam core
After wrapping up one layer of epoxy construction glue film, in foam core outer package vacuum bag, Vacuumizing bag to vacuum makes glue film compacting in foam table
Face removes vacuum bag after vacuum debulk.
It is further comprising the steps of in the step (6): foam core is placed in order to realize the laying of foam surface prepreg
On prepreg in die cavity, position is adjusted, agrees with foam with die cavity；The non-paving of prepreg is layer-by-layer to cavity surface part
It separates, removes isolation film, turn to foam upper surface, the entire foam of bedding, in prepreg pleated portions separate process from small nose of wing
Clip, every layer of clip position are arranged in a staggered manner, and method completes all prepreg pavings according to this.
As a further improvement of the present invention, the solidification temperature in the step (3) is 130 DEG C, curing time 2h.
As a further improvement of the present invention, in the step (7), solidification temperature is 125 DEG C, curing time 2h.
Detailed description of the invention
Fig. 1 is the three-dimensional structure diagram of mold in the present invention.
Fig. 2 is the three-dimensional structure diagram of mold when the foam one being glued together in the present invention and foam two are placed in die cavity.
Fig. 3 is the structural schematic diagram of winglet in the present invention.
Wherein, 1 falsework, 2 positioning moulds, 3 die cavitys, 4 limited blocks one, 5 limited blocks two, 6 working faces.
Specific embodiment
Invention is further explained with reference to the accompanying drawing.
A kind of preparation method of winglet as shown in FIG. 1 to 3, in this implementation, for convenience of description, area is big
It is foam one, area is small for foam two；Preparing the mold that winglet uses includes the falsework 1 with die cavity 3, work
There is working face 6 identical with winglet shape, for working face 6 in die cavity 3, winglet can just be fitted in work on frame 1
Make on face 6, in the longitudinal direction, the side of working face 6 is placed with several limited blocks 1, and the other side of working face 6 is equipped with limit
Block 25, limited block 1 and limited block 25 are detachably connected with falsework 1, and limited block 1 and limited block 25 are used to admittedly
Determine the position of foam, the falsework 1 in 3 outside of die cavity is equipped with positioning mould 2, and positioning mould 2 is equipped with for positioning finished product surplus
Rank is positioned, winglet is prepared and includes the following steps,
(1) Foam machining: processing two foams according to product model, (in this implementation, for convenience of description, area is greatly
Foam one, area are small for foam two), one end of foam one can fit together with one end of foam two；
(2) foam dehumidify: the foam processed is wrapped up using airfelt, is put into baking oven, 120 DEG C drying 2 hours, with removing
The moisture that foam surface absorbs, dries the foam core finished and takes out from baking oven, is put into the polybag of sealing and stores with spare；
(3) splicing of foam: one layer of epoxy construction glue film is respectively pasted into one end that foam one and foam two can fit together, will be steeped
The splicing of foam one faces the splicing face of quasi- foam two, to be glued together foam one and foam two, the foam that will be glued together
One and foam two be placed on the working face 6 of falsework 1, limited block 1 and limited block 25, fixed foam one and foam are installed
Two position pastes vacuum bag on mold and wraps foam one and foam two, vacuum bag is evacuated to vacuum, and mold is sent into and is dried
Case solidification, solidification temperature are 130 DEG C, curing time 2h, are cooled to room temperature after the completion of solidification, take out mold, open vacuum bag,
The foam one and foam two after solidifying are taken out, the foam one and foam two after solidification are in hereafter referred to collectively as foam core；
(4) prepreg blanking: simulating the shape of each layer of blanking figure using three-dimensional artificial software, enables its shape bedding in winglet
Outer surface keeps the tablet deflection during laying minimum, blanking figure is imported into the operating system of automatic blanking machine, will be pre-
Leaching material is put on automatic blanking machine bracket, according to the every block piece of program tailoring, and with label paper identifier number；
