CN207808546U - The forming frock of unmanned plane composite wing integral panel - Google Patents
The forming frock of unmanned plane composite wing integral panel Download PDFInfo
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- CN207808546U CN207808546U CN201721830960.6U CN201721830960U CN207808546U CN 207808546 U CN207808546 U CN 207808546U CN 201721830960 U CN201721830960 U CN 201721830960U CN 207808546 U CN207808546 U CN 207808546U
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Abstract
The utility model discloses a kind of forming frocks of unmanned plane composite wing integral panel,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 mold includes former,Former is formed according to covering outer surface Machining of Curved Surface,I-beam mold for forming monnolithic case contour surface is identical as 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 on respective I-beam edge strip at lower flange is formed with depth groove identical with lower flange thickness on I-beam,Clamping positioning mechanism is clamped positioning to I-beam molding from covering front and rear edge both sides with assembling die respectively.
Description
Technical field
The utility model belongs to composite processing manufacturing field more particularly to a kind of short range unmanned plane composite wing
The forming frock of integral panel.
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 can significantly reduce the construction weight of various products under conditions of ensureing product strength, 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, improves 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 processes 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 reduces a kind of method of cost.
Utility model content
The purpose of this utility model is to provide one kind having light-weight, the composite wing entirety of the high advantage of intensity
The forming frock of siding.
The forming frock of the unmanned plane composite wing integral panel of the utility model is for being integrally formed ground manufacture nothing
Man-machine composite wing integral panel, the integral panel include being erected on covering identical with wing side surface shape and covering
The twin I-beam risen, forming frock includes covering forming mold, I-beam mold for forming and clamping positioning mechanism, the illiteracy
Skin mold for forming includes former, and former is formed according to covering outer surface Machining of Curved Surface, and the I-beam mold for forming is whole
Appearance profile curved surface is identical as 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
The length of mold is identical as the molding length of I-beam is needed, and left and right mold is respectively provided with thickness close to one end of I-beam web
It spends for 5-10mm with type silicane rubber plate, silicane rubber plate length is equal with I-beam die length, on respective I-beam edge strip
Corresponding I-shaped beam mould upper and lower surface at lower flange is formed with depth groove identical with lower flange thickness on I-beam, when
When I-beam is multiple, intermediate auxiliary mold is installed between adjacent two I-beam mold for forming, described clamp is determined
Position mechanism is divided into leading edge clamping positioning mechanism and rear clamping positioning mechanism, is molded respectively from covering front and rear edge to the I-beam
It is clamped positioning with mold.
It is preferred that the I-beam include extend along wing length direction, front and back preceding I-beam disposed in parallel in the width direction
With rear I-beam, for the preceding I-beam than rear I-shaped beam length, the I-beam mold for forming includes that preceding I-beam molding is left
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 being arranged 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, configure in covering former
In the groove being arranged on rear wall, adjusting bolt screw thread of the spiral shell into the withstanding tight block being fixed on covering former front-rear side walls respectively
Hole, bolt end are withstood on respectively on the wall with groove opposite side of front and rear edge loose piece, are clamped to mold to adjust loose piece.
It is preferred that there are one the rear side clamping positioning mechanism configurations, it is located at the substantially intermediate of the rear I-beam configuring area
Position, the front side clamping positioning mechanism have configuration two, are located at the preceding I-beam configuring area, and press from both sides positioned at the rear side
The both sides of tight detent mechanism.
It is made it is preferred that the left and right mold is all made of aluminium alloy with intermediate auxiliary with die main body.
The utility model has the advantages that：
(1) a kind of short range unmanned plane composite wing integral panel of the utility model is with light-weight, intensity is high, resistance to
The advantages that tired, corrosion-resistant, shock resistance.Since autoclave molding solidification can not used, equipment cost is greatly reduced, is assembled into
This also further reduction；
(2) the utility model transmits solidifying pressure using silastic material, and silicon rubber has excellent high temperature oxidation resisting
Property, can meet most of intermediate temperature setting composite materials moulding process requirement, in addition its can arbitrary figuration, be suitable as shape
The compound auxiliary mould (metal positive+silicane rubber plate) of complicated product, and the spy expanded with heat and contract with cold due to silicon rubber after product molding
Property, stripping result is good；
(3) 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 structural schematic diagram of the utility model unmanned plane composite wing integral panel.
Fig. 2 is assembling schematic diagram of the utility model forming frock before covering formpiston.
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 mode
In the following, being illustrated with reference to the accompanying drawings to the most preferred embodiment of the utility model.Head when being installed with wing in text
Direction is to come to define front-rear direction, and it is left side to define above-mentioned front direction on airfoil cross-section (Fig. 2).
As shown in Figure 1, the novel short range unmanned plane composite wing integral panel I of the utility model include covering 1, it is preceding
I-beam 2 and rear I-beam 3, preceding I-beam 2 and rear I-beam 3 configured in parallel before and after wing width direction, preceding I-beam 2 compare
I-beam 3 is grown afterwards.Integral panel is made of composite material, and the high-performance fiber prepreg that the composite material uses, is carbon
At least one of fibers such as fiber, glass fibre, aramid fiber can be homogenous material, can be two or more material
Combination, the present embodiment preferentially use carbon fiber prepreg, have light-weight, the high advantage of intensity.The integral panel weight
Gently, intensity is high, it is often more important that it can be used as main force support structure to carry higher load.
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 form Integral Wing Panel molding cavity altogether, preceding I-beam molding die 5 and 6, rear I-beam at
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 that boundary is configured at 3 both sides of rear I-beam 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 on respective I-beam at lower flange formation
Be formed with depth groove identical with upper lower flange thickness in upper and lower surface, preceding I-beam molding die 5 and 6 and rear I-beam at
Pattern has the configuration of 7 and 8 same ways, and the web of former I-beam 2 is 2 both sides of I-beam before boundary is configured at, 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 lower flange shape on respective I-beam
At being formed with depth groove identical with upper lower flange thickness in the upper and lower surface at place.
In rear side setting, there are one clamping positioning mechanisms, are located 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, configure the groove being arranged on covering former rear wall
In, into the threaded hole for the 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 configures 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 and set two grooves being arranged on covering cavity block front side wall
In, two adjusting bolts 13 respectively spiral shell into the threaded hole for 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.
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 4
In shape groove bottom wall；
2, 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 the upper and lower surface of preceding I-beam molding die 5 and 6, rear I-beam molding die 7 and 8 be integrally rolled into c-type
High-performance fiber；
3, 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.
4, 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
The angles R are filled, i.e., are filled and led up the angles upper and lower side R 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；
5, 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；
6, it is 5-10mm silicon rubber to be laid with a layer thickness in the upper surface for placing 5,6,9,7,8 molds, covers molding mold
11, molding is put into baking oven after tightening, and is cured by cure profile；
7, it is demoulded after the completion of solidification, obtains composite wing integral panel.
The short range unmanned plane composite wing integral panel of the utility model has that light-weight, intensity is high, endurance, resistance to
The advantages that burn into shock resistance, it is often more important that integral panel I its load-carrying construction can be used as to carry higher load.
Claims (5)
1. a kind of forming frock of unmanned plane composite wing integral panel, for being integrally formed ground manufacture unmanned plane composite wood
Expect Integral Wing Panel, which includes the duplexing word holded up on covering identical with wing side surface shape and covering
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 mold includes former, and former is formed according to covering outer surface Machining of Curved Surface, the I-beam forming mould
It is identical as 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 as the molding length of I-beam is needed, 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
It is identical as lower flange thickness on I-beam that corresponding I-shaped beam mould upper and lower surface on beam edge strip at lower flange is formed with depth
Groove intermediate auxiliary mold, institute are installed between adjacent two I-beam mold for forming when I-beam is multiple
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 wing integral panel according to claim 1, it is characterised in that：It is described
I-beam include extend along wing length direction, front and back preceding I-beam disposed in parallel and rear I-beam in the width direction, it is described
For preceding I-beam than rear I-shaped beam length, the I-beam mold for forming includes preceding I-beam molding left and right mold, rear I-beam
Molding left and right grinding tool and intermediate auxiliary mold, intermediate auxiliary mold are located at preceding I-beam left mould tool and rear I-beam
Between right mould tool.
3. the forming frock of unmanned plane composite wing integral panel according to claim 2, it is characterised in that：It is described
Clamping positioning mechanism includes withstanding tight block, adjusting bolt and loose piece, and the loose piece of leading edge clamping positioning mechanism has I-beam before cooperation
In the groove of mold leading edge shape being arranged in covering former edge wall with type groove, configuration, rear side clamping positioning mechanism
Loose piece have I-shaped beam mould rear shape after cooperation with type groove, configuration is arranged recessed on covering former rear wall
In slot, into the threaded hole for the withstanding tight block being fixed on covering former front-rear side walls, bolt end pushes up 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 wing integral panel according to claim 3, it is characterised in that：It is described
There are one the configurations of rear clamping positioning mechanism, is located at the intermediate position of the rear I-beam configuring area, the leading edge clamps fixed
Position mechanism configures two, is located 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 wing integral panel according to any one of claim 1-4, special
Sign is：The left and right mold is all made of aluminium alloy with die main body with intermediate auxiliary and is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721830960.6U CN207808546U (en) | 2017-12-25 | 2017-12-25 | The forming frock of unmanned plane composite wing integral panel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721830960.6U CN207808546U (en) | 2017-12-25 | 2017-12-25 | The forming frock of unmanned plane composite wing integral panel |
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| Publication Number | Publication Date |
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| CN207808546U true CN207808546U (en) | 2018-09-04 |
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| CN201721830960.6U Active CN207808546U (en) | 2017-12-25 | 2017-12-25 | The forming frock of unmanned plane composite wing integral panel |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| CN109382956A (en) * | 2018-11-09 | 2019-02-26 | 北京航天新风机械设备有限责任公司 | A kind of anti-heat insulating component dead size molding die of abnormal complex and method |
| CN112297470A (en) * | 2020-10-10 | 2021-02-02 | 江西洪都航空工业集团有限责任公司 | Composite vertical stabilizer forming die |
-
2017
- 2017-12-25 CN CN201721830960.6U patent/CN207808546U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108177360A (en) * | 2017-12-25 | 2018-06-19 | 航天神舟飞行器有限公司 | The forming frock and its forming method of unmanned plane composite wing integral panel |
| CN108177360B (en) * | 2017-12-25 | 2024-07-05 | 航天神舟飞行器有限公司 | Forming tool and forming method for integral wall plate of unmanned aerial vehicle composite wing |
| CN109382956A (en) * | 2018-11-09 | 2019-02-26 | 北京航天新风机械设备有限责任公司 | A kind of anti-heat insulating component dead size molding die of abnormal complex and method |
| CN112297470A (en) * | 2020-10-10 | 2021-02-02 | 江西洪都航空工业集团有限责任公司 | Composite vertical stabilizer forming die |
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