CN101885215A - Forming method of composite material leaf grille for controlling speed of aviation aircraft - Google Patents
Forming method of composite material leaf grille for controlling speed of aviation aircraft Download PDFInfo
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- CN101885215A CN101885215A CN2009100509947A CN200910050994A CN101885215A CN 101885215 A CN101885215 A CN 101885215A CN 2009100509947 A CN2009100509947 A CN 2009100509947A CN 200910050994 A CN200910050994 A CN 200910050994A CN 101885215 A CN101885215 A CN 101885215A
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Abstract
The invention discloses a forming method of a composite material leaf grille for controlling the speed of an aviation aircraft. The method comprises the following steps of: (1) preparing a special metal hard mold; (2) preparing a silastic soft film; (3) laying a composite material; (4) solidifying; and (5) demolding. The invention solves the problem of forming difficulty due to the complicated structure of the leaf grille and has the advantages of low mold manufacture cost, simple and convenient operation, and the like.
Description
Technical field
The present invention relates to a kind of forming method of composite material leaf grille for controlling speed of aviation aircraft.
Background technology
The blade grid is mainly used in the control speed of space shuttle.The blade cell structure mainly is made up of the grid of 72 different size specifications, and the blade of 12 different sizes is arranged on the width.Because the complex structure of blade grid, blade grid forming mould complexity, difficult forming.At present, the domestic relevant report that does not also have about the composite material leaf grille for controlling speed of aviation aircraft moulding.Do not collect similar data both at home and abroad as yet yet.
Summary of the invention
Because blade cell structure complexity and the problem of moulding difficulty, the object of the present invention is to provide a kind of forming method of composite material leaf grille for controlling speed of aviation aircraft in order to solve.The present invention not only provides the forming method of blade grid, and design and the manufacture method of moulding with particular manufacturing craft is provided, and has solved blade grid forming mould complicated problems.
In order to reach the foregoing invention purpose, the technical scheme that the present invention is adopted for its technical problem of solution provides a kind of forming method of composite material leaf grille for controlling speed of aviation aircraft, comprises the steps:
Step 1: preparation special-purpose metal die,
According to the blade cell structure, make metal die with different 72 grid of size specification;
Step 2: preparation silicon rubber soft mode,
The liquid silastic that configures is poured into lentamente in the grid of blade grid special-purpose metal die of step 1 preparation, after top pressing board covers grid, room temperature was placed 20～30 hours, behind the silicon rubber vulcanization to be cast, take out the silicon rubber soft mode of blade grid punch with 72 different size specifications;
Step 3: the shop layer,
The preimpregnation cloth that composite is made is laid in the preimpregnation cloth that cuts respectively on the silicon rubber soft mode then according to the different size cutting of blade grid grid, and the lay number of plies of preimpregnation cloth is determined according to the thickness of blade grid;
Step 4: solidify,
The silicon rubber soft mode of the good preimpregnation cloth of lay is fixed in the metal die, covers cover plate, put into autoclave, heat up, pressurize, solidify after vacuumizing;
Step 5: the demoulding,
After being cooled to room temperature, take off 72 blade grid silicon rubber soft modes earlier, the composite material blade grid after will solidifying again takes out from the metal die.
Above-mentioned steps one, described metal die comprises: perpendicular baffle plate and diaphragm plate that metal material is made are inserted on the base that has slot, form 72 different grid of size specification; Each grid top is fixed by alignment pin, cushion block, top pressing board.
Above-mentioned steps two, the configuration of described liquid silastic comprises: use the R-311W liquid silastic to make soft mode, pour liquid silastic into mixing tank, mixing tank is vacuumized, requirement vacuum＜-0.9Mpa, and stirred fast 3～10 minutes, be configured to liquid silastic.