(5) preparation of mold: cleaning mold inner-cavity residue has been cleared up after residue using clean strap dipping acetone to mould
Tool inner cavity is wiped, and the residue for influencing product is washed, and wipes mold inner-cavity with clean strap dip striping compound after drying,
Release agent wipes release agent again after drying, repeat to wipe again after being spaced 15 minutes between wiping release agent 5 times, every twice, wipe
After complete last time release agent, mold is sent into oven drying, dries and is taken out after being cooled to room temperature spare；
(6) prepreg paving: according to ply stacking-sequence, by prepreg paving to the working face 6 in die cavity 3, the face of prepreg
Product is greater than the area of die cavity 3, and the part beyond die cavity 3 is successively separated using isolation film, until all prepreg pavings are completed,
Limited block 1 and limited block 25 are installed on mold, after wrapping up one layer of epoxy construction glue film outside foam core, by foam core
It is put into the die cavity 3 for being affixed with prepreg, turns over prepreg, prepreg is made to wrap foam core；
(7) solidify: pasting vacuum bag outside die cavity 3, prepreg is compacted on the surface of foam core, by mould by bag vacuum
Tool is sent into baking oven, is solidified according to curing process, wherein solidification temperature is 125 DEG C, curing time 2h；
(8) it demoulds: after solidification, closing baking oven, after mold temperature is cooled to room temperature, takes out mold, remove preliminary product；
(9) post-production: the positioning rank in control positioning mould 2 obtains into after cutting the outside surplus of positioning rank using cutting machine
Product.
In order to further increase the anti-bending strength of winglet, in step (6), laying method is specifically that will cut in step (4)
The four layers of prepreg alignment position line cut out, successively paving is on working face 6, the paving of first layer prepreg to the 4th layer of prepreg
Layer angle is successively are as follows: 45 °, 0 °, -45 °, 90 °, during paving, part of the non-paving of prepreg on mold uses isolation film
Successively keep apart, after the completion of first layer paving, in 3 outer package vacuum bag of die cavity, vacuum bag is evacuated to vacuum, vacuum pressure
Real prepreg is forced, vacuum 15min is kept, removes vacuum bag, continues next layer of paving, after the completion of whole pavings, in die cavity 3
Vacuum bag is evacuated to vacuum by outer package vacuum bag, and vacuum all prepregs of pressure compaction paste each layer prepreg closely
It closes, vacuumizes compacting 4h.
It is further comprising the steps of in step (6) in order to improve the compactness of glue film and foam core: to be wrapped up in foam wicking surface
After one layer of epoxy construction glue film, in foam core outer package vacuum bag, Vacuumizing bag to vacuum makes glue film compacting in foam surface, very
Vacuum bag is removed after pneumatics reality.
It is further comprising the steps of in step (6): foam core is placed on mould in order to realize the laying of foam surface prepreg
On prepreg in chamber 3, position is adjusted, agrees with foam with die cavity 3；The non-paving of prepreg is layer-by-layer to 3 surface portion of die cavity
It separates, removes isolation film, turn to foam upper surface, the entire foam of bedding, in prepreg pleated portions separate process from small nose of wing
Clip, every layer of clip position are arranged in a staggered manner, and method completes all prepreg pavings according to this.
Prepreg in the present embodiment is combined by 3233 epoxy resin and EW180B glass fabric, after solidification
Composite material can be become, 3233 epoxy resin are intermediate temperature setting epoxy resin, and maximum operation (service) temperature is 70 DEG C, can satisfy the wing
The use environment of tip winglet, EW180B glass fabric is plain cloth, at low cost, and performance is stablized；The power of composite material
It is as shown in table 1 to learn performance.
1 3233/EW180B composite materials property of table
In the present embodiment, foam preferably uses Polymethacrylimide (PMI) foam, and PMI foamed heat-resistance performance is good, thermal deformation
Temperature is high, being capable of curing molding integrated with prepreg；Specific strength, specific modulus are highest in foamed material；Compression creep
Can be good, it can adapt to composite pressure molding；Fire protecting performance is good；It is good with various resin compatibles；Light weight.
Preparation cost of the invention is low, and the winglet light weight prepared, specific strength is big, and specific modulus is high, and performance is steady
It is fixed；It can be applied in the work for preparing unmanned plane winglet.
The present invention is not limited to the above embodiments, on the basis of technical solution disclosed by the invention, the skill of this field
For art personnel according to disclosed technology contents, one can be made to some of which technical characteristic by not needing creative labor
A little replacements and deformation, these replacements and deformation all fall in the scope of protection of the present invention.
Claims (6)
1. a kind of preparation method of winglet, which is characterized in that preparing the mold that winglet uses includes having die cavity
Falsework has working face identical with winglet shape on the falsework, and for working face in die cavity, winglet can be rigid
It is fitted on working face well, in the longitudinal direction, the side of working face is placed with several limited blocks one, and the other side of working face is set
There is limited block two, limited block one and limited block two are detachably connected with falsework, and limited block one and limited block two are used to admittedly
Determine the position of foam, the falsework on the outside of die cavity is equipped with positioning mould, and positioning mould is equipped with the positioning for positioning finished product surplus
Rank prepares winglet and includes the following steps,
(1) Foam machining: foam one and foam two are processed according to product model, one end of foam one can be with one end of foam two
It fits together；
(2) foam dehumidify: the foam processed is wrapped up using airfelt, is put into baking oven, 120 DEG C drying 2 hours, with removing
The moisture that foam surface absorbs, dries the foam core finished and takes out from baking oven, is put into the polybag of sealing and stores with spare；
(3) splicing of foam: one layer of epoxy construction glue film is respectively pasted into one end that foam one and foam two can fit together, will be steeped
The splicing of foam one faces the splicing face of quasi- foam two, to be glued together foam one and foam two, the foam that will be glued together
One and foam two be placed on the working face of falsework, limited block one and limited block two be installed, fixed foam one and foam two
Position pastes vacuum bag on mold and wraps foam one and foam two, vacuum bag is evacuated to vacuum, and mold feeding baking oven is consolidated
Change, be cooled to room temperature after the completion of solidification, take out mold, open vacuum bag, foam one and foam two after solidifying is taken out, after solidification
Foam one and foam two in hereafter referred to collectively as foam core；
(4) prepreg blanking: simulating the shape of each layer of blanking figure using three-dimensional artificial software, enables its shape bedding in winglet
Outer surface keeps the tablet deflection during laying minimum, blanking figure is imported into the operating system of automatic blanking machine, will be pre-
Leaching material is put on automatic blanking machine bracket, according to the every block piece of program tailoring, and with label paper identifier number；
(5) preparation of mold: cleaning mold inner-cavity residue has been cleared up after residue using clean strap dipping acetone to mould
Tool inner cavity is wiped, and the residue for influencing product is washed, and wipes mold inner-cavity with clean strap dip striping compound after drying,
Release agent wipes release agent again after drying, repeat to wipe again after being spaced 15 minutes between wiping release agent 5 times, every twice, wipe
After complete last time release agent, mold is sent into oven drying, dries and is taken out after being cooled to room temperature spare；
(6) prepreg paving: according to ply stacking-sequence, by the working face in prepreg paving to die cavity, the area of prepreg
Greater than the area of die cavity, the part beyond die cavity is successively separated using isolation film, until all prepreg pavings are completed, will be limited
Position block one and limited block two are installed on mold, and after wrapping up one layer of epoxy construction glue film outside foam core, foam core is put into paving
It posts in the die cavity of prepreg, turns over prepreg, prepreg is made to wrap foam core；
(7) solidify: pasting vacuum bag outside die cavity, prepreg is compacted on the surface of foam core, by mould by bag vacuum
Tool is sent into baking oven, is solidified according to curing process；
(8) it demoulds: after solidification, closing baking oven, after mold temperature is cooled to room temperature, takes out mold, remove preliminary product；
(9) post-production: the positioning rank in control positioning mould obtains into after cutting the outside surplus of positioning rank using cutting machine
Product.
