CN111559141A - Prestressed bistable composite material structure and manufacturing method thereof - Google Patents
Prestressed bistable composite material structure and manufacturing method thereof Download PDFInfo
- Publication number
- CN111559141A CN111559141A CN202010473673.4A CN202010473673A CN111559141A CN 111559141 A CN111559141 A CN 111559141A CN 202010473673 A CN202010473673 A CN 202010473673A CN 111559141 A CN111559141 A CN 111559141A
- Authority
- CN
- China
- Prior art keywords
- fiber
- bistable
- prestressed
- composite material
- 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.)
- Pending
Links
- 239000002131 composite material Substances 0.000 title claims abstract description 73
- 238000004519 manufacturing process Methods 0.000 title claims description 13
- 239000000835 fiber Substances 0.000 claims abstract description 102
- 239000004744 fabric Substances 0.000 claims abstract description 26
- 239000011347 resin Substances 0.000 claims abstract description 15
- 229920005989 resin Polymers 0.000 claims abstract description 15
- 238000000034 method Methods 0.000 claims abstract description 14
- 239000000463 material Substances 0.000 claims abstract description 8
- 238000005516 engineering process Methods 0.000 claims abstract description 7
- 238000007731 hot pressing Methods 0.000 claims abstract description 5
- 230000005284 excitation Effects 0.000 claims abstract description 4
- -1 polyethylene Polymers 0.000 claims description 12
- 238000010438 heat treatment Methods 0.000 claims description 8
- 239000004743 Polypropylene Substances 0.000 claims description 7
- 229920001155 polypropylene Polymers 0.000 claims description 7
- 239000003365 glass fiber Substances 0.000 claims description 6
- 244000198134 Agave sisalana Species 0.000 claims description 5
- 235000011624 Agave sisalana Nutrition 0.000 claims description 5
- 239000004698 Polyethylene Substances 0.000 claims description 5
- 229920000747 poly(lactic acid) Polymers 0.000 claims description 5
- 229920000573 polyethylene Polymers 0.000 claims description 5
- 239000004626 polylactic acid Substances 0.000 claims description 5
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 238000011084 recovery Methods 0.000 claims description 4
- 229920002748 Basalt fiber Polymers 0.000 claims description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 3
- 230000002457 bidirectional effect Effects 0.000 claims description 3
- 229910052796 boron Inorganic materials 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 229920001778 nylon Polymers 0.000 claims description 3
- 241000931705 Cicada Species 0.000 claims description 2
- 239000003822 epoxy resin Substances 0.000 claims description 2
- 239000002657 fibrous material Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 108090000623 proteins and genes Proteins 0.000 claims description 2
- 102000004169 proteins and genes Human genes 0.000 claims description 2
- 229920006305 unsaturated polyester Polymers 0.000 claims description 2
- 229920001567 vinyl ester resin Polymers 0.000 claims description 2
- 230000009466 transformation Effects 0.000 abstract description 4
- 238000000465 moulding Methods 0.000 abstract 1
- 230000008569 process Effects 0.000 description 10
- 230000007704 transition Effects 0.000 description 6
- 230000005489 elastic deformation Effects 0.000 description 4
- 238000002360 preparation method Methods 0.000 description 4
- 108010022355 Fibroins Proteins 0.000 description 3
- 239000004699 Ultra-high molecular weight polyethylene Substances 0.000 description 3
- 229920000785 ultra high molecular weight polyethylene Polymers 0.000 description 3
- 238000005452 bending Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000007935 neutral effect Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 239000004593 Epoxy Substances 0.000 description 1
- 239000004677 Nylon Substances 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
- B32B5/024—Woven fabric
-
- 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
- B29C70/345—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 matched moulds
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/06—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material
- B32B27/08—Layered products comprising a layer of synthetic resin as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/12—Layered products comprising a layer of synthetic resin next to a fibrous or filamentary layer
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/32—Layered products comprising a layer of synthetic resin comprising polyolefins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/36—Layered products comprising a layer of synthetic resin comprising polyesters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B27/00—Layered products comprising a layer of synthetic resin
- B32B27/38—Layered products comprising a layer of synthetic resin comprising epoxy resins
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/56—Folding or collapsing to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03D—WIND MOTORS
- F03D1/00—Wind motors with rotation axis substantially parallel to the air flow entering the rotor
- F03D1/06—Rotors
- F03D1/065—Rotors characterised by their construction elements
- F03D1/0675—Rotors characterised by their construction elements of the blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/02—Synthetic macromolecular fibres
- B32B2262/0253—Polyolefin fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/06—Vegetal fibres
- B32B2262/062—Cellulose fibres, e.g. cotton
- B32B2262/065—Lignocellulosic fibres, e.g. jute, sisal, hemp, flax, bamboo
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/08—Animal fibres, e.g. hair, wool, silk
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/101—Glass fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Sustainable Energy (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Textile Engineering (AREA)
- Remote Sensing (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention provides a novel prestressed bistable composite material thin shell structure, which comprises a thin shell formed by hot pressing of composite fiber layering, wherein the composite fiber comprises fiber layering processed by a prestressed technology, the composite fiber layering material comprises long fiber fabric and resin, the bistable structure can stably exist under stretching and curling configurations, can realize repeated transformation of the stable structure under external excitation, and can be used as a safety hinge assembly structure. The invention provides a method for preparing a bistable composite material structure based on a fiber prestress technology, which comprises the steps of carrying out prestress treatment on fibers; layering and die assembly of the composite material; hot-pressing curing molding of the composite material structure; demolding and pretreating. The internal stress of the structure can be adjusted under the condition of not increasing the material quality and the geometric configuration, the comprehensive performance of the bistable structure is fundamentally improved, the stable state and the deformation characteristic of the structure are adjusted and controlled, and the bistable structure has greater advantages in the fields of aerospace and the like.
Description
Technical Field
The invention relates to the technical field of mechanical structures, in particular to a design and manufacturing method of a thin shell structure made of a prestressed bistable composite material.
Background
The bistable composite material structure is a thin shell structure prepared based on a high-molecular-group composite material, has two stable configurations of stretching and curling, and can realize repeated transformation of the stable configurations under external excitation. Due to the advantages of the structure in the aspects of light weight, corrosion resistance, simplification of a traditional mechanical hinge mechanism, optimization of aerodynamic efficiency and the like, the structure has high economic value and wide application prospect in the aspects of design and manufacture of extensible/foldable three-dimensional structures with large expansion ratio, which are not only used for aircraft landing gears, but also constructed for aircraft wings, large-scale wind driven generator blades and aerospace. However, with the development of the aerospace industry, higher requirements are put forward on the tensile/compressive capacity of a deformable structure, and the improvement of the mechanical property and the functional property of the structure is urgently needed to adapt to the increasing design requirements.
Disclosure of Invention
The invention improves the problems, namely the technical problem to be solved by the invention is the uncontrollable property of the stable state configuration and the deformation characteristic of the bistable composite material structure.
The specific embodiment of the invention is as follows: the novel prestressed bistable composite shell structure comprises a shell formed by hot pressing composite fiber layers, wherein the composite fibers comprise fiber layers processed by a prestress technology, and the composite fiber layer material comprises long fiber fabrics and resin.
Further, the prestressing technology is to apply prestress to the fiber layup within the yield limit of the fiber, and the fiber undergoes elastic or visco-elastic recovery after the prestress is removed, and generates compressive stress inside the thin shell structure, so that the structural internal stress realizes the transition from tensile stress to zero and then to compressive stress.
Further, the fiber fabric is brittle fiber or tough fiber, and the resin is any one of epoxy resin, unsaturated polyester, vinyl ester resin, polyethylene, polypropylene and polylactic acid resin.
Further, the brittle fiber is one of glass fiber, carbon fiber, boron fiber or basalt fiber; the tough fiber is one of nylon fiber, polyethylene fiber, polypropylene fiber, cicada silk protein fiber or hemp plant fiber.
Furthermore, when the fiber fabric is a bidirectional fiber fabric, the ply adopts a symmetrical ply structure, the fiber fabric is a unidirectional fiber fabric, and the ply adopts a reverse symmetrical ply structure.
Further, the thin shell structure is prepared into a pipe body with an opening and can be axially curled to another stable shape under external excitation in an extension state.
The invention also designs a manufacturing method of the novel prestressed bistable composite material thin shell structure, which comprises two manufacturing methods of an elastic prestressed bistable composite material structure and a viscoelasticity prestressed bistable composite material structure based on the prestress principle of different fiber materials:
the manufacturing steps of the elastic prestressed bistable composite material structure are as follows:
(1) pre-stressing a particular fibre lay within the yield limit of the fibre;
(2) under the premise of keeping the prestress level, preparing a composite material layer according to the design requirement, and placing the composite material layer in a forming mold;
(3) heating and pressurizing the mould to solidify and form the mould;
(4) unloading the fiber prestress;
(5) demolding and pretreating the product;
the manufacturing steps of the viscoelastic prestress bistable composite material structure are as follows:
(1) pre-stressing a particular fibre lay within the yield limit of the fibre;
(2) unloading the prestress to enable the fiber to be in a viscoelasticity recovery stage;
(3) preparing a composite material layer according to design requirements, and placing the composite material layer in a forming mold;
(4) heating and pressurizing the mould to solidify and form the mould;
(5) demolding and pre-treating the product.
Compared with the prior art, the invention has the following beneficial effects: the invention provides a method for preparing a bistable composite material structure based on a fiber prestress technology, which can realize the adjustment of the internal stress of the structure under the condition of not increasing the mass and the geometric configuration of the material, fundamentally improve the comprehensive performance of the bistable structure, realize the regulation and control of the stable state and the deformation characteristic of the structure and bring greater advantages into play in the fields of aerospace and the like.
Drawings
FIG. 1 is a schematic representation of several stable configurations of the structures of the present invention;
FIG. 2 is a schematic diagram of a structural preparation scheme of the elastic prestressed bistable composite material of the present invention.
Fig. 3 is a schematic view of a preparation scheme of the viscoelastic prestressed bistable composite material structure of the present invention.
Fig. 4 is a schematic diagram illustrating deformation characteristics of the prestressed bistable structure during folding process.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The invention relates to a novel prestressed bistable composite shell structure, which comprises a shell formed by hot pressing composite fiber plies, wherein the composite fibers comprise fiber plies subjected to prestress technical treatment, the composite fiber ply material comprises long fiber fabrics and resin, the prestress technical treatment is to apply prestress to the fiber plies within the yield limit of the fibers, the fibers can be recovered through elasticity or viscoelasticity after the prestress is removed, and compressive stress is generated inside the shell structure, so that the structural internal stress realizes the transformation from tensile stress to zero and then to the compressive stress.
The elastic prestress bistable composite material structure is suitable for fragile fibers such as glass fibers, carbon fibers, boron fibers and basalt fibers. The viscoelastic prestress bistable composite material structure is suitable for tough fibers such as nylon, polyethylene, polypropylene, fