CN105172161A - Automatic fiber placement forming method for grid skin structure with part concave structure - Google Patents
Automatic fiber placement forming method for grid skin structure with part concave structure Download PDFInfo
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- CN105172161A CN105172161A CN201510521039.2A CN201510521039A CN105172161A CN 105172161 A CN105172161 A CN 105172161A CN 201510521039 A CN201510521039 A CN 201510521039A CN 105172161 A CN105172161 A CN 105172161A
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- fiber placement
- automatic fiber
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- 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
- B29C70/342—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 isostatic pressure
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- 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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/382—Automated fiber placement [AFP]
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- 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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
-
- 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
Abstract
The invention discloses an automatic fiber placement forming method for a grid skin structure with a part concave structure. The method comprises the following steps that a forming mold is selected; material is presoaked with the adoption of a hot melting method; presoaked fibers are prepared; placement in the thickened area of the part concave position and placement for other parts of a grid shell body are completed with the aid of hands by using the presoaked material; glue absorption is conducted in a hot-pressing pot; a first skin placement is conducted; skin glue absorption is conducted in the hot-pressing pot; a second skin placement is conducted; solidification is conducted; and polishing treatment is conducted, and automatic fiber placement forming for the grid skin structure with the part concave structure is completed. According to the method, the technical problem that automatic fiber placement can not be conducted in the concave position is solved, and the application of an automatic fiber placement technique on a composite typical structure component is achieved.
Description
Technical field
The present invention relates to a kind of automatic fiber placement forming method, belong to composite material process planning technology.
Background technology
External in composite material skin component series products extensive use automatic forming technology, its with automatic fiber placement technology for Typical Representative.Automatic fiber placement technology is that several preimpregnation silk multiaxis placement head (mechanical hand) is laid in mandrel surface according to the determined laying direction of designing requirement after pressure roller next part is a silk ribbon, compacting is shaped, and whole process is completed by computer measurement and control, coherent system.
The automatic fiber placement technology set advantage of Filament-wound Machine and automated tape-laying technology, according to the change of component body surface configuration, can cut off tow at any time, continues conveying tow, be applicable to the complex shaped components such as concave curved surface, convex surface, variable cross-section shaping when needing.The shaping composite conical shell class A of geometric unitA of external employing automatic fiber placement technology comprises the Cryogenic tank, Atlas5 type carrier rocket load adapter etc. of U.S. Minotaur rocket radome fairing, u.s. space shuttle.
At present, the grid reinforced structure that space industry is commonly used mostly is the assembly of simple revolving body or simple revolving body, and the automatic fiber placement of the grid ribbed lattice housing for the bent bus of non-analytic solutions and the grid stressed-skin construction with local concave configuration not yet relates to, many Technological adaptabilities improve or upgrading is necessary.
Summary of the invention
The technical problem that the present invention solves is: overcome the deficiencies in the prior art, a kind of grid stressed-skin construction automatic fiber placement forming method recessed with local is provided, solving cannot the technical problem of automatic fiber placement at lower recess, achieves the application of automatic fiber placement technology on composite typical structure part.
Technical solution of the present invention is: a kind of grid stressed-skin construction automatic fiber placement forming method recessed with local, comprises the steps:
(1) mould is chosen to;
(2) adopt hot melt prepreg, according to product three-dimensional digital model, the laying size of portion's recessed area of playing a game carries out accurate Calculation, and utilizes the accurate blanking of automatic blanking equipment;
(3) hot melt prepreg is adopted, according to product three-dimensional digital model, the preimpregnation silk quantity of the shaping use of estimation covering laying, and utilize preimpregnation silk to divide cutting device to prepare preimpregnation silk;
(4) manual laying and other part layings of grid stressed-skin construction of having assisted thickened area, recessed position, local of the prepreg of step (2) are utilized;
(5) in autoclave, carry out suction glue, adopt rigidity, flexible combination former, under local, recess is by pressing plate or pressure ring shaping;
(6) first time covering laying is carried out:
(6.1) for mould installs prolonged process ring additional, the preimpregnation silk of step (3) is utilized to adopt automatic fiber placement equipment to realize equal thickness covering lay, and without obvious bedding void in laying;
(6.2) covering is under local during recess lay, and first by unsettled for placement head lay, molding die surface or the prepreg of not lower with the local recess of pressure roller contact, and only carry out compacting at edge, thickened area, recessed position, local or prolonged process ring place;
(6.3) after each laying piddler completes, the preimpregnation silk of lower for local recess is cut off at non-compacting outer edge place, and by hand preimpregnation silk is carried out flange compaction treatment at local recessed area;
(7), after covering laying completes for the first time, in autoclave, carry out covering inhale glue, under local, recess is by pressure ring or pressing plate shaping, then by the coated compacting of outer die combinations;
(8) second time covering laying is carried out
By first time, the mode of covering laying carries out second time covering laying, thickness covering being reached design in advance.
(9) by the grid stressed-skin construction through above-mentioned steps process at hot pressing in-tank-solidification;
(11) after having solidified, carry out grinding process to grid stressed-skin construction, remove burrs on edges, the grid stressed-skin construction automatic fiber placement completing band local recessed is shaping.
When the dimension precision requirement of authorities subordinate recess is higher, after second time covering laying completes, under local, recess increase machine adds removal laying, and after the solidification is complete, carries out mechanical process to grid stressed-skin construction, and removal machine adds layer.
When inhaling glue in described step (5) in autoclave, inhale glue temperature 80 DEG C-85 DEG C, temperature retention time 60min, pressure 0.3MPa ± 0.02MPa.
When carrying out covering suction glue in described step (7) in autoclave, inhale glue temperature 70 C-90 DEG C, temperature retention time 60min-120min, pressure 0.3MPa-0.6MPa.
In described step (9) when hot pressing in-tank-solidification, solidification temperature 160 DEG C-180 DEG C, hardening time 6h-8h, solidifying pressure 0.6MPa-0.8MPa.
Compared to the prior art the present invention, has following beneficial effect:
For the grid covering member of band local concave configuration (as window and end frame), because automatic fiber placement technology cannot realize the covering laying compacting of local recessed area in shaping covering process, and be easy to covering recessed area edge and occur interference and collision, propose a kind of grid stressed-skin construction automatic fiber placement forming method being suitable for being with local concave configuration, solve the interference problem of recess automatic fiber placement head and mould under local, by the mode of placement head unsettled lay of recess under local, achieve the continuous lay of the grid stressed-skin construction laying track of band local concave configuration, ensure that shaping efficiency, and by manual auxiliary flange compacting and repeatedly suction glue shaping, the grid ribbed lattice housing full angle laying high-quality lay and the overall co-curing that achieve the bent bus of non-analytic solutions of band local concave configuration are shaping.
Accompanying drawing explanation
Fig. 1 is the inventive method flow chart;
Fig. 2 is lower end frame covering, strengthens district and rib ply sequence schematic diagram;
Fig. 3 is vertical end frame laying schematic diagram;
Fig. 4 is vertical end frame local matched moulds state;
Fig. 5 is vertical end frame local laying schematic diagram;
Fig. 6 is that covering inhales glue vertical end frame local matched moulds view;
Fig. 7 is solidification vertical end frame local matched moulds view;
Fig. 8 is that plot structure schematic diagram strengthened by window;
Fig. 9 is window local laying schematic diagram;
Figure 10 is that blocking tool view is inhaled in window local;
Figure 11 is window local covering laying schematic diagram;
Figure 12 is that covering inhales glue and solidification vertical end frame local matched moulds view.
Detailed description of the invention
The common requirement that taper (curved surface) the construction sections high-quality often adopted for space flight model is shaping and the technological gap of domestic composite material skin structure automatic moulding and the moulding process present situation of state's inner conical (curved surface) housing, the molding mode that one is suitable for the composite material grid stressed-skin construction being with local concave configuration (as window and vertical end frame) is proposed, adopt the mode that manual auxiliary automatic fiber placement is shaping, can realize being with the full angle laying of the composite material taper housing of local concave configuration (as window and vertical end frame) shaping.
As shown in Figure 1, the inventive method comprises the steps:
(1) mould is chosen to;
(2) adopt hot melt prepreg, according to product three-dimensional digital model, be converted into two dimensional surface laying geomery, the laying size of portion's recessed area of playing a game carries out accurate Calculation, and utilizes the accurate blanking of automatic blanking equipment;
(3) adopt hot melt prepreg, according to product three-dimensional digital model planning piddler track, covering laying preimpregnation silk quantity is calculated, and utilizes preimpregnation silk to divide cutting device to prepare preimpregnation silk;
(4) manual laying and other part layings of grid housing of having assisted thickened area, recessed position, local of the prepreg of step (2) are utilized;
(5) in autoclave, carry out suction glue pre-compacted, adopt rigidity, flexible combination former, under local, recess is by pressing plate or press strip shaping; Inhale glue temperature 80 DEG C-85 DEG C, temperature retention time 60min, pressure 0.3MPa ± 0.02MPa.
(6) first time covering laying is carried out:
(6.1) for mould installs prolonged process ring additional, the pneumatic pressure roller of employing automatic fiber placement equipment is exerted pressure, infrared lamps, utilizes automatic fiber placement equipment to realize equal thickness covering lay, and without obvious bedding void in laying; Now skin thickness is lower than the thickness designed in advance;
(6.2) covering is under local during recess lay, and first by unsettled for placement head lay, molding die surface or the prepreg of not lower with the local recess of pressure roller contact, and only carry out compacting at edge, thickened area, recessed position, local or prolonged process ring place;
(6.3) after each laying piddler completes, the preimpregnation silk of lower for local recess is cut off at non-compacting outer edge place, and by hand preimpregnation silk is carried out flange compaction treatment at local recessed area;
(7), after covering laying completes for the first time, in autoclave, carry out covering inhale glue, under local, recess is by press strip or pressing plate shaping, then by the coated compacting of outer die combinations; Inhale glue temperature 70 C-90 DEG C, temperature retention time 60min-120min, pressure 0.3MPa-0.6MPa.
(8) second time covering laying is carried out: the mode of covering laying carries out second time covering laying by first time, thickness covering being reached design in advance.
(9) by the grid stressed-skin construction through above-mentioned steps process at hot pressing in-tank-solidification, adopt rigidity former during solidification, solidification temperature 160 DEG C-180 DEG C, hardening time 6h-8h, solidifying pressure 0.6MPa-0.8MPa.；
(11) after having solidified, carry out grinding process to grid stressed-skin construction, remove burrs on edges, the grid stressed-skin construction automatic fiber placement completing band local recessed is shaping.
When the dimension precision requirement of authorities subordinate recess is higher, after second time covering laying completes, under local, recess increase machine adds removal laying, and after the solidification is complete, carries out mechanical process to grid stressed-skin construction, and removal machine adds layer.
Local recessedly comprises two large classes: closed and non-enclosed, closed take window as Typical Representative, non-enclosed with vertical end frame for Typical Representative, provide two embodiments for vertical end frame and window respectively below.
Embodiment 1: the grid stressed-skin construction of band vertical end frame is shaping
Vertical end frame forming requirements: component lower end frame is vertical end mount structure.For keeping covering laying continuous, in lower end frame thinning place's amendment laying scheme, opposite end frame thickeies laying and deletes, thickness is reduced to 11.5mm by 18.5mm along R8 radian.Be illustrated in figure 2 lower end frame covering, strengthen district and rib ply sequence schematic diagram.
