CN110450937A - Composite material " work " type stringer wall panel structure, molding die and forming method - Google Patents
Composite material " work " type stringer wall panel structure, molding die and forming method Download PDFInfo
- Publication number
- CN110450937A CN110450937A CN201910784953.4A CN201910784953A CN110450937A CN 110450937 A CN110450937 A CN 110450937A CN 201910784953 A CN201910784953 A CN 201910784953A CN 110450937 A CN110450937 A CN 110450937A
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- laying
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- intercalation
- covering
- stringer
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- 238000000465 moulding Methods 0.000 title claims abstract description 28
- 239000002131 composite material Substances 0.000 title claims abstract description 27
- 238000000034 method Methods 0.000 title claims abstract description 21
- 230000002687 intercalation Effects 0.000 claims abstract description 49
- 238000009830 intercalation Methods 0.000 claims abstract description 49
- 238000007711 solidification Methods 0.000 claims abstract description 10
- 230000008023 solidification Effects 0.000 claims abstract description 10
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 10
- 229910052802 copper Inorganic materials 0.000 claims description 10
- 239000010949 copper Substances 0.000 claims description 10
- 238000010276 construction Methods 0.000 claims description 5
- 230000002093 peripheral effect Effects 0.000 claims description 3
- 239000000463 material Substances 0.000 abstract description 4
- 238000002360 preparation method Methods 0.000 abstract description 4
- 238000010586 diagram Methods 0.000 description 7
- 238000004519 manufacturing process Methods 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000009786 automated tape laying Methods 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000002994 raw material Substances 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
- 239000002699 waste material Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
- B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
-
- 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
- B29C33/42—Moulds or cores; Details thereof or accessories therefor characterised by the shape of the moulding surface, e.g. ribs or grooves
-
- 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
-
- 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
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Architecture (AREA)
- Civil Engineering (AREA)
- Structural Engineering (AREA)
- Finishing Walls (AREA)
- Moulding By Coating Moulds (AREA)
- Devices For Post-Treatments, Processing, Supply, Discharge, And Other Processes (AREA)
Abstract
The present invention relates to technique for aircraft composite technical field, providing a kind of composite material " work " type stringer wall panel structure, molding die and forming method, the wall panel structure includes several " C " type layings, intermediate intercalation, flange intercalation and covering laying；In covering laying, closure and covering the laying solidification of " C " type laying connect " C " type laying lying side-by-side；Intermediate intercalation is set in the gap between adjacent " C " type laying, and intermediate intercalation and the solidification of covering laying connect；The upper flange of " work " type stringer is collectively formed in " C " type laying, the top of intermediate intercalation in the setting of flange intercalation.The present invention can get the splicing area much larger than tradition work shape stringer Material Stiffened Panel, while increasing stringer bearing capacity, reduce the processing capacity of stringer；" C " type laying is supported using Collapsible mould, the release problems of composite material " work " type stringer is solved, the preparation of stringer structure can be fast implemented.
Description
Technical field
The present invention relates to technique for aircraft composite technical field, in particular to a kind of composite material " work " type stringer siding knot
Structure, molding die and forming method.
Background technique
Composite material " work " type stringer Material Stiffened Panel is widely used in fuselage main force support structure, especially aerofoil wall panel structure
In.Common " work " type stringer structure type is as shown in Figure 1.
The main problem of traditional structure forms is analyzed as follows:
1, T-type stringer siding is compared, " work " type stringer siding has higher structure efficiency, bending resistance and stringer side
Edge impact resistance is improved；
2, existing " work " type stringer wall panel structure design scheme, upper lower flange are both needed to reserve enough surplus satisfaction manufacture sides
The processing request on boundary；
3, the splicing area surplus of traditional " work " type stringer Material Stiffened Panel is small, and when degumming influences integral panel structure.
Summary of the invention
An object of the present invention is exactly to have overcome the deficiencies of the prior art and provide a kind of composite material " work " type stringer wall
Hardened structure, molding die and forming method reduce the waste of raw material, improve laying efficiency, reduce tooling preparation cost, improve
Stringer bottom laying and covering bonding quality, guarantee the quality and precision of product.
The present invention adopts the following technical scheme:
A kind of composite material " work " type stringer wall panel structure, is used for plane airfoil siding, and composite material " work " type is long
Purlin wall panel structure includes " C " type laying, intermediate intercalation, flange intercalation and covering laying；
" C " type laying side by side parallel described in several is laid in the covering laying, the closure of " C " the type laying
In plane, the closure and covering laying solidification are connected；There are gap, institutes between " C " type laying described in adjacent 2
It states and the intermediate intercalation is set in gap, the intermediate intercalation solidifies with " C " type laying and the covering laying to be connect；It is described
The setting of flange intercalation forms the upper flange of " work " type stringer at " C " the type laying and the top of intermediate intercalation；The flange is inserted
Layer solidifies with the top of " C " the type laying, intermediate intercalation to be connect.
Further, using co-curing or altogether between described " C " the type laying, intermediate intercalation, flange intercalation and covering laying
Cementation process realizes integral solidifying.
Further, " C " the type laying at stringer wall panel structure both ends is half c-type.
A kind of molding die of above-mentioned composite material " work " type stringer wall panel structure, comprising:
" C " type laying forming frock is used for lay-up molding " C " type laying；
Flange tooling is used for the upper flange of lay-up molding " work " type stringer；
Covering tooling is used for laying covering laying, and realizes that " C " type laying is connect with the solidification of covering laying.
Further, described " C " the type laying forming frock, including dismountable left block, right block, upper stopper and lower block
Block；
The lower stopper is inverted T shaped piece；The left block, right block include ontology and protruding portion, the left block, the right side
Block passes through protruding portion symmetric support in the flange surfaces of the lower stopper；The upper stopper is arranged in the lower stopper
Portion；The left block, right block, upper stopper and lower stopper, which can fit closely, to be integral；
" C " the type laying is preforming by the left stop block body, upper stopper, the outer peripheral edge of right stop block body.
Further, the flange tooling, covering tooling are slab construction.
Further, the upper stopper, lower stopper are correspondingly arranged positioning mechanism；The positioning mechanism be groove and with it is described
The corresponding plush copper of groove；
When the groove is arranged in the upper stopper, the corresponding plush copper is arranged in the lower stopper；When the lower stopper
When the groove is arranged, the corresponding plush copper is arranged in the upper stopper.
A kind of forming method of composite material " work " type stringer wall panel structure, using above-mentioned molding die, including it is as follows
Step:
S1, left block, right block, upper stopper and lower stopper collectively constitute " C " type laying forming frock, for single " C "
The lay-up molding of type laying；Keep " C " type laying and the relative position of " C " type laying forming frock it is constant, " C " type laying and
" C " type laying tooling forms the first assembly；
S2, several described first assembly side by side parallel are placed, and are interleave in setting between adjacent " C " the type laying
Layer is completed Zone R using spill item and is filled, forms the second assembly；The Zone R is between " C " the type laying and intermediate intercalation
The gap of formation；Then second assembly is subjected to whole 180 ° of overturning；
S3, lower stopper is detached, keeps left block, right block, upper stopper and " C " type laying relative position constant；According to
Flange intercalation and flange tooling are placed in design, form third assembly；
S4, it will position, be then combined with covering laying, after Vacuum Package between the third assembly and covering tooling
Complete whole co-curing molding.
Further, the forming method further include:
Described in S5, dismounting when " C " type laying forming frock, the upper stopper is first removed, then removes the left block, the right side
Block.
Further, in step S2,180 ° of overturning is carried out several described first assemblys first, then adjacent institute
It states and intermediate intercalation is set between " C " type laying, obtain second assembly.
The present invention also provides a kind of aircraft, the above-mentioned composite material of the aircraft utilization " work " type stringer wall panel structures.
The invention has the benefit that " C " type laying is bonded completely with covering laying, it is long that acquisition is far longer than traditional work shape
The splicing area of purlin Material Stiffened Panel while increasing stringer bearing capacity, reduces the processing capacity of stringer, simultaneously effective avoids
The problem of entire wall panel structure influenced due to stringer degumming；The technique that co-curing can be used or be glued altogether completes siding knot
The integral solidifying of structure greatly improves manufacture efficiency, reduces the composite material proportion of goods damageds；" C " type is spread using Collapsible mould
Layer is supported, and is solved the release problems of composite material " work " type stringer, can be fast implemented the preparation of stringer structure；This hair
It is bright simple for process, there is great promotional value.
Detailed description of the invention
Fig. 1 show traditional " work " type stringer wall panel structure schematic diagram.
Fig. 2 show a kind of composite material of the embodiment of the present invention " work " type stringer wall panel structure schematic diagram.
Fig. 3 show the structural schematic diagram of " C " type laying forming frock.
Fig. 4 show the structural schematic diagram of the second assembly.
Fig. 5 show the structural schematic diagram of third assembly.
Fig. 6 show composite material " work " type stringer wall panel structure core model demoulding schematic diagram.
Fig. 7 show left block (right block) structural schematic diagram.
In figure: the left block of 1-；2- upper stopper；The right block of 3-；4- lower stopper；5- " C " type laying；Intercalation among 6-；The angle 7-R
Filler；8- flange intercalation；9- flange tooling；10- covering laying；11- covering tooling；101- ontology；102- protruding portion.
Specific embodiment
Below in conjunction with specific attached drawing the present invention is described in detail specific embodiment.It should be noted that in following embodiments
The combination of the technical characteristic or technical characteristic of description is not construed as isolated, they can be combined with each other to reaching
To superior technique effect.
As shown in Fig. 2, a kind of composite material of the embodiment of the present invention " work " type stringer wall panel structure, including several " C " types
Laying 5, intermediate intercalation 6, flange intercalation 8 and covering laying 10；5 side by side parallel of " C " type laying described in several is laid in described
In covering laying 10, the closure of " C " the type laying 5 is in plane, and the closure and the covering laying 10 solidification connect；
There are gap between " C " type laying 5 described in adjacent 2, the intermediate intercalation 6, the intermediate intercalation 6 are set in the gap
Bottom and the covering laying 10 solidification connect；The flange intercalation 8 setting is in " C " the type laying 5, intermediate intercalation 6
The upper flange of " work " type stringer is collectively formed in top；The top of the flange intercalation 8 and " C " the type laying 5, intermediate intercalation 6
Solidification connection.
Preferably, between described " C " the type laying 5, intermediate intercalation 6, flange intercalation 8 and covering laying 10 using co-curing or
Cementation process realizes integral solidifying altogether.
" C " the type laying 5 at stringer wall panel structure both ends is half c-type (half of complete " C " type laying or part),
The angle R filler 7 is filled in the angle the R gap of 8 end of flange intercalation (being collectively formed with covering laying 10, " C " type laying 5).
The embodiment of the present invention can be set by automated tape-laying or manual paving compared to original " work " type stringer wall panel structure
Meter scheme, which increases stringer and effective splicing region of stressed-skin construction, reduces stringer while increasing the bearing capacity of stringer
Processing capacity.
As shown in figure 3, a kind of molding die of above-mentioned composite material " work " type stringer wall panel structure of the embodiment of the present invention, packet
It includes:
" C " type laying forming frock is used for lay-up molding " C " type laying 5；Preferably, described " C " the type laying forms work
Dress, including dismountable left block 1, right block 3, upper stopper 2 and lower stopper 4；The lower stopper 4 is inverted T shaped piece；The left gear
Block 1, right block 3 include ontology 101 and protruding portion 102, and (ontology 101 is formed for " C " type laying 5, prominent as shown in Figure 7
Mat formation and position for flange intercalation 8 and flange tooling 9 in portion 102), the left block 1, right block 3 are by protruding portion 102
Symmetric support is in the flange surfaces of the lower stopper 4；The upper stopper 2 is arranged on 4 top of lower stopper；The left block
1, right block 3, upper stopper 2 and lower stopper 4, which can fit closely, is integral；" C " the type laying 5 passes through the left block sheet
Body, upper stopper 2, the outer peripheral edge of right stop block body are preforming
Flange tooling 9 is slab construction, is used for the upper flange of lay-up molding " work " type stringer；
Covering tooling 11 is slab construction, is used for laying covering laying 10, and realize " C " type laying 5 and covering laying 10
Solidification connection.
Preferably, the upper stopper 2, lower stopper 4 are correspondingly arranged positioning mechanism；The positioning mechanism be groove and with it is described
The corresponding plush copper of groove；When the groove is arranged in the upper stopper 2, the corresponding plush copper is arranged in the lower stopper 4；Or
When the groove is arranged in the lower stopper 4, the corresponding plush copper is arranged in the upper stopper 2.
Molding die provided by the invention solves the release problems of composite material " work " type stringer, can fast implement
The preparation of stringer structure improves the molding production efficiency of stringer.
The forming method of a kind of composite material of the embodiment of the present invention " work " type stringer wall panel structure, uses above-mentioned shaping mould
Tool, includes the following steps:
S1, left block 1, right block 3, upper stopper 2 and lower stopper 4 collectively constitute " C " type laying forming frock, for single
The lay-up molding (and curing molding after later period and 10 entire combination of covering laying) of " C " type laying 5；Left block 1, right block 3
Fit structure between fit structure and upper stopper 2 and lower stopper 4 between lower stopper 4 between groove, plush copper, it is ensured that combined type
Forming frock overall co-ordination gap is met the requirements；Keep " C " type laying 5 and the relative position of " C " type laying forming frock constant,
" C " type laying 5 and " C " type laying tooling form the first assembly；As shown in Figure 3；
S2, several described first assembly side by side parallel are placed, and are arranged between adjacent " C " the type laying 5 intermediate
Intercalation 6 is completed Zone R using spill item and is filled, forms the second assembly；The Zone R is " C " the type laying 5 and intermediate intercalation 6
Between the gap that is formed；Then second assembly is carried out whole 180 ° of overturning (can also be using first to several institutes
It states the first assembly and carries out 180 ° of overturning, then intermediate intercalation 6 is set between adjacent " C " the type laying 5, obtain described the
Two assemblys)；As shown in Figure 4；
S3, lower stopper 4 is detached, keeps left block 1, right block 3, upper stopper 2 and 5 relative positions of " C " type laying constant；
Flange intercalation 8 and flange tooling 9 are placed according to design, forms third assembly；As shown in Figure 5；
S4, it will position, be then combined with covering laying 10, vacuum seal between the third assembly and covering tooling 11
Whole co-curing molding is completed after dress, it is also shown in FIG. 5；
Relatively difficult problem is demoulded for drum stringer co-curing wall panel structure, the application has also been devised as shown in Figure 6
The knockout course S5 that removes respectively of " C " type laying forming frock: described in dismounting when " C " type laying forming frock, first remove institute
Upper stopper 2 is stated, the left block 1, right block 3 are then removed.
Although several embodiments of the present invention are had been presented for herein, it will be appreciated by those of skill in the art that In
Without departing from the spirit of the invention, the embodiments herein can be changed.Above-described embodiment is only exemplary, no
It should be using the embodiments herein as the restriction of interest field of the present invention.
Claims (10)
1. a kind of composite material " work " type stringer wall panel structure, which is characterized in that inserted including " C " type laying, intermediate intercalation, flange
Layer and covering laying；
" C " type laying side by side parallel described in several is laid in the covering laying, and the closure of " C " the type laying is in flat
Face, the closure and covering laying solidification connect；There are gaps between " C " type laying described in adjacent 2, between described
The intermediate intercalation is set in gap, and the intermediate intercalation solidifies with " C " type laying and the covering laying to be connect；The flange
Intercalation setting forms the upper flange of " work " type stringer at " C " the type laying and the top of intermediate intercalation；The flange intercalation with
" C " the type laying, intermediate intercalation top solidify connection.
2. composite material " work " type stringer wall panel structure as described in claim 1, which is characterized in that " C " the type laying, in
Between between intercalation, flange intercalation and covering laying using co-curing or altogether cementation process realize integral solidifying.
3. composite material " work " type stringer wall panel structure as described in claim 1, which is characterized in that the stringer wall panel structure
" C " the type laying at both ends is half c-type.
4. a kind of molding die of composite material as described in any one of claims 1-3 " work " type stringer wall panel structure, special
Sign is, comprising:
" C " type laying forming frock is used for lay-up molding " C " type laying；
Flange tooling is used for the upper flange of lay-up molding " work " type stringer；
Covering tooling is used for laying covering laying, and realizes that " C " type laying is connect with the solidification of covering laying.
5. molding die as claimed in claim 4, which is characterized in that " C " the type laying forming frock, including it is dismountable
Left block, right block, upper stopper and lower stopper；
The lower stopper is inverted T shaped piece；The left block, right block include ontology and protruding portion, the left block, right block
Through protruding portion symmetric support in the flange surfaces of the lower stopper；The upper stopper is arranged on the lower stopper top；
The left block, right block, upper stopper and lower stopper, which can fit closely, to be integral；
" C " the type laying is preforming by the left stop block body, upper stopper, the outer peripheral edge of right stop block body.
6. molding die as claimed in claim 5, which is characterized in that the flange tooling, covering tooling are slab construction.
7. molding die as claimed in claim 5, which is characterized in that the upper stopper, lower stopper are correspondingly arranged positioning mechanism；
The positioning mechanism is groove and plush copper corresponding with the groove；
When the groove is arranged in the upper stopper, the corresponding plush copper is arranged in the lower stopper；When the lower stopper is arranged
When the groove, the corresponding plush copper is arranged in the upper stopper.
8. a kind of forming method of composite material " work " type stringer wall panel structure, which is characterized in that using such as claim 5 or 6
The molding die, includes the following steps:
S1, left block, right block, upper stopper and lower stopper collectively constitute " C " type laying forming frock, for single " C " type paving
The lay-up molding of layer；Keep " C " type laying and the relative position of " C " type laying forming frock constant, " C " type laying and " C " type
Laying tooling forms the first assembly；
S2, several described first assembly side by side parallel are placed, and intermediate intercalation is arranged between adjacent " C " the type laying,
Zone R is completed using spill item to fill, and forms the second assembly；The Zone R is to be formed between " C " the type laying and intermediate intercalation
Gap；Then second assembly is subjected to whole 180 ° of overturning；
S3, lower stopper is detached, keeps left block, right block, upper stopper and " C " type laying relative position constant；According to design
Flange intercalation and flange tooling are placed, third assembly is formed；
S4, it will be positioned between the third assembly and covering tooling, be then combined with covering laying, completed after Vacuum Package
Whole co-curing molding.
9. forming method as claimed in claim 8, which is characterized in that the forming method further include:
Described in S5, dismounting when " C " type laying forming frock, the upper stopper is first removed, then removes the left block, right gear
Block.
10. forming method as claimed in claim 8 or 9, which is characterized in that in step S2, first several described first
Assembly carries out 180 ° of overturning, and intermediate intercalation is then arranged between adjacent " C " the type laying, obtains second combination
Body.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910784953.4A CN110450937B (en) | 2019-08-23 | 2019-08-23 | I-shaped long-purlin wallboard structure made of composite material, forming die and forming method |
| PCT/CN2019/114632 WO2021035941A1 (en) | 2019-08-23 | 2019-10-31 | Wall plate structure for composite-material stringer in shape of chinese character "工", and forming mold and forming method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910784953.4A CN110450937B (en) | 2019-08-23 | 2019-08-23 | I-shaped long-purlin wallboard structure made of composite material, forming die and forming method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110450937A true CN110450937A (en) | 2019-11-15 |
| CN110450937B CN110450937B (en) | 2020-12-04 |
Family
ID=68488849
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910784953.4A Active CN110450937B (en) | 2019-08-23 | 2019-08-23 | I-shaped long-purlin wallboard structure made of composite material, forming die and forming method |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN110450937B (en) |
| WO (1) | WO2021035941A1 (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
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| CN111267367A (en) * | 2020-03-16 | 2020-06-12 | 沈阳飞机工业（集团）有限公司 | Processing method for forming double-side zero-degree fiber T-shaped stringer |
| CN111392410A (en) * | 2020-04-02 | 2020-07-10 | 常州市新创智能科技有限公司 | I-shaped stringer core mold transfer device and method |
| CN111958884A (en) * | 2020-08-17 | 2020-11-20 | 沈阳飞机工业（集团）有限公司 | Composite material large-scale wing I-shaped stringer wallboard forming tool |
| CN112356462A (en) * | 2020-10-16 | 2021-02-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Integral forming tool and process for composite material U-shaped long-purlin stiffened wall plate structure |
| CN115742362A (en) * | 2022-11-15 | 2023-03-07 | 江西洪都航空工业集团有限责任公司 | Composite square tube bending inclined support paving and pasting mold |
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| CN111070724A (en) * | 2019-11-20 | 2020-04-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Integral forming method and tool for composite material U-shaped stringer wallboard |
| CN111070724B (en) * | 2019-11-20 | 2021-08-17 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Integral forming method and tool for composite material U-shaped stringer wallboard |
| CN111267367A (en) * | 2020-03-16 | 2020-06-12 | 沈阳飞机工业（集团）有限公司 | Processing method for forming double-side zero-degree fiber T-shaped stringer |
| CN111392410A (en) * | 2020-04-02 | 2020-07-10 | 常州市新创智能科技有限公司 | I-shaped stringer core mold transfer device and method |
| CN111392410B (en) * | 2020-04-02 | 2020-10-02 | 常州市新创智能科技有限公司 | I-shaped stringer core mold transfer device and method |
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| CN112356462A (en) * | 2020-10-16 | 2021-02-12 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Integral forming tool and process for composite material U-shaped long-purlin stiffened wall plate structure |
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| CN115742362A (en) * | 2022-11-15 | 2023-03-07 | 江西洪都航空工业集团有限责任公司 | Composite square tube bending inclined support paving and pasting mold |
Also Published As
| Publication number | Publication date |
|---|---|
| CN110450937B (en) | 2020-12-04 |
| WO2021035941A1 (en) | 2021-03-04 |
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