CN204263555U - For the RTM mold for forming of large technique for aircraft composite spoiler joint - Google Patents
For the RTM mold for forming of large technique for aircraft composite spoiler joint Download PDFInfo
- Publication number
- CN204263555U CN204263555U CN201420603702.4U CN201420603702U CN204263555U CN 204263555 U CN204263555 U CN 204263555U CN 201420603702 U CN201420603702 U CN 201420603702U CN 204263555 U CN204263555 U CN 204263555U
- Authority
- CN
- China
- Prior art keywords
- die cavity
- forming
- cover plate
- rtm mold
- aircraft composite
- 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.)
- Active
Links
Landscapes
- Moulds For Moulding Plastics Or The Like (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The utility model relates to a kind of RTM mold for forming for large technique for aircraft composite spoiler joint, and described RTM mold for forming comprises cover plate, sealing strip, die cavity, thimble and compressing tablet from top to bottom; Described cover plate is connected with die cavity by screw; The position of described sealing strip between cover plate and die cavity; Described thimble is arranged in position, cavity bottom hole, is connected by thimble by the screw of band compressing tablet with die cavity.The beneficial effects of the utility model are: utilize the composite products that this mould RTM is shaping, integration degree is high, and weight loss effect is good, manufacturing process is simple, belong to low-cost manufacturing technique, overcome tradition and adopt hardware, quality weighs and the problem of globality difference.
Description
Technical field
The utility model belongs to composite material forming field, is specifically related to a kind of RTM mold for forming for large technique for aircraft composite spoiler joint.
Background technology
Loss of weight is the theme that airplane design is eternal, adopt one of core objective of composite will alleviate the construction weight of aircraft exactly, the high specific strength of composite, high ratio modulus, good decay resistance, higher damage tolerance performance and good anti-fatigue performance etc. all can bring obvious weight loss effect, and composite builds and can adopt global formation, reduce the use of securing member, not only can play the effect of loss of weight, production cost and assembly work amount can also be reduced.
In the present invention RTM mould prepare for large technique for aircraft composite spoiler joint, compared with traditional Test of Laminate Composites, the RTM-D braided composites adopted is a kind of novel structural material, the method of braiding is adopted first fiber to be made prefabricated component, then adopt RTM technique by low glutinous resin injection mould, final curing, its advantage is that the damage tolerance of finished product is high, formed precision is high, porosity is little, the Rigidity and strength of thickness direction is high, and interlaminar strength is high, and the simple cost of moulding process is low.
Utility model content
For defect of the prior art, the purpose of this utility model is to provide a kind of RTM mold for forming for large technique for aircraft composite spoiler joint,
The utility model is achieved through the following technical solutions:
The utility model provides a kind of RTM mold for forming for large technique for aircraft composite spoiler joint, and described RTM mold for forming mainly comprises cover plate, sealing strip, die cavity, thimble and compressing tablet from top to bottom;
Described cover plate is connected with die cavity by screw; The position of described sealing strip between cover plate and die cavity; Described thimble is arranged in position, cavity bottom hole, is connected by thimble by the screw of band compressing tablet with die cavity.
Preferably, described cover plate is provided with some gum-injecting ports.
More preferably, described gum-injecting port is positioned at cover plate middle part, and quantity is 1 ~ 5.
Preferably, described cover plate inside is provided with spew groove.
More preferably, the cross section of described spew groove is I shape.
Preferably, the inside of described die cavity is provided with groove and some gum outlets, and gum outlet is arranged in die cavity interior grooves.
More preferably, described gum outlet is positioned at groove floor or top, bottom surface is no more than 5cm place, and gum outlet quantity is 1 ~ 4.
Preferably, described die cavity is provided with some centre hole positions; Described centre hole position is located at the plane place of two auricle places and the die cavity stretched out die cavity inside.
More preferably, described centre hole bit quantity is 2 ~ 6.
Compared with prior art, the utility model has following beneficial effect:
1, utilize this formed in mould composite products, more preferably realize the overall performance of product, damage tolerance is high, and formed precision is high, and porosity is little, and the Rigidity and strength of thickness direction is high, and interlaminar strength is high;
2, compared with metal material, achieve the loss of weight of product, the globality of product, improve product mechanical property, the process costs of simplification.