Because vertical end frame and thickened area equal thickness are comparatively large, therefore need the material block first hot melt prepreg being paved into 5-7 layer, enter baking oven and inhale glue in advance, then size as required, carry out the blanking of material block, laying, autoclave suction glue.
Need lower loop be loaded onto during the coated suction glue of vertical end frame, inhale glue sizing die, to ensure its end frame circumferential surface flatness end frame laying hoop is fixing.
Before covering laying, vertical end frame must be strengthened inner thickened area, district paved complete.
(1) mould prepares
Installed by die assembly, prolonged process ring wouldn't be installed, cleaning die surface, and release agent application.
(2) prepreg blanking
Adopt hot melt prepreg.According to product three-dimensional digital model, by conversion, precise art is carried out to vertical end frame transition region laying size, and utilizes the accurate blanking of automatic blanking equipment.
(3) preimpregnation silk prepares
Adopt hot melt prepreg.According to product three-dimensional digital model, covering laying preimpregnation silk quantity is calculated, and utilizes preimpregnation silk to divide cutting device to prepare preimpregnation silk.
(4) vertical end frame laying
A. manual laying and other part layings of grid housing of having assisted Kuang Duankuang thickened area, lower end, vertical end frame position;
B. manual laying and other part layings of grid housing of having assisted lower end, vertical end frame position frame end frame ramp-transition zone;
Be illustrated in figure 3 the vertical end frame schematic diagram after laying.
(5) glue is inhaled
Inhale glue to carry out in autoclave, adopt rigidity, flexible combination former, at end, frame place increases pressure ring shaping, inhales glue temperature 80 DEG C-85 DEG C, temperature retention time 60min, pressure 0.3MPa ± 0.02MPa.Be illustrated in figure 4 and inhale glue vertical end frame local matched moulds view.
(6) first time covering laying is carried out:
Skin thickness 2.5mm, laying is [(± 45/0/ ± 30/0/ ± 30)/90 (1 layer)] s, adopts automatic fiber placement shaping.According to skin thickness, twice laying method is adopted to carry out paved, first time paving [(± 45/0/ ± 30/0/ ± 30)/90/ ± 30/0/ ± 30].
Should install prolonged process ring additional before component covering lay, it adopts 16 tow laies, carries out increase and decrease yarn and controls, realize equal thickness covering lay according to planned trajectory in laid course.Adopt pneumatic pressure roller to exert pressure in lay, adopt infrared lamps, good paving between laying is applied, without obvious bedding void.
Component covering, when vertical end frame place's lay, because its appearance and size is less relative to pressure roller size, first by unsettled for placement head lay, only carries out compacting at prolonged process ring place, and leaves the non-compacted region of 15mm at pressure ring near die side.Be illustrated in figure 5 vertical end frame local laying schematic diagram.
After each laying piddler completes, the preimpregnation silk at vertical end frame place is cut off at non-compacting outer edge place, and by hand preimpregnation silk is carried out flange compaction treatment in vertical end frame region.
(7) covering inhales glue
After first time, covering laying completed, carry out autoclave inhale glue pre-compacted, shaping.
Covering is inhaled glue and is carried out in autoclave, as required, increases the shaping of hoop press strip at vertical end frame place, then by the coated compacting of outer die combinations.Inhale glue temperature 70 C-90 DEG C, temperature retention time 60min-120min, pressure 0.3MPa-0.6MPa.Be illustrated in figure 6 covering and inhale glue vertical end frame local matched moulds view.
(8) second time covering laying is carried out
By first time, the mode of covering laying is carried out second time will to remain [± 45] paved.
(9) machine adds a layer laying
Vertical end frame dimension precision requirement is higher, and vertical end frame is reduced to 11.5mm by 18.5mm along R8 radian due to its overlay thickness, for ensureing radian, adopting winding to increase vertical end frame machine and adding removal laying, ensureing its precision after having solidified by machined.
(10) solidify
Product, at hot pressing in-tank-solidification, adopts rigidity former during solidification, solidification temperature 160 DEG C-180 DEG C, hardening time 6h-8h, solidifying pressure 0.6MPa-0.8MPa.Solidification vertical end frame local matched moulds view as shown in Figure 7.
(11) machined
After product goes out tank, carry out mechanical process, removal machine adds layer, and keeps vertical end frame size, carries out grinding process, removes burrs on edges, and the grid stressed-skin construction automatic fiber placement completing band vertical end frame is shaping.
Embodiment 2: the grid stressed-skin construction of band window is shaping
Window forming requirements: window strengthens district's straight forming out, but not products solidifying aft-loaded airfoil, its thickness has 20mm to fall sharply to 10mm at window edge, and edge is different from vertical end edge edge, and its laying edge needs perpendicular to covering.Be illustrated in figure 8 window and strengthen plot structure schematic diagram.
(1) mould prepares
Installed by die assembly, prolonged process ring wouldn't be installed, cleaning die surface, and release agent application.
(2) prepreg blanking
Adopt hot melt prepreg.According to product three-dimensional digital model, by conversion, precise art is carried out to window region laying size, and utilizes the accurate blanking of automatic blanking equipment.
(3) preimpregnation silk prepares
Adopt hot melt prepreg.According to product three-dimensional digital model, covering laying preimpregnation silk quantity is calculated, and utilizes preimpregnation silk to divide cutting device to prepare preimpregnation silk.
(4) window laying
A. manual laying and other part layings of grid housing of having assisted step thickened area in window;
B. manual laying and other part layings of grid housing of having assisted window outer step thickened area;
Be illustrated in figure 9 window local laying schematic diagram.
(5) glue is inhaled
Inhale glue to carry out in autoclave, adopt rigidity, flexible combination former, at window place, cap reforming is installed, inhale glue temperature 80 DEG C-85 DEG C, temperature retention time 60min, pressure 0.3MPa ± 0.02MPa.If Figure 10 is that blocking tool view is inhaled in window local.
(6) first time covering laying is carried out:
Skin thickness 2.5mm, laying is [(± 45/0/ ± 30/0/ ± 30)/90 (1 layer)] s, adopts automatic fiber placement shaping.According to skin thickness, twice laying method is adopted to carry out paved, first time paving [(± 45/0/ ± 30/0/ ± 30)/90/ ± 30/0/ ± 30].
Cover body covering lay adopts 16 tow laies, carries out increase and decrease yarn and controls, realize equal thickness covering lay according to planned trajectory in laid course.Adopt pneumatic pressure roller to exert pressure in lay, adopt infrared lamps, good paving between laying is applied, without obvious bedding void.
Cover body covering is when window place lay, and because its appearance and size is less relative to pressure roller size, first by unsettled for placement head lay, pressure roller does not contact with the window boss on segmental mandrel, only contacts with the compacting of window outer edge.
After each laying piddler completes, by the preimpregnation silk at window place in the window between region cut off perpendicular to machine direction, and manual preimpregnation silk is carried out flange compaction treatment at window area.
Be window local covering laying schematic diagram as shown in figure 11.
(7) covering inhales glue
After first time, covering laying completed, carry out autoclave inhale glue pre-compacted, shaping.
Covering is inhaled glue and is carried out in autoclave, as required, increases cap reforming at window place, then by the coated compacting of outer die combinations.Inhale glue temperature 70 C-90 DEG C, temperature retention time 60min-120min, pressure 0.3MPa-0.6MPa.
(8) second time covering laying is carried out:
By first time, the mode of covering laying carries out second time covering laying, will remain [± 45] paved.
(9) solidify
Product, at hot pressing in-tank-solidification, adopts rigidity former during solidification, solidification temperature 160 DEG C-180 DEG C, hardening time 6h-8h, solidifying pressure 0.6MPa-0.8MPa.Be solidification vertical end frame local matched moulds view as shown in figure 12.
(11) post processing
After product goes out tank, carry out grinding process, remove burrs on edges, the grid stressed-skin construction automatic fiber placement completing band window is shaping.
See embodiment 1 and embodiment 2, can complete the shaping of the grid stressed-skin construction of band window and vertical end frame, concrete glue number of times of inhaling can adjust as required.
The content be not described in detail in description of the present invention belongs to the known technology of professional and technical personnel in the field.
Claims (5)
1., with the grid stressed-skin construction automatic fiber placement forming method that local is recessed, it is characterized in that comprising the steps:
(1) mould is chosen to;
(2) adopt hot melt prepreg, according to product three-dimensional digital model, the laying size of portion's recessed area of playing a game carries out accurate Calculation, and utilizes the accurate blanking of automatic blanking equipment;
(3) hot melt prepreg is adopted, according to product three-dimensional digital model, the preimpregnation silk quantity of the shaping use of estimation covering laying, and utilize preimpregnation silk to divide cutting device to prepare preimpregnation silk;
(4) manual laying and other part layings of grid stressed-skin construction of having assisted thickened area, recessed position, local of the prepreg of step (2) are utilized;
(5) in autoclave, carry out suction glue, adopt rigidity, flexible combination former, under local, recess is by pressing plate or pressure ring shaping;
(6) first time covering laying is carried out:
(6.1) for mould installs prolonged process ring additional, the preimpregnation silk of step (3) is utilized to adopt automatic fiber placement equipment to realize equal thickness covering lay, and without obvious bedding void in laying;
(6.2) covering is under local during recess lay, and first by unsettled for placement head lay, molding die surface or the prepreg of not lower with the local recess of pressure roller contact, and only carry out compacting at edge, thickened area, recessed position, local or prolonged process ring place;
(6.3) after each laying piddler completes, the preimpregnation silk of lower for local recess is cut off at non-compacting outer edge place, and by hand preimpregnation silk is carried out flange compaction treatment at local recessed area;
(7), after covering laying completes for the first time, in autoclave, carry out covering inhale glue, under local, recess is by pressure ring or pressing plate shaping, then by the coated compacting of outer die combinations;
(8) second time covering laying is carried out
By first time, the mode of covering laying carries out second time covering laying, thickness covering being reached design in advance.
(9) by the grid stressed-skin construction through above-mentioned steps process at hot pressing in-tank-solidification;
(11) after having solidified, carry out grinding process to grid stressed-skin construction, remove burrs on edges, the grid stressed-skin construction automatic fiber placement completing band local recessed is shaping.
2. a kind of grid stressed-skin construction automatic fiber placement forming method recessed with local according to claim 1, it is characterized in that: when the dimension precision requirement of authorities subordinate recess is higher, after second time covering laying completes, under local, recess increase machine adds removal laying, and after the solidification is complete, carry out mechanical process to grid stressed-skin construction, removal machine adds layer.
3. a kind of grid stressed-skin construction automatic fiber placement forming method recessed with local according to claim 1, it is characterized in that: when inhaling glue in described step (5) in autoclave, inhale glue temperature 80 DEG C-85 DEG C, temperature retention time 60min, pressure 0.3MPa ± 0.02MPa.
4. a kind of grid stressed-skin construction automatic fiber placement forming method recessed with local according to claim 1, it is characterized in that: when carrying out covering suction glue in described step (7) in autoclave, inhale glue temperature 70 C-90 DEG C, temperature retention time 60min-120min, pressure 0.3MPa-0.6MPa.
5. a kind of grid stressed-skin construction automatic fiber placement forming method recessed with local according to claim 1, it is characterized in that: in described step (9) when hot pressing in-tank-solidification, solidification temperature 160 DEG C-180 DEG C, hardening time 6h-8h, solidifying pressure 0.6MPa-0.8MPa.
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| CN201510521039.2A CN105172161B (en) | 2015-08-21 | 2015-08-21 | It is a kind of with partially recessed grid stressed-skin construction automatic fiber placement forming method |
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| CN201510521039.2A CN105172161B (en) | 2015-08-21 | 2015-08-21 | It is a kind of with partially recessed grid stressed-skin construction automatic fiber placement forming method |
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| CN105172161B CN105172161B (en) | 2017-07-07 |
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| CN105643955A (en) * | 2016-03-21 | 2016-06-08 | 航天材料及工艺研究所 | High-precision copying method of carbon fiber composite space optical mirror plane |
| CN105690795A (en) * | 2016-03-21 | 2016-06-22 | 航天材料及工艺研究所 | Die and method for molding composite material of semi-closed cavity gridding stressed-skin structure |
| CN106515045A (en) * | 2016-12-18 | 2017-03-22 | 湖北三江航天江北机械工程有限公司 | Automatic laying molding method for composite connection skirt |
| CN108501398A (en) * | 2018-03-16 | 2018-09-07 | 航天材料及工艺研究所 | A kind of composite material casing, molding die and the forming method of the window containing in-flanges |
| CN109228394A (en) * | 2018-08-24 | 2019-01-18 | 中航复合材料有限责任公司 | A kind of quick molding method of composite material fuselage reinforcing rib |
| CN109278319A (en) * | 2018-08-10 | 2019-01-29 | 南京航空航天大学 | A kind of spread automatically for the twin pressure roller with rib revolving body twines molding machine |
| CN110591356A (en) * | 2019-09-11 | 2019-12-20 | 长春长光宇航复合材料有限公司 | Wave-transparent composite material half cover and preparation method thereof |
| CN110920643A (en) * | 2019-12-18 | 2020-03-27 | 常州市新创智能科技有限公司 | Plate body structure for guide plate |
| CN111196044A (en) * | 2018-11-16 | 2020-05-26 | 中航复合材料有限责任公司 | Compression molding method for carbon fiber composite material mechanical arm |
| CN112364402A (en) * | 2020-10-27 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Method for quickly generating curved surface mesh for laying simulation step |
| CN114311728A (en) * | 2021-10-29 | 2022-04-12 | 航天材料及工艺研究所 | Negative curvature composite material grid structural member and forming method thereof |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000048830A1 (en) * | 1999-02-16 | 2000-08-24 | Toray Industries, Inc. | Frp structure body and production method therefor |
| US20020056788A1 (en) * | 2000-11-15 | 2002-05-16 | Toyota Motor Sales, U.S.A. Inc. | One-piece closed-shape structure and method of forming same |
| US20030049431A1 (en) * | 1999-10-26 | 2003-03-13 | Hong Jin Crown Corporation, Ltd. | Dual-structure helmet and method of manufacturing the same |
| CN101450533A (en) * | 2007-11-30 | 2009-06-10 | 航天材料及工艺研究所 | Carbon fiber reinforcement resin base composite material lattice structural-component conforming die and method |
| CN103817953A (en) * | 2013-12-18 | 2014-05-28 | 中航复合材料有限责任公司 | Method for automatically laying tapes to manufacture composite material beam |
| CN103978698A (en) * | 2014-05-21 | 2014-08-13 | 航天材料及工艺研究所 | Method for forming composite conical shell with end frame |
-
2015
- 2015-08-21 CN CN201510521039.2A patent/CN105172161B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2000048830A1 (en) * | 1999-02-16 | 2000-08-24 | Toray Industries, Inc. | Frp structure body and production method therefor |
| US20030049431A1 (en) * | 1999-10-26 | 2003-03-13 | Hong Jin Crown Corporation, Ltd. | Dual-structure helmet and method of manufacturing the same |
| US20020056788A1 (en) * | 2000-11-15 | 2002-05-16 | Toyota Motor Sales, U.S.A. Inc. | One-piece closed-shape structure and method of forming same |
| CN101450533A (en) * | 2007-11-30 | 2009-06-10 | 航天材料及工艺研究所 | Carbon fiber reinforcement resin base composite material lattice structural-component conforming die and method |
| CN103817953A (en) * | 2013-12-18 | 2014-05-28 | 中航复合材料有限责任公司 | Method for automatically laying tapes to manufacture composite material beam |
| CN103978698A (en) * | 2014-05-21 | 2014-08-13 | 航天材料及工艺研究所 | Method for forming composite conical shell with end frame |
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| CN105690795A (en) * | 2016-03-21 | 2016-06-22 | 航天材料及工艺研究所 | Die and method for molding composite material of semi-closed cavity gridding stressed-skin structure |
| CN105690795B (en) * | 2016-03-21 | 2018-04-10 | 航天材料及工艺研究所 | A kind of semi-enclosed cavity grid stressed-skin construction composite material shaping mould and method |
| CN105643955A (en) * | 2016-03-21 | 2016-06-08 | 航天材料及工艺研究所 | High-precision copying method of carbon fiber composite space optical mirror plane |
| CN106515045A (en) * | 2016-12-18 | 2017-03-22 | 湖北三江航天江北机械工程有限公司 | Automatic laying molding method for composite connection skirt |
| CN106515045B (en) * | 2016-12-18 | 2019-02-15 | 湖北三江航天江北机械工程有限公司 | Composite material joint skirt automatic placement molding method |
| CN108501398B (en) * | 2018-03-16 | 2020-11-20 | 航天材料及工艺研究所 | Composite material shell containing inward flanging window, forming die and forming method |
| CN108501398A (en) * | 2018-03-16 | 2018-09-07 | 航天材料及工艺研究所 | A kind of composite material casing, molding die and the forming method of the window containing in-flanges |
| CN109278319A (en) * | 2018-08-10 | 2019-01-29 | 南京航空航天大学 | A kind of spread automatically for the twin pressure roller with rib revolving body twines molding machine |
| CN109278319B (en) * | 2018-08-10 | 2021-02-19 | 南京航空航天大学 | Double-pressure roller automatic laying and winding forming device for ridged revolving body |
| CN109228394A (en) * | 2018-08-24 | 2019-01-18 | 中航复合材料有限责任公司 | A kind of quick molding method of composite material fuselage reinforcing rib |
| CN109228394B (en) * | 2018-08-24 | 2020-12-29 | 中航复合材料有限责任公司 | Rapid forming method for composite material fuselage reinforcing rib |
| CN111196044A (en) * | 2018-11-16 | 2020-05-26 | 中航复合材料有限责任公司 | Compression molding method for carbon fiber composite material mechanical arm |
| CN110591356A (en) * | 2019-09-11 | 2019-12-20 | 长春长光宇航复合材料有限公司 | Wave-transparent composite material half cover and preparation method thereof |
| CN110591356B (en) * | 2019-09-11 | 2022-02-22 | 长春长光宇航复合材料有限公司 | Wave-transparent composite material half cover and preparation method thereof |
| CN110920643A (en) * | 2019-12-18 | 2020-03-27 | 常州市新创智能科技有限公司 | Plate body structure for guide plate |
| CN112364402A (en) * | 2020-10-27 | 2021-02-12 | 成都飞机工业（集团）有限责任公司 | Method for quickly generating curved surface mesh for laying simulation step |
| CN112364402B (en) * | 2020-10-27 | 2022-04-08 | 成都飞机工业（集团）有限责任公司 | Method for quickly generating curved surface mesh for laying simulation step |
| CN114311728A (en) * | 2021-10-29 | 2022-04-12 | 航天材料及工艺研究所 | Negative curvature composite material grid structural member and forming method thereof |
| CN114800969A (en) * | 2022-04-27 | 2022-07-29 | 江苏铁锚玻璃股份有限公司 | Device for accelerating polysulfide glue curing and use method thereof |
| CN114800969B (en) * | 2022-04-27 | 2023-07-28 | 江苏铁锚玻璃股份有限公司 | Device for accelerating curing of polysulfide glue and application method thereof |
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