2. a kind of preparation method of winglet according to claim 1, which is characterized in that in the step (6), laying
Method is specifically that the four layers of prepreg cut out in step (4) are directed at position line, and successively paving is on working face, first
The laying angle of layer prepreg to the 4th layer of prepreg is followed successively by: 45 °, 0 °, -45 °, 90 °, during paving, prepreg is not spread
The part being attached on mold is successively kept apart using isolation film,, will be true in die cavity outer package vacuum bag after the completion of first layer paving
Empty bag is evacuated to vacuum, and vacuum pressure compaction prepreg keeps vacuum 15min, removes vacuum bag, continues next layer of paving
Vacuum bag after the completion of whole pavings, in die cavity outer package vacuum bag, is evacuated to vacuum, vacuum pressure compaction is all by patch
Prepreg fits closely each layer prepreg, vacuumizes compacting 4h；
Wherein, with the exhibition of winglet to for 0 °, 45 ° of laying angle are the exhibition along winglet to the angle after rotating counterclockwise 45 °, are spread
90 ° of angle of layer are, to the angle after rotating counterclockwise 90 °, -45 ° of laying angle is along the Zhan Xiangshun of winglet along the exhibition of winglet
Hour hands rotate the angle after 45 °.
3. a kind of preparation method of winglet according to claim 1, which is characterized in that also wrapped in the step (6)
Include following steps: after foam wicking surface wraps up one layer of epoxy construction glue film, in foam core outer package vacuum bag, Vacuumizing bag is extremely
Vacuum makes glue film compacting remove vacuum bag after foam surface, vacuum debulk.
4. a kind of preparation method of winglet according to claim 1, which is characterized in that also wrapped in the step (6)
It includes following steps: foam core is placed on the prepreg in die cavity, adjust position, agree with foam with die cavity；By prepreg
Non- paving is successively separated to cavity surface part, is removed isolation film, is turned to foam upper surface from small nose of wing, bedding entirely steeps
Foam, in prepreg pleated portions separate process clip, every layer of clip position is arranged in a staggered manner, and method is complete by all prepreg pavings according to this
At.
5. a kind of preparation method of winglet according to any one of claims 1 to 4, which is characterized in that the step
(3) solidification temperature in is 130 DEG C, curing time 2h.
6. a kind of preparation method of winglet according to any one of claims 1 to 4, which is characterized in that the step
Suddenly in (7), solidification temperature is 125 DEG C, curing time 2h.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810762989.8A CN109016562B (en) | 2018-07-12 | 2018-07-12 | Preparation method of wingtip winglet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810762989.8A CN109016562B (en) | 2018-07-12 | 2018-07-12 | Preparation method of wingtip winglet |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109016562A true CN109016562A (en) | 2018-12-18 |
| CN109016562B CN109016562B (en) | 2021-04-23 |
Family
ID=64641096
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810762989.8A Active CN109016562B (en) | 2018-07-12 | 2018-07-12 | Preparation method of wingtip winglet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109016562B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109849362A (en) * | 2019-01-12 | 2019-06-07 | 航天神舟飞行器有限公司 | A kind of unmanned plane winglet manufacturing method |
| CN112743869A (en) * | 2020-12-18 | 2021-05-04 | 珠海市海斯比船舶工程有限公司 | Hull construction method adopting prepreg |
| CN114311741A (en) * | 2021-12-14 | 2022-04-12 | 常州市新创智能科技有限公司 | Method and die for preforming composite material window frame |
| CN114654635A (en) * | 2021-12-24 | 2022-06-24 | 平高集团有限公司 | Method for improving surface smoothness of epoxy casting product |
| CN115071157A (en) * | 2022-06-24 | 2022-09-20 | 江苏恒铭达航空设备有限公司 | Aviation composite winglet assembly forming process |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106985413A (en) * | 2017-04-13 | 2017-07-28 | 中航复合材料有限责任公司 | A kind of forming frock for foam core filled composite material structure winglet |
-
2018
- 2018-07-12 CN CN201810762989.8A patent/CN109016562B/en active Active
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106985413A (en) * | 2017-04-13 | 2017-07-28 | 中航复合材料有限责任公司 | A kind of forming frock for foam core filled composite material structure winglet |
Non-Patent Citations (1)
| Title |
|---|
| 成艳娜，刘向阳: "某型飞机PMI泡沫夹层结构翼梢小翼成型技术研究", 《粘接》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109849362A (en) * | 2019-01-12 | 2019-06-07 | 航天神舟飞行器有限公司 | A kind of unmanned plane winglet manufacturing method |
| CN112743869A (en) * | 2020-12-18 | 2021-05-04 | 珠海市海斯比船舶工程有限公司 | Hull construction method adopting prepreg |
| CN114311741A (en) * | 2021-12-14 | 2022-04-12 | 常州市新创智能科技有限公司 | Method and die for preforming composite material window frame |
| CN114311741B (en) * | 2021-12-14 | 2022-10-18 | 常州市新创智能科技有限公司 | Method and die for preforming composite material window frame |
| CN114654635A (en) * | 2021-12-24 | 2022-06-24 | 平高集团有限公司 | Method for improving surface smoothness of epoxy casting product |
| CN115071157A (en) * | 2022-06-24 | 2022-09-20 | 江苏恒铭达航空设备有限公司 | Aviation composite winglet assembly forming process |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109016562B (en) | 2021-04-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109016562A (en) | A kind of preparation method of winglet | |
| CN103407175B (en) | A kind of integral forming method of fiber-reinforced resin matrix compound material wing box | |
| CN105904740B (en) | A kind of integral manufacturing method of composite material light continuous fiber grid | |
| CN103407173B (en) | A kind of integral forming method of fiber-reinforced resin matrix compound material wing | |
| CN108407332B (en) | Compression molding method for composite material grid skin structural part | |
| CN110193955B (en) | Process forming method for composite outer wing of small and medium-sized unmanned aerial vehicle | |
| CN105216345B (en) | RTM global formation orthogonal stiffenerses structure member (cover)s and its manufacture method | |
| CN106827587B (en) | The forming method of application and its wing of the HSM technique in wing molding | |
| EP3093121A1 (en) | Aircraft component with closed box structure | |
| CN106828967A (en) | Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method | |
| CN108891040B (en) | Manufacturing method of composite horizontal tail wing of small and medium-sized unmanned aerial vehicle | |
| EP2723554A2 (en) | Tool for manufacturing a preform assembly | |
| CN103057126A (en) | Large-scale composite material integral molding blade and molding process thereof | |
| CN105034403A (en) | Method for manufacturing composite shell | |
| CN109203510A (en) | A kind of preparation method of joint flange | |
| CN108638538A (en) | A kind of simple composite material grid product forming method | |
| CN110193956A (en) | A kind of small drone composite material vertical tail moulding technique | |
| CN103231464A (en) | Honeycomb preforming method for large-curvature composite material interlayer piece | |
| CN103935042B (en) | The manufacture method of the hollow rotor of unmanned vehicle and hollow rotor | |
| CN109866496A (en) | A kind of frequency selects the preparation method of radome exemplar | |
| CN109551789A (en) | A kind of preparation method that stickup angle is supported with polyurethane of blade of MW class wind turbine | |
| CN109049753B (en) | Preparation method of heat-resistant nose cone | |
| CN109016571B (en) | Preparation method of airfoil | |
| CN105673358B (en) | A kind of large size trailing edge segmentation pneumatic equipment bladess connection structure and manufacture craft | |
| CN111055517B (en) | XPS extruded sheet inner core and epoxy resin composite material glider wing and preparation method thereof |
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 | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |