CN108177360A - The forming frock and its forming method of unmanned plane composite wing integral panel - Google Patents
The forming frock and its forming method of unmanned plane composite wing integral panel Download PDFInfo
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- CN108177360A CN108177360A CN201711419393.XA CN201711419393A CN108177360A CN 108177360 A CN108177360 A CN 108177360A CN 201711419393 A CN201711419393 A CN 201711419393A CN 108177360 A CN108177360 A CN 108177360A
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- 239000002131 composite material Substances 0.000 title claims description 39
- 238000000465 moulding Methods 0.000 claims abstract description 31
- 229920001971 elastomer Polymers 0.000 claims abstract description 9
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- 230000000875 corresponding Effects 0.000 claims abstract description 3
- 238000003754 machining Methods 0.000 claims abstract description 3
- 239000000835 fiber Substances 0.000 claims description 37
- 229920002379 silicone rubber Polymers 0.000 claims description 11
- 238000004519 manufacturing process Methods 0.000 claims description 9
- 230000015572 biosynthetic process Effects 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 238000005755 formation reaction Methods 0.000 claims description 4
- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- 239000004760 aramid Substances 0.000 claims description 3
- 229920003235 aromatic polyamide Polymers 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- 238000003786 synthesis reaction Methods 0.000 claims 1
- 230000002194 synthesizing Effects 0.000 claims 1
- 239000002023 wood Substances 0.000 claims 1
- 239000000463 material Substances 0.000 abstract description 6
- 238000010586 diagram Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000005260 corrosion Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 235000013399 edible fruits Nutrition 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive Effects 0.000 description 1
- 239000000789 fastener Substances 0.000 description 1
- 239000000295 fuel oil Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 101710031899 moon Proteins 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 229920000260 silastic Polymers 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/20—Opening, closing or clamping
- B29C33/202—Clamping means operating on closed or nearly closed mould parts, the clamping means being independently movable of the opening or closing means
-
- 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
- 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
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2083/00—Use of polymers having silicon, with or without sulfur, nitrogen, oxygen, or carbon only, in the main chain, as moulding material
-
- 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
Abstract
The invention discloses a kind of unmanned planes to answer material Integral Wing Panel forming frock and its forming method,Integral panel includes covering and twin I-beam,Forming frock includes covering forming mold,I-beam mold for forming and clamping positioning mechanism,Covering forming includes former with mold,Former is formed according to covering outer surface Machining of Curved Surface,I-beam mold for forming monnolithic case contour surface is identical with covering inner surface,It is split to form left and right mold at the web of I-beam that need to be molded,Left and right mold respectively close to one end of I-beam web be provided with thickness be 5 10mm with type silicane rubber plate,Silicane rubber plate length is equal with I-beam die length,Corresponding I-shaped beam mould upper and lower surface above and below respective I-beam edge strip at flange is formed with the depth groove identical with flange thickness above and below I-beam,Clamping positioning mechanism is clamped positioning to I-beam molding from covering front and rear edge both sides with assembling die respectively.The present invention makes integral panel with being integrally formed.
Description
Technical field
The invention belongs to composite processing manufacturing field more particularly to a kind of short range unmanned plane composite wing are whole
The forming frock and its forming method of siding.
Background technology
In recent years, deeply rocket has been widely used in it with the development of technology, composite material with application study, has flown
The military fields such as machine.Composite material under conditions of product strength is ensured, can significantly reduce the construction weight of various products, and
This further means that automobile, aircraft etc. the consumption for reducing fuel oil, has achieved the purpose that energy-saving and emission-reduction, therefore, composite material
It also has broad application prospects in the military-civil field such as automobile, train, aviation.In addition, composite material parts can significantly subtract
Few connector simplifies the manufacturing process of parts.Composite wing integral panel can effectively reduce parts and fastener,
Mitigate wing structure weight, improve the reliability and durability of aircraft.
Composite Panels part as primary load bearing, it is desirable that the laying position of structure, angle are accurate, the ruler of constituent element
Very little and position degree is accurate, only in this way effectively could carry and transmit load.Traditional offhand technique processing siding class
Part often will appear inside parts quality problems, the situations such as composition element morpheme size deviation, part quality stability difference.
The composite structure of global formation is the important measures of the aircraft loss of weight such as unmanned plane and a kind of method for reducing cost.
Invention content
It is whole that first of the present invention is designed to provide a kind of composite wing with the advantages of light-weight, intensity is high
The forming frock of body wall plate；Second object of the present invention is to provide a kind of manufacturer of above-mentioned composite material integral panel
Method, the manufacturing method of the present invention step is simple, easy to operate, and production efficiency is high, reduces cost.
The forming frock of the unmanned plane composite wing integral panel of the present invention manufactures unmanned plane for being integrally formed ground
Composite wing integral panel, the integral panel include what is holded up on the covering and covering identical with wing side surface shape
Twin I-beam, forming frock include covering forming mold, I-beam mold for forming and clamping positioning mechanism, the covering into
Type includes former with mold, and former is formed according to covering outer surface Machining of Curved Surface, the I-beam mold for forming monnolithic case
Contour surface is identical with covering inner surface, need to be molded at the web of I-beam to be split to form left and right mold, left and right mold
Length it is identical with needing the length of molding I-beam, left and right mold is respectively provided with thickness close to one end of I-beam web and is
5-10mm with type silicane rubber plate, silicane rubber plate length is equal with I-beam die length, is turned over above and below respective I-beam edge strip
Corresponding I-shaped beam mould upper and lower surface at side is formed with the depth groove identical with flange thickness above and below I-beam, works as I-shaped
When beam is multiple, intermediate auxiliary mold, the clamping and positioning machine are installed between adjacent two I-beam mold for forming
Structure is divided into leading edge clamping positioning mechanism and rear clamping positioning mechanism, respectively from covering front and rear edge to the I-beam forming mould
Tool is clamped positioning.
It is preferred that the I-beam is included along the extension of wing length direction, the in the width direction front and rear preceding I-beam being arranged in parallel
With rear I-beam, for the preceding I-beam than rear I-shaped beam length, it is left that the I-beam mold for forming includes preceding I-beam molding
Right mould tool, rear I-beam molding left and right grinding tool and intermediate auxiliary mold, the intermediate auxiliary are located at preceding I-beam with mold
Right mould has between rear I-beam left mould tool.
It is preferred that the clamping positioning mechanism includes withstanding tight block, adjusting bolt and loose piece, the loose piece of leading edge clamping positioning mechanism
In the groove set in covering former edge wall with type groove, configuration with I-shaped beam mould leading edge shape before cooperation,
The loose piece of rear side clamping positioning mechanism have I-shaped beam mould rear shape after cooperation with type groove, be configured in covering former
In the groove set on rear wall, adjusting bolt respectively spiral shell into the screw thread for the withstanding tight block being fixed on covering former front-rear side walls
Hole, bolt end are withstood on respectively on the wall with groove opposite side of front and rear edge loose piece, and mold is clamped to adjust loose piece.
It is preferred that there are one the rear side clamping positioning mechanism configurations, positioned at the substantially intermediate of the rear I-beam configuring area
Position, the front side clamping positioning mechanism has configuration two, is pressed from both sides positioned at the preceding I-beam configuring area, and positioned at the rear side
The both sides of tight detent mechanism.
It is preferred that the left and right mold is made with intermediate auxiliary with die main body of aluminium alloy.
The forming method of the unmanned plane composite material integral panel of the present invention utilizes any in above-mentioned five technical solutions
The forming frock manufacture integral panel of unmanned plane composite material integral panel described in, including Step 1: by least one
High-performance fiber is centainly sequentially coated with by certain number of plies in the spill groove bottom wall of covering forming mold cavity block；Step 2:
The high-performance fibre is wrapped up according to the mode that is coated with of step 1 in the silicane rubber plate end of the left and right mold of I-beam mold for forming
Dimension, the high-performance fiber on mould ends side are used to form I-beam web, the high-performance fiber on surface above and below mold
It is used to form I-beam edge strip flange；Step 3: the left and right mold of I-beam mold for forming high-performance fiber is sticked into
End pairing, carry out R angle fillings in the upper and lower end parts of apposition position, i.e., be twisted into pairing using high-performance fiber with fiber type item
The upper and lower side R angles at place are filled and led up, then whole above the high-performance fiber of the flange formation on left and right mold respectively upper and lower surface
Body is coated with high-performance fiber, forms I-beam flange up and down；Step 4: by each left and right mold and intermediate auxiliary mold pair
Synthesize the curve form of wing cover；It is laid with Step 5: being placed on the I-beam mold for forming after pairing by step 1
In the covering forming mold of good high-performance fiber, and the clamping positioning mechanism for adjusting both sides is compressed；Step 6: in step
Five upper surface for being placed with I-beam mold for forming is laid with a layer thickness as 5-10mm silicon rubber, covers formpiston, and molding is twisted
It is next to be put into baking oven, cured by cure profile；Step 7: being demoulded after the completion of curing, it is whole to obtain composite wing
Body wall plate.
It is preferred that the high-performance fiber is any one or a few in carbon fiber, glass fibers, aramid fiber.
The present invention has the advantages that：
(1) a kind of short range unmanned plane composite wing integral panel of the invention has that light-weight, intensity is high, resistance to tired
The advantages that labor, corrosion-resistant, shock resistance.Since autoclave molding curing can not used, equipment cost, assembly cost are greatly reduced
Also it is further to reduce；
(2) a kind of short range unmanned plane composite wing integral panel manufacturing method step of the invention is simple, using one
Body chemical conversion type manufactures, easy to operate, is molded accurate positioning, is not assembled by being glued, welding or be mechanically connected, with traditional integral panel
Compared to connector is significantly reduced, integral panel parts are simplified, reduce equipment and assembly cost, alleviate weight, increased
The strong structural strength of composite wing integral panel effectively improves the reliability of composite wing；
(3) solidifying pressure is transmitted using silastic material, silicon rubber has excellent high-temperature oxidation, can meet
Most of intermediate temperature setting composite materials moulding process requirement, in addition its can arbitrary figuration, be suitable for use as complex-shaped product
Compound auxiliary mould (metal positive+silicane rubber plate), and the characteristic expanded with heat and contract with cold after product molding due to silicon rubber, demoulding effect
Fruit is good；
(4) I-beam assembled tool carries clamping positioning mechanism, makes I-beam web uniform force, I-beam integrated positioning
Accurately.
Description of the drawings
Fig. 1 is the structure diagram of unmanned plane composite wing integral panel of the present invention.
Fig. 2 is assembling schematic diagram of the forming frock of the present invention before formpiston is covered.
Fig. 3 (1) (2) is rear side I-beam molding left and right mold butt-joint process schematic diagram.
Fig. 4 is the scheme of installation of clamping positioning mechanism.
Fig. 5 is molding schematic diagram.
Specific implementation
In the following, highly preferred embodiment of the present invention is illustrated with reference to the accompanying drawings.Heading when being installed in text with wing
To come to define front-rear direction, and above-mentioned front direction is defined as left side on airfoil cross-section (Fig. 2).
As shown in Figure 1, the novel short range unmanned plane composite wing integral panel I of the present invention includes covering 1, preceding I-shaped
Beam 2 and rear I-beam 3, preceding I-beam 2 and rear I-beam 3 are along configured in parallel before and after wing width direction, and preceding I-beam 2 is than rear work
Word beam 3 is grown.Integral panel is made of composite material, the high-performance fiber prepreg that the composite material uses, be carbon fiber,
At least one of fibers such as glass fibre, aramid fiber can be homogenous material, can be the group of two or more material
It closes, the present embodiment preferentially using carbon fiber prepreg, has the advantages of light-weight, intensity is high.The integral panel is light-weight, strong
Degree is high, it is often more important that it can carry higher load as main force support structure.
As shown in Figure 2-5, the forming frock of integral panel I includes the former 4 of covering forming, molding mold 11, preceding work
Word beam molding die 5 and 6, rear I-beam molding die 7 and 8, I-beam auxiliary positioning mold 9 and clamping positioning mechanism clamp
Detent mechanism includes withstanding tight block 12, adjusting bolt 13 and loose piece 14.
Former 4 and molding mold 11 are provided with baltimore groove, former 4 and conjunction according to wing cover side surface curve respectively
Mould mold 11 can be formed altogether Integral Wing Panel molding cavity, preceding I-beam molding die 5 and 6, rear I-beam into
Pattern has the monnolithic case contour curve and wing outer profile curve identical of 7 and 8 and the composition of I-beam auxiliary positioning mold 9, after
The web of I-beam 3 is configured at rear 3 both sides of I-beam for boundary after I-beam molding die 7 and 8, respective close to I-beam
One end of 3 webs is respectively arranged with the silicon rubber 10 that thickness is 5-10mm, and above and below respective I-beam at flange formation
Be formed with the depth groove identical with upper and lower flange thickness in upper and lower surface, preceding I-beam molding die 5 and 6 and rear I-beam into
Pattern has the configuration of 7 and 8 same ways, and the web of former I-beam 2 is configured at preceding 2 both sides of I-beam for boundary, in respective patch
One end of 2 web of nearly I-beam is provided with the silicon rubber end that thickness is 5-10mm, and the flange shape above and below respective I-beam
The depth groove identical with upper and lower flange thickness is formed on into the upper and lower surface at place.
In rear side setting there are one clamping positioning mechanism, positioned at the substantially intermediate position of rear I-beam configuring area, rear side
Loose piece 14 there is the groove of 8 rear shape of cooperation I-shaped beam mould, the groove set on covering former rear wall is configured
In, into the threaded hole of withstanding tight block 12 being fixed on cavity block rear wall, the end of adjusting bolt 13 is withstood on 13 spiral shell of adjusting bolt
On the wall with groove opposite side of the loose piece 14 of rear side.Front side clamping positioning mechanism is configured two, I-beam configuration before being respectively positioned on
Region, and two front side clamping positioning mechanisms are distributed in the both sides of rear side clamping positioning mechanism.Two loose pieces 14 of front side are equal
Groove with 5 leading edge shape of I-shaped beam mould before cooperation, and distribute two grooves put and set on covering cavity block front side wall
In, two adjusting bolts 13 respectively spiral shell into the threaded hole of two withstanding tight blocks 2 being fixed on cavity block front side wall, two adjusting bolts
13 end is withstood on respectively on the wall with groove opposite side of two loose pieces of front side.By screwing the adjusting bolt 13 of both sides,
The loose piece 14 of front and rear sides can be made to be slided in respective groove, so as to adjust it to combining rear I-beam shaping mould
The pressing force of tool.
I-beam mold for forming 5-8 and auxiliary mould 9 are aluminium alloy main body.
It first has to get out the required main material of integral panel manufacture using above-mentioned forming frock manufacture integral panel
And auxiliary material；Covering former 4, I-beam formpiston 5-8 and 9 surface of auxiliary mould are cleaned, and release agent application；Then
It is manufactured according to following sequences.
1st, at least one high-performance fiber is centainly sequentially coated with by certain number of plies in covering forming mold cavity block 4
In spill groove bottom wall；
2nd, at the end of preceding I-beam molding die 5 and 6, the respectively close I-beam web of rear I-beam molding die 7 and 8
Portion is laid with the silicon rubber 10 that a layer thickness is 5-10mm, according to silicon rubber 10 of the package mode of step 1 at I-beam web
Outer surface and preceding I-beam molding die 5 and 6, the upper and lower surface of rear I-beam molding die 7 and 8 be integrally rolled into c-type
High-performance fiber；
3rd, the preceding I-beam molding die 5 and 6 for being coated with high-performance fiber respectively come with into 10 one side pairing of silicon rubber, incited somebody to action
The rear I-beam molding die 7 and 8 for being coated with high-performance fiber respectively comes with 10 one side pairing of silicon rubber, c-type centre position
High-performance fiber is used to form the web of I-beam, and the high-performance fiber of upper and lower both sides is used to form the flange on the upside of I-beam
With the sleeping side of downside.
4th, it is carried out in the upper and lower end parts of preceding I-beam molding die 5 and 6,7 and 8 respective apposition position of rear I-beam molding die
R angles are filled, i.e., are filled and led up the upper and lower side R angles of apposition position using the high-performance fiber being twisted into type shape, then above and below respectively
The high-performance fiber entire surface that flange on surface or sleeping side are formed is coated with high-performance fiber, formed each I-beam flange and
Sleeping side；
5th, according to 5,6,9,7,8 sequence by each die assembly together, and be placed on the moon for laying high-performance fiber
In mould 4, both sides adjustment bolt 13 is adjusted, the mold combined is clamped using the loose piece 14 of both sides；
6th, a layer thickness is laid in the upper surface for placing 5,6,9,7,8 molds as 5-10mm silicon rubber, covers molding mold
11, molding is put into baking oven after tightening, and is cured by cure profile；
7th, it is demoulded after the completion of curing, obtains composite wing integral panel.
The present invention short range unmanned plane composite wing integral panel have it is light-weight, intensity is high, endurance, corrosion resistant
The advantages that erosion, shock resistance, it is often more important that integral panel I its can be used as the higher load of load-carrying construction carrying.
Claims (7)
1. a kind of forming frock of unmanned plane composite wing integral panel for being integrally formed manufactures unmanned plane composite wood
Expect Integral Wing Panel, which includes the duplexing word holded up on the covering and covering identical with wing side surface shape
Beam, it is characterised in that：The forming frock includes covering forming mold, I-beam mold for forming and clamping positioning mechanism,
The covering forming includes former with mold, and former is formed according to covering outer surface Machining of Curved Surface, the I-beam forming mould
It is identical with covering inner surface to have monnolithic case contour surface, is split to form left and right mould at the web of I-beam that need to be molded
Tool, the length of left and right mold is identical with needing the length of molding I-beam, and left and right mold is respectively close to one end of I-beam web
Be provided with thickness be 5-10mm with type silicane rubber plate, silicane rubber plate length is equal with I-beam die length, in respective I-shaped
Corresponding I-shaped beam mould upper and lower surface above and below beam edge strip at flange is formed with depth, and flange thickness is identical up and down with I-beam
Groove, when I-beam is multiple, intermediate auxiliary mold, institute are installed between adjacent two I-beam mold for forming
It states clamping positioning mechanism and is divided into leading edge clamping positioning mechanism and rear clamping positioning mechanism, respectively from covering front and rear edge to the work
Word beam mold for forming is clamped positioning.
2. the forming frock of unmanned plane composite material integral panel according to claim 1, it is characterised in that：The I-shaped
Beam is included along the extension of wing length direction, the in the width direction front and rear preceding I-beam being arranged in parallel and rear I-beam, the preceding work
Word beam is than rear I-shaped beam length, and the I-beam mold for forming includes preceding I-beam molding left and right mold, rear I-beam is molded
With left and right grinding tool and intermediate auxiliary mold, intermediate auxiliary mold is located at preceding I-beam left mould tool and rear I-beam right mould
Between tool.
3. the forming frock of unmanned plane composite material integral panel according to claim 2, it is characterised in that：The clamping
Detent mechanism includes withstanding tight block, adjusting bolt and loose piece, and the loose piece of leading edge clamping positioning mechanism has I-shaped beam mould before cooperation
In the groove set in covering former edge wall with type groove, configuration of leading edge shape, the work of rear side clamping positioning mechanism
Block has the groove set on covering former rear wall with type groove, configuration of I-shaped beam mould rear shape after cooperation
In, into the threaded hole for the withstanding tight block being fixed on covering former front-rear side walls, bolt end withstands on spiral shell adjusting bolt respectively respectively
On the wall with groove opposite side of front and rear edge loose piece, mold is clamped to adjust loose piece.
4. the forming frock of unmanned plane composite material integral panel according to claim 3, it is characterised in that：The rear
There are one clamping positioning mechanism configurations, positioned at the intermediate position of the rear I-beam configuring area, the leading edge clamping and positioning machine
Structure is configured two, positioned at the preceding I-beam configuring area, and positioned at the both sides of the rear clamping positioning mechanism.
5. the forming frock of the unmanned plane composite material integral panel according to any one of claim 1-4, feature exist
In：The left and right mold is made with intermediate auxiliary with die main body of aluminium alloy.
6. a kind of forming method of unmanned plane composite material integral panel utilizes the nothing described in any one of Claims 1 to 55
The forming frock manufacture integral panel of man-machine composite material integral panel, which is characterized in that including：
Step 1: at least one high-performance fiber is centainly sequentially coated with by certain number of plies in the recessed of covering forming mold cavity block
In shape groove bottom wall；
Step 2: it is wrapped up in the silicane rubber plate end of the left and right mold of I-beam mold for forming according to the mode that is coated with of step 1
The high-performance fiber, the high-performance fiber on mould ends side are used to form I-beam web, on the surface above and below mold
High-performance fiber be used to form I-beam edge strip；
Step 3: by the end pairing for sticking high-performance fiber of the left and right mold of I-beam mold for forming, in apposition position
Upper and lower end parts carry out R angle fillings, i.e., be twisted into using high-performance fiber and fill and lead up the upper and lower side R angles of apposition position with fiber type item,
Then high-performance fiber, shape are integrally coated with above the high-performance fiber of the flange formation on left and right mold respectively upper and lower surface
Flange above and below into the I-beam；
Step 4: by each left and right mold with intermediate auxiliary mould to the curve form of synthesis wing cover；
Step 5: by the I-beam mold for forming after pairing be placed on by step 1 lay the covering of high-performance fiber into
In type mold, and the clamping positioning mechanism for adjusting both sides is compressed；
Step 6: a layer thickness is laid in the upper surface of the placement I-beam mold for forming of step 5 as 5-10mm silicon rubber,
Formpiston is covered, molding is put into baking oven after tightening, is cured by cure profile；
Step 7: being demoulded after the completion of curing, composite wing integral panel is obtained.
7. the forming method of unmanned plane composite material integral panel according to claim 6, it is characterised in that：The high property
Energy fiber is any one or a few in carbon fiber, glass fibers, aramid fiber.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108891040A (en) * | 2018-06-21 | 2018-11-27 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method |
| CN109305329A (en) * | 2018-10-26 | 2019-02-05 | 上海歌尔泰克机器人有限公司 | The processing method of wing, unmanned vehicle and wing |
| CN109532059A (en) * | 2018-12-03 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of production method of hollow and thin-walled airfoil structure composite material element |
| CN110712324A (en) * | 2019-10-30 | 2020-01-21 | 航天特种材料及工艺技术研究所 | Integrated die for molding and assembling composite material wings |
| CN112238551A (en) * | 2020-09-27 | 2021-01-19 | 航天特种材料及工艺技术研究所 | Multi-part integrated forming assembly die and forming assembly method for composite wing |
| CN112848374A (en) * | 2021-01-09 | 2021-05-28 | 哈尔滨工业大学 | Combined flange clamp for flexible capsule wall winding process |
| CN110712324B (en) * | 2019-10-30 | 2022-06-24 | 航天特种材料及工艺技术研究所 | Integrated die for molding and assembling composite material wings |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108891040A (en) * | 2018-06-21 | 2018-11-27 | 西安爱生技术集团公司 | A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method |
| CN109305329A (en) * | 2018-10-26 | 2019-02-05 | 上海歌尔泰克机器人有限公司 | The processing method of wing, unmanned vehicle and wing |
| CN109532059A (en) * | 2018-12-03 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A kind of production method of hollow and thin-walled airfoil structure composite material element |
| CN110712324A (en) * | 2019-10-30 | 2020-01-21 | 航天特种材料及工艺技术研究所 | Integrated die for molding and assembling composite material wings |
| CN110712324B (en) * | 2019-10-30 | 2022-06-24 | 航天特种材料及工艺技术研究所 | Integrated die for molding and assembling composite material wings |
| CN112238551A (en) * | 2020-09-27 | 2021-01-19 | 航天特种材料及工艺技术研究所 | Multi-part integrated forming assembly die and forming assembly method for composite wing |
| CN112848374A (en) * | 2021-01-09 | 2021-05-28 | 哈尔滨工业大学 | Combined flange clamp for flexible capsule wall winding process |
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