CN108407330B - C-shaped section composite material bistable shell structure and forming die - Google Patents
C-shaped section composite material bistable shell structure and forming die Download PDFInfo
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- CN108407330B CN108407330B CN201810174454.9A CN201810174454A CN108407330B CN 108407330 B CN108407330 B CN 108407330B CN 201810174454 A CN201810174454 A CN 201810174454A CN 108407330 B CN108407330 B CN 108407330B
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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
-
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
Abstract
The invention provides a C-shaped section composite material bistable shell structure and a forming die, wherein the forming die consists of an air bag and a female die, the female die consists of an upper female die and a lower female die, the section profile contour line of the upper female die is formed by smoothly transiting a first arc profile line, a second arc profile line, a third arc profile line, a fourth arc profile line and a fifth arc profile line, the second arc profile line, the third arc profile line and the fourth arc profile line form a symmetrical arc concave structure, and the second arc profile line and the fourth arc profile line are symmetrically distributed on two sides of the third arc profile line and are semi-circles. According to the invention, through improving the design of the die structure, the quality problem of the irregular edge area caused by extrusion of the edge of the C-shaped section composite material bistable shell structure is solved.
Description
Technical Field
The invention relates to a C-shaped section composite material bistable shell structure and a forming die, and belongs to the technical field of composite material processing.
Background
The composite material bistable shell structure with the C-shaped cross section capable of being crimped and stabilized bidirectionally is a composite material shell structure capable of being crimped and stabilized bidirectionally. The bistable structure is mainly based on a shell structure, and means that the bistable structure can respectively keep a stable bending deformation state along two directions at different time along two directions of the surface of the shell structure. The bistable structure can be realized in two ways: one is to superpose and compound the shell structures in different bending directions layer by layer to form an integral shell structure, and the shell structures in different bending directions can influence the compounded shell structure in respective directions; and secondly, by mainly utilizing the anisotropy of the composite material, firstly performing a composite material shell structure, forming strain energy after the composite material shell structure is subjected to external force in a direction different from the bending direction of performing, and finally achieving a second stable state. Due to the fact that the bistable shell structure of the composite material is paid attention from abroad, series derivative products are researched and developed, various support functions can be achieved, and meanwhile low weight and rapid expansion can be guaranteed. The research, development and report of the product are not seen at present in China.
Bistable shell structures were first applied to satellite antennas in the 50's of the last century, and a metal-shell bistable structure invented by f.p.j.rimrott was crimped in both directions of the face and remained stable.in 2000, Iqbal K, Daton-L ovett et al published an article of bistable tubes made of composite material and applied for related patents in 2001, U.S. Pat. nos. US6217975 and US 6256938.
US6217975B1 describes an extensible hollow tube structure made of a composite of a reinforcing fiber fabric and a resin, and illustrates that the invention utilizes the characteristics of a composite material fiber lay-up to impart the bistable characteristic to the extensible hollow tube structure, and can realize curling in two directions, and the appearance of the extensible hollow tube structure is shown in fig. 5. The direction A is the state of the length direction, and at the moment, a tubular structure with an opening can be formed, and the direction B is the completely curled state, and a tubular structure wrapped layer by layer can be formed. When in the a state, the structure can be transformed into the B state by externally applying a pressure to the direction a; in the state B, the structure can be changed to the state a by applying a pulling force to the direction a from the outside.
US6256938B1 describes a bistable tube with a bayonet structure which allows self-closing. The structure is that a plurality of sawtooth structures are processed on the edge of the pipe wall along the direction 1, and when the opening of the pipe along the direction 1 is closed, the sawteeth on two sides are meshed with each other, so that the pipe forms a closed whole, and the integral strength and rigidity of the pipe are improved.
US6602574 describes a bistable tube with an internal supporting vane structure.
At present, a patent based on a bistable shell theory is mainly a composite material open pipe applied by Daton-L ovett, composite material fiber layering is simply mentioned in the patent, and a preparation method of the composite material fiber layering is not described in detail.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a C-shaped section composite bistable shell structure, a die and a method which can be formed by adopting an air bag.
The forming die comprises an air bag and a female die, wherein the female die comprises an upper female die and a lower female die, the profile contour line of the section of the upper female die is formed by smoothly transiting a first arc profile, a second arc profile, a third arc profile, a fourth arc profile and a fifth arc profile, the second arc profile, the third arc profile and the fourth arc profile form a symmetrical arc concave structure, the second arc profile and the fourth arc profile are symmetrically distributed on two sides of the third arc profile and are semicircular, the third arc profile is consistent with the profile line of the inner surface of the bistable shell structure with the C-shaped section, the arc length L is the width of a C-shaped opening of the bistable shell structure with the C-shaped section, the diameter D of the second arc profile and the fourth arc profile is larger than the thickness D of the bistable shell structure with the C-shaped section, the first arc profile and the fifth arc profile are symmetrically distributed on two sides of the bistable shell structure with the C-shaped section, and the diameter D of the second arc profile and the fourth arc profile are consistent with the thickness D of the bistable shell structure with the outer surface of the bistable shell structure with the C-shaped section.
The diameter D of the second arc-shaped line and the fourth arc-shaped line is 110-200% of the thickness D of the bistable shell structure of the composite material with the C-shaped section.
The section profile of the lower female die is a semicircle and is consistent with the outer surface of the C-shaped section composite material bistable shell structure.
The invention adopts the female die design with a special profile, so that the air bag process for preparing the convoluted closing body can be used for the non-section convoluted closing body, the arc concave structure can effectively relieve the irregularity of the edge area caused by the extrusion of the edge of the C-shaped structure during the forming, and the product quality is improved.
A C-shaped section composite material bistable shell structure is formed by adopting an air bag, two ends of a C-shaped opening are of semicircular structures, and the semicircular diameter of the semicircular structures is larger than the thickness of the C-shaped section composite material bistable shell structure.
Compared with the prior art, the invention has the beneficial effects that:
(1) according to the invention, through improving the design of the die structure, the quality problem of the irregular edge area caused by extruding the edge of the C-shaped section composite material bistable shell structure is solved;
(2) the invention adopts the air bag to form the non-section convoluted closing body, thus realizing high efficiency, low cost and high quality;
(3) the C-shaped opening is designed into a semicircular concave structure, so that the edge of the preformed body can be completely attached to the concave structure and limited, and the problems of distortion, corrugation and the like of the edge of the C-shaped structure caused by extrusion of the edge part of the preformed body when an air bag is pressurized can be avoided;
(4) the opening of the C-shaped section composite material bistable shell structure is specially designed, so that the C-shaped section composite material bistable shell structure can be formed by adopting an air bag.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a schematic view of a female mold of the present invention;
FIG. 3 is a schematic view of the product and bladder arrangement of the present invention;
FIG. 4 is a schematic view of the construction of the upper female mold of the present invention;
fig. 5 is a schematic view of a bistable shell structure.
Detailed Description
The present invention will be described in detail with reference to the following examples and accompanying drawings.
The invention provides a C-shaped cross section composite bistable shell structure 3 which can be formed by an air bag, as shown in figure 3, wherein two ends of a C-shaped opening are of semicircular structures, and the semicircular diameter of the C-shaped opening is larger than the thickness of the C-shaped cross section composite bistable shell structure. The outer profile of the C-shaped section composite material bistable shell structure is formed by the inner surface of a female die, and the inner profile is formed by the outer profile of an air bag.
As shown in fig. 1 and 2, the invention provides a forming mold of a C-shaped cross-section composite bistable shell structure, which comprises an air bag 2 and a female mold 1, wherein the female mold 1 comprises an upper female mold 11 and a lower female mold 12, as shown in fig. 4, a profile contour line of the cross section of the upper female mold is formed by smooth transition of a first arc-shaped profile 111, a second arc-shaped profile 112, a third arc-shaped profile 113, a fourth arc-shaped profile 114 and a fifth arc-shaped profile 115, the second arc-shaped profile 112, the third arc-shaped profile 113 and the fourth arc-shaped profile 114 form a symmetrical arc-concave structure, the second arc-shaped profile 112 and the fourth arc-shaped profile 114 are symmetrically distributed on two sides of the third arc-shaped profile 113 and are semi-circular structures, the third arc-shaped profile 113 is consistent with the inner surface profile of the C-shaped cross-section composite bistable shell structure 1, an arc length L is a C-shaped opening width of the C-shaped cross-section composite bistable shell structure, a diameter D of the second arc-shaped profile 112 and the fourth arc-shaped profile 114 is greater than a thickness D of a thickness of a C-shaped cross-section composite bistable shell structure 3, D is equal to a perimeter of a bistable shell structure formed by a perimeter of 70% of the bistable shell structure with a bistable composite shell structure having a bi-shaped cross-stable thickness of the C-shaped cross-stable shell structure.
The invention further provides a method for forming the C-shaped section composite material bistable shell structure, the C-shaped section composite material bistable shell structure is made of continuous fibers or fiber fabrics through multilayer layering, size change can be generated in the process of compacting the multilayer composite materials, in order to ensure the perimeter of the C-shaped structure, the perimeter of the C-shaped structure is ensured to be slightly smaller than the perimeter of the inner profile of the mold during layering design, and the perimeter of the composite material preformed through layering is 1-10% smaller than the perimeter of the inner profile of the female mold.
And after the female die is closed, the female die is fastened and fixed through bolts or an external fastening frame. The mould can be heated by a heating pipe or an oven, and the heating temperature is determined according to the type of the composite material matrix resin. For example, the curing temperature of epoxy resin is 60-200 ℃, the curing temperature of high-temperature resin such as bismaleimide resin, cyanate resin and the like is 180-220 ℃, and the heating curing time is relatively long, usually 60-180 minutes. If a thermoplastic matrix is adopted, the heating temperature needs to be ensured to be higher than the viscous flow temperature of the resin, and the resin and the fibers are ensured to be fully infiltrated. A longer cooling time is required after heating to prevent the product from deforming due to demoulding above the hardening temperature. The forming process needs to be controlled except heating and pressurizing, air mixed in the composite material laying layer is removed through repeated pressurizing for many times, and the product quality is guaranteed.
Example 1
The glass fiber laid cloth/epoxy resin prepreg is used as a material of a C-shaped structure, and the prepreg is firstly paved and molded according to design. Inflating and pressurizing the air bag, controlling the pressure to be 0.02-0.1bar, then paving the prepreg paving layer on the outer surface of the air bag, then loading the air bag into a female die, and closing the die and fastening. The temperature is gradually raised to the softening point of the resin, typically 30-80 ℃, during which the bladder pressure is maintained constant. After reaching the softening point temperature, the air bag is continuously pressurized, the pressure is increased to 0.05-0.3bar, the pressure is released to the initial pressure after 5 minutes of maintenance, and then the pressure is increased to 0.05-0.3 bar. Repeating the pressurizing process for 2-5 times, maintaining the pressure at 0.1-0.5bar, heating to 130 deg.C, maintaining the temperature for 120 min, cooling to 80 deg.C, and demolding.
Example 2
The glass fiber laid cloth/PA 66 prepreg is used as a material of a C-shaped structure, and the prepreg is firstly paved and molded according to design. Inflating and pressurizing the air bag, controlling the pressure to be 0.02-0.1bar, then paving the prepreg paving layer on the outer surface of the air bag, then loading the air bag into a female die, and closing the die and fastening. The temperature is gradually raised to the softening point temperature of the resin, typically at 160 ℃, during which the bladder pressure is maintained constant. After reaching the softening point temperature, the air bag is continuously pressurized, the pressure is increased to 0.05-0.3bar, the pressure is released to the initial pressure after 5 minutes of maintenance, and then the pressure is increased to 0.05-0.3 bar. Repeating the pressurizing process for 2-5 times, starting to increase the pressure to 0.1-0.5bar, then increasing the temperature to 130 ℃, keeping the temperature for 15 minutes, then reducing the temperature to below 60 ℃, and demoulding.
The invention has not been described in detail and is in part known to those of skill in the art.
Claims (7)
1. The utility model provides a forming die of bistable shell structure of C shape cross-section combined material which characterized in that: the double-layer composite shell structure is characterized by comprising an air bag and a female die, wherein the female die comprises an upper female die and a lower female die, the profile contour line of the section of the upper female die is formed by smoothly transiting a first arc profile, a second arc profile, a third arc profile, a fourth arc profile and a fifth arc profile, the second arc profile, the third arc profile and the fourth arc profile form a symmetrical arc concave structure, the second arc profile and the fourth arc profile are symmetrically distributed on two sides of the third arc profile and are semicircular, and the diameter D of the second arc profile and the fourth arc profile is greater than the thickness D of the C-shaped section composite bistable shell structure.
2. The forming die of the bistable shell structure of composite material with C-shaped section according to claim 1, wherein: the diameter D of the second arc-shaped line and the fourth arc-shaped line is 110-200% of the thickness D of the bistable shell structure of the composite material with the C-shaped section.
3. The mold for molding the bistable shell structure of composite material with C-shaped cross section according to claim 1, wherein the third arc-shaped profile is consistent with the profile of the inner surface of the bistable shell structure of composite material with C-shaped cross section, and the arc length L is the width of the C-shaped opening of the bistable shell structure of composite material with C-shaped cross section.
4. The forming die of the bistable shell structure of composite material with C-shaped section according to claim 1, wherein: the first arc-shaped line and the fifth arc-shaped line are symmetrically distributed on two sides of the arc-shaped concave structure, and the molded lines of the first arc-shaped line and the fifth arc-shaped line are consistent with the molded lines of the outer surface of the C-shaped section composite material bistable shell structure.
5. The forming die of the bistable shell structure of composite material with C-shaped section according to claim 1, wherein: the section profile of the lower female die is a semicircle and is consistent with the outer surface of the C-shaped section composite material bistable shell structure.
6. A C-section composite bistable shell structure prepared by using the molding die of claim 1, wherein: the inner molded surface of the bistable shell structure is formed by an air bag, the outer molded surface of the bistable shell structure is formed by a female die, the cross sections at two ends of the C-shaped opening are semicircular structures, and the diameter of each semicircle is 110-200% of the thickness of the bistable shell structure.
7. A C-section composite bistable shell structure according to claim 6, wherein: the thickness of the bistable shell structure is the average thickness of the area, which accounts for 70 to 90 percent of the perimeter of the cross section, in the middle of the bistable shell structure.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810174454.9A CN108407330B (en) | 2018-03-02 | 2018-03-02 | C-shaped section composite material bistable shell structure and forming die |
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| CN201810174454.9A CN108407330B (en) | 2018-03-02 | 2018-03-02 | C-shaped section composite material bistable shell structure and forming die |
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| CN108407330A CN108407330A (en) | 2018-08-17 |
| CN108407330B true CN108407330B (en) | 2020-07-10 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012168741A1 (en) * | 2011-06-09 | 2012-12-13 | Rtl Materials Ltd | Coilable extendible member and methods |
| CN107152603A (en) * | 2016-12-07 | 2017-09-12 | 航天特种材料及工艺技术研究所 | A kind of bistable state shell structure and its manufacture method |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012168741A1 (en) * | 2011-06-09 | 2012-12-13 | Rtl Materials Ltd | Coilable extendible member and methods |
| CN107152603A (en) * | 2016-12-07 | 2017-09-12 | 航天特种材料及工艺技术研究所 | A kind of bistable state shell structure and its manufacture method |
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| CN108407330A (en) | 2018-08-17 |
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