Above-mentioned steps four, described curing mode are that the staged intensification is solidified, and concrete parameter is: autoclave is warming up to 100 ± 5 ℃, is incubated 1 hour; Be warming up to 140 ± 5 ℃ again, be incubated 1.5 hours; When mold temperature was increased to 95 ± 5 ℃, autoclave began pressurization, and pressure is 0.3 ± 0.1Mpa; When mold temperature was increased to 120 ± 5 ℃, pressure increased to 0.7 ± 0.1Mpa; Mold temperature is increased to 177 ± 3 ℃, is incubated 3 hours; Begin cooling subsequently, mold temperature is reduced to 90 ℃, and autoclave stops pressurization.
The forming method of composite material leaf grille for controlling speed of aviation aircraft of the present invention, owing to adopted the metal die to carry out the method for compound material laying layer autoclave molding in conjunction with the silicon rubber soft mode, the required metal die of manufacturing is simplified greatly, the moulding process simple possible of blade grid can be used for the mass production of space shuttle control speed with the blade grid.Beneficial effects such as the Mold Making cost is low, simple to operation have been obtained.
Description of drawings
Fig. 1 is the engineering view of blade grid;
Fig. 2 is the employed special-purpose metal die of the forming method of blade grid of the present invention;
Fig. 3 is that the A of Fig. 2 is to view;
Fig. 4 is the process chart of forming method of the present invention.
The specific embodiment
Below in conjunction with description of drawings the preferred embodiments of the present invention.
Fig. 1 is the engineering view of blade grid of the present invention, and as shown in Figure 1, the blade grid is made up of 72 different grid 101 of size dimension specification.
Because 72 grid size specification sizes of blade grid have nothing in common with each other, so adopt traditional metal die shop formable layer, die mould complexity, complex forming technology.Therefore, the invention provides a kind of forming method of blade grid, Fig. 4 is the process chart of forming method of the present invention, and shown in the embodiment of Fig. 4, method of the present invention comprises the steps:
Step 1: preparation special-purpose metal die,
According to the blade cell structure, design specialized metal die, Fig. 2 is the employed special-purpose metal die of the forming method of blade grid of the present invention, Fig. 3 is that the A of Fig. 2 is to view, as shown in Figures 2 and 3, in particular manufacturing craft, perpendicular baffle plate 201 and diaphragm plate 202 are inserted on the base 203 that has slot, thereby have formed 72 different grid of size specification.Each grid top is fixed by alignment pin 204, cushion block 205, top pressing board 206.
Step 2: preparation silicon rubber soft mode,
Use the R-311W liquid silastic to make soft mode, pour liquid silastic into mixing tank, mixing tank is vacuumized, require vacuum＜-0.9Mpa, and stirred fast 3～10 minutes.
The silicon rubber for preparing is poured into lentamente in the grid of blade grid special-purpose metal die of step 1 preparation, after top pressing board covers grid, room temperature was placed 20～30 hours, behind the silicon rubber vulcanization to be cast, took out the silicon rubber soft mode with 72 different size specification blade grid punch.
Step 3: the shop layer,
The preimpregnation cloth that composite is made is laid in the preimpregnation cloth that cuts respectively on the silicon rubber soft mode then according to the different size cutting of blade grid grid, and the lay number of plies of preimpregnation cloth is determined according to the thickness of blade grid.
Step 4: solidify,
The silicon rubber soft mode of the good preimpregnation cloth of lay is fixed in the metal die, covers cover plate, put into autoclave, heat up, pressurize, solidify after vacuumizing.
Curing mode is that the staged intensification is solidified, and autoclave is warming up to 100 ± 5 ℃, is incubated 1 hour; Be warming up to 140 ± 5 ℃ again, be incubated 1.5 hours; When mold temperature was increased to 95 ± 5 ℃, autoclave began pressurization, and pressure is 0.3 ± 0.1Mpa; When mold temperature was increased to 120 ± 5 ℃, pressure increased to 0.7 ± 0.1Mpa; Mold temperature is increased to 177 ± 3 ℃, is incubated 3 hours; Begin cooling subsequently, mold temperature is reduced to 90 ℃, and autoclave stops pressurization.
Step 5: the demoulding,
After being cooled to room temperature, take off 72 blade grid silicon rubber soft modes earlier, the composite material blade grid after will solidifying again takes out from the metal die.
Through evidence: the blade grid according to forming method is as mentioned above made, can satisfy following specification requirement:
1) grid can carry the radially weight of 1884.1Kg and radially outer 758.18Kg simultaneously, load with stepless action on the trellis of grid;
2) any one preposition guider must be stood inefficacy.Limit in mean pressure is 2.0055Kg/cm2, and maximum normal working pressure or limiting pressure are greater than [limiting pressure/1.5] or 1.3863Kg/cm2;
3) product size satisfies the assembling instructions for use;
4) serviceability temperature of blade grid reaches 120 ℃.
Claims (4)
1. the forming method of a composite material leaf grille for controlling speed of aviation aircraft is characterized in that, this method comprises the steps:
Step 1: preparation special-purpose metal die,
According to the blade cell structure, make metal die with different 72 grid of size specification;
Step 2: preparation silicon rubber soft mode,
The liquid silastic that configures is poured into lentamente in the grid of blade grid special-purpose metal die of step 1 preparation, after top pressing board covers grid, room temperature was placed 20～30 hours, behind the silicon rubber vulcanization to be cast, take out the silicon rubber soft mode of blade grid punch with 72 different size specifications;
Step 3: the shop layer,
The preimpregnation cloth that composite is made is laid in the preimpregnation cloth that cuts respectively on the silicon rubber soft mode then according to the different size cutting of blade grid grid, and the lay number of plies of preimpregnation cloth is determined according to the thickness of blade grid;
Step 4: solidify,
The silicon rubber soft mode of the good preimpregnation cloth of lay is fixed in the metal die, covers cover plate, put into autoclave, heat up, pressurize, solidify after vacuumizing;
Step 5: the demoulding,
After being cooled to room temperature, take off 72 blade grid silicon rubber soft modes earlier, the composite material blade grid after will solidifying again takes out from the metal die.
2. the forming method of blade grid as claimed in claim 1, it is characterized in that: described step 1: preparation special-purpose metal die, described metal die comprises: perpendicular baffle plate and diaphragm plate that metal material is made are inserted on the base that has slot, form 72 different grid of size specification; Each grid top is fixed by alignment pin, cushion block, top pressing board.
3. the forming method of blade grid as claimed in claim 1, it is characterized in that: described step 2: preparation silicon rubber soft mode, the configuration of described liquid silastic comprises: use the R-311W liquid silastic to make soft mode, pour liquid silastic into mixing tank, mixing tank is vacuumized, requirement vacuum＜-0.9Mpa, and stirred fast 3～10 minutes, be configured to liquid silastic.
4. the forming method of blade grid as claimed in claim 1 is characterized in that: described step 4: solidify, described curing mode is that the staged intensification is solidified, and concrete parameter is: autoclave is warming up to 100 ± 5 ℃, is incubated 1 hour; Be warming up to 140 ± 5 ℃ again, be incubated 1.5 hours; When mold temperature was increased to 95 ± 5 ℃, autoclave began pressurization, and pressure is 0.3 ± 0.1Mpa; When mold temperature was increased to 120 ± 5 ℃, pressure increased to 0.7 ± 0.1Mpa; Mold temperature is increased to 177 ± 3 ℃, is incubated 3 hours; Begin cooling subsequently, mold temperature is reduced to 90 ℃, and autoclave stops pressurization.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009100509947A CN101885215A (en) | 2009-05-12 | 2009-05-12 | Forming method of composite material leaf grille for controlling speed of aviation aircraft |
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| CN2009100509947A CN101885215A (en) | 2009-05-12 | 2009-05-12 | Forming method of composite material leaf grille for controlling speed of aviation aircraft |
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| CN101885215A true CN101885215A (en) | 2010-11-17 |
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| CN2009100509947A Pending CN101885215A (en) | 2009-05-12 | 2009-05-12 | Forming method of composite material leaf grille for controlling speed of aviation aircraft |
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102294831A (en) * | 2011-09-15 | 2011-12-28 | 上海晋飞复合材料科技有限公司 | Compression moulding method for prepreg |
| CN102601899A (en) * | 2012-04-01 | 2012-07-25 | 哈尔滨飞机工业集团有限责任公司 | Core of composite rib box molding mold of helicopter rudder and manufacturing method of core |
| CN103307021A (en) * | 2013-06-17 | 2013-09-18 | 北京理工大学 | Reverse engineering forming method of turbomachinery blade grid based on mixed material filling |
| CN104708835A (en) * | 2014-11-06 | 2015-06-17 | 上海复合材料科技有限公司 | RTM (resin transfer molding) molding method for carbon-fibre composite complex grid structure |
| CN105082557A (en) * | 2014-05-07 | 2015-11-25 | 深圳光启创新技术有限公司 | Manufacturing method of grating |
| CN105423116A (en) * | 2015-11-05 | 2016-03-23 | 江苏恒神股份有限公司 | Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood |
| CN106827585A (en) * | 2017-02-21 | 2017-06-13 | 江苏恒神股份有限公司 | A kind of forming method of carbon fibre composite grid |
| CN110696389A (en) * | 2019-11-20 | 2020-01-17 | 西安交通大学 | Fiber reinforced thermosetting composite material preformed body curing method |
| CN112172198A (en) * | 2019-07-03 | 2021-01-05 | 中国航发商用航空发动机有限责任公司 | Blade cascade forming die and blade cascade forming method |
-
2009
- 2009-05-12 CN CN2009100509947A patent/CN101885215A/en active Pending
Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102294831B (en) * | 2011-09-15 | 2014-05-14 | 上海晋飞复合材料科技有限公司 | Compression moulding method for prepreg |
| CN102294831A (en) * | 2011-09-15 | 2011-12-28 | 上海晋飞复合材料科技有限公司 | Compression moulding method for prepreg |
| CN102601899A (en) * | 2012-04-01 | 2012-07-25 | 哈尔滨飞机工业集团有限责任公司 | Core of composite rib box molding mold of helicopter rudder and manufacturing method of core |
| CN103307021B (en) * | 2013-06-17 | 2015-06-17 | 北京理工大学 | Reverse engineering forming method of turbomachinery blade grid based on mixed material filling |
| CN103307021A (en) * | 2013-06-17 | 2013-09-18 | 北京理工大学 | Reverse engineering forming method of turbomachinery blade grid based on mixed material filling |
| CN105082557A (en) * | 2014-05-07 | 2015-11-25 | 深圳光启创新技术有限公司 | Manufacturing method of grating |
| CN105082557B (en) * | 2014-05-07 | 2018-11-06 | 深圳光启创新技术有限公司 | The manufacturing method of grid |
| CN104708835A (en) * | 2014-11-06 | 2015-06-17 | 上海复合材料科技有限公司 | RTM (resin transfer molding) molding method for carbon-fibre composite complex grid structure |
| CN105423116A (en) * | 2015-11-05 | 2016-03-23 | 江苏恒神股份有限公司 | Hood adopting longitudinal-transverse reinforced rib structure and adopting RTM entire shaping technology and manufacturing method of hood |
| CN106827585A (en) * | 2017-02-21 | 2017-06-13 | 江苏恒神股份有限公司 | A kind of forming method of carbon fibre composite grid |
| CN112172198A (en) * | 2019-07-03 | 2021-01-05 | 中国航发商用航空发动机有限责任公司 | Blade cascade forming die and blade cascade forming method |
| CN112172198B (en) * | 2019-07-03 | 2022-02-22 | 中国航发商用航空发动机有限责任公司 | Blade cascade forming die and blade cascade forming method |
| CN110696389A (en) * | 2019-11-20 | 2020-01-17 | 西安交通大学 | Fiber reinforced thermosetting composite material preformed body curing method |
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Application publication date: 20101117 |