Accompanying drawing explanation
By reading the detailed description done non-limiting example with reference to the following drawings, other features, objects and advantages of the present utility model will become more obvious:
Fig. 1 is the structural representation of the utility model RTM mould;
Wherein 1 is screw; 2 is cover plates; 3 is sealing strips; 4 is die cavities; 5 is thimbles; 6 is compressing tablets;
Fig. 2 is the positive schematic perspective view of the utility model mould;
Fig. 3 is the schematic perspective view of the die cavity of the utility model mould;
Fig. 4 is the front view of the die cavity of the utility model mould;
Wherein, 7 is centre hole positions;
Fig. 5 is the front view of the cover plate of the utility model mould.
Detailed description of the invention
Below in conjunction with specific embodiment, the utility model is described in detail.Following examples will contribute to those skilled in the art and understand the utility model further, but not limit the utility model in any form.It should be pointed out that to those skilled in the art, without departing from the concept of the premise utility, some distortion and improvement can also be made.These all belong to protection domain of the present utility model.
embodiment 1
The present embodiment relates to a kind of RTM mold for forming for large technique for aircraft composite spoiler joint, existing composition graphs 1,2,3,4,5 is described further, the RTM mould for spoiler joint that the present embodiment relates to, comprise: screw 1, cover plate 2, sealing strip 3, die cavity 4, thimble 5, compressing tablet 6; Described cover plate middle part is provided with 1 gum-injecting port; Described die cavity inside is provided with 2 gum outlets, and gum outlet is positioned at die cavity groove bottommost; Thimble room quantity is 2.
In the utility model, put in the position, hole corresponding to die cavity 4 by thimble 5, be connected with compressing tablet 6 by soket head cap screw with die cavity 4, ensure to closely cooperate, air-tightness is good, and composite spoiler joint three-dimensional braiding preforms is put into die cavity.
Sealing strip 3 is placed on the relevant position of die cavity 4, covers cover plate 2 and compressed by screw 1, guarantee that the air-tightness of mould is good.
Glue is injected according to certain pressure by gum-injecting port, all has to gum outlet position glue to flow out and stop injecting glue, then solidify, complete product preparation.
During the demoulding, unload lower cover, by thimble, product is ejected from die cavity, can take out smoothly.
embodiment 2
The present embodiment relates to a kind of RTM mold for forming for large technique for aircraft composite spoiler joint, and technical scheme is as the preference of embodiment 1, and improvements are only: described cover plate middle part is provided with 3 gum-injecting ports; Described die cavity inside is provided with 2 gum outlets, and gum outlet is positioned at 2.5cm place on die cavity bottom portion of groove; Thimble room quantity is 4.
embodiment 3
The present embodiment relates to a kind of RTM mold for forming for large technique for aircraft composite spoiler joint, and technical scheme is as the preference of embodiment 1, and improvements are only: described cover plate middle part is provided with 5 gum-injecting ports; Described die cavity inside is provided with 4 gum outlets, and gum outlet is positioned at 5cm place on die cavity bottom portion of groove; Thimble room quantity is 6.
Above specific embodiment of the utility model is described.It is to be appreciated that the utility model is not limited to above-mentioned particular implementation, those skilled in the art can make various distortion or amendment within the scope of the claims, and this does not affect flesh and blood of the present utility model.
Claims (9)
1. the RTM mold for forming for large technique for aircraft composite spoiler joint, it is characterized in that, described RTM mold for forming comprises cover plate (2), sealing strip (3), die cavity (4), thimble (5) and compressing tablet (6) from top to bottom; Described cover plate (2) is connected with die cavity (4) by screw (1); Described sealing strip (3) is positioned at the position between cover plate (2) and die cavity (4); Described thimble (5) is arranged in die cavity (4) base apertures position, is connected by thimble (5) by the screw (1) of band compressing tablet (6) with die cavity (4).
2. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 1, it is characterized in that, described cover plate (2) is provided with some gum-injecting ports.
3. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 2, it is characterized in that, described gum-injecting port is positioned at cover plate (2) middle part, and quantity is 1 ~ 5.
4. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 1, it is characterized in that, described cover plate (2) inside is provided with spew groove.
5. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 4, it is characterized in that, the cross section of described spew groove is I shape.
6. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 1, is characterized in that, the inside of described die cavity (4) is provided with groove and some gum outlets, and gum outlet is arranged in die cavity interior grooves.
7. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 6, is characterized in that, described gum outlet is positioned at groove floor or distance top, bottom surface is no more than 5cm place, and quantity is 1 ~ 4.
8. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 1, it is characterized in that, described die cavity (4) is provided with some centre hole positions; Described centre hole position is located at the plane place of two auricle places and the die cavity stretched out die cavity inside.
9. the RTM mold for forming for large technique for aircraft composite spoiler joint according to claim 8, it is characterized in that, described centre hole bit quantity is 2 ~ 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420603702.4U CN204263555U (en) | 2014-10-17 | 2014-10-17 | For the RTM mold for forming of large technique for aircraft composite spoiler joint |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420603702.4U CN204263555U (en) | 2014-10-17 | 2014-10-17 | For the RTM mold for forming of large technique for aircraft composite spoiler joint |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204263555U true CN204263555U (en) | 2015-04-15 |
Family
ID=52798450
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420603702.4U Active CN204263555U (en) | 2014-10-17 | 2014-10-17 | For the RTM mold for forming of large technique for aircraft composite spoiler joint |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204263555U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235236A (en) * | 2015-11-12 | 2016-01-13 | 江苏恒神股份有限公司 | Autoclave die for improving surface quality of workpiece and method |
| CN112873906A (en) * | 2020-12-25 | 2021-06-01 | 中国航空制造技术研究院 | RTM forming die of composite material barrel structure |
-
2014
- 2014-10-17 CN CN201420603702.4U patent/CN204263555U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235236A (en) * | 2015-11-12 | 2016-01-13 | 江苏恒神股份有限公司 | Autoclave die for improving surface quality of workpiece and method |
| CN112873906A (en) * | 2020-12-25 | 2021-06-01 | 中国航空制造技术研究院 | RTM forming die of composite material barrel structure |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103909658B (en) | Composite material connecting skirt forming method and mold and inner rubber core mold forming mold | |
| CN105415709B (en) | 3D nylon wind pipes are molded the moulding process of fire-retardant camber beam and make mold | |
| CN207172615U (en) | A kind of air conditioner housing injection mold | |
| CN103273604A (en) | Curing and forming method of hollow structural member made of composite material | |
| CN204263555U (en) | For the RTM mold for forming of large technique for aircraft composite spoiler joint | |
| CN204622394U (en) | A kind of carbon fiber cell type prefabricated component is made and is used shaper | |
| CN102785308A (en) | Once-shaped forming die of air chamber rubber diaphragm and forming process | |
| CN104249448A (en) | Processing method of ABS (acrylonitrile-butadiene-styrene) resin low pressure injection refrigerator inner container | |
| CN206264252U (en) | A kind of plastic, rubber injection molding device | |
| CN103479384B (en) | A kind of sound guide tube, sound guide tube preparation method and mould | |
| CN204309189U (en) | A kind of rubber rectangular ring mould | |
| CN101920562A (en) | Clear dimension compression molding method for phenolic resin based complex profile product | |
| CN104972601A (en) | Injection molding method of double-color super-thick cladding element | |
| CN204658827U (en) | A kind of heavy wall photoconduction injection moulding quadric injection mould mould | |
| CN202826268U (en) | Mold structure with assembled mold core | |
| CN103769541B (en) | Volute center mold-splitting forming method and forming tooling | |
| CN207345100U (en) | The molding die of aircraft machine cover shell | |
| CN102343648A (en) | Double-colored injection mold for spinning | |
| CN207240916U (en) | High-pressure resin Transfer molding mould | |
| CN213533888U (en) | Composite material preforming frock | |
| CN204451063U (en) | Box cover die in single valve pin trumpet assembly two-fold | |
| CN204604753U (en) | Without the mould structure of thimble vestige on a kind of injecting products | |
| CN204235840U (en) | A kind of mould with combination exhaust insert structure | |
| CN204149459U (en) | The exhaust of double color mould enters minor structure | |
| CN206455893U (en) | One kind one goes out six needle-valve injection molds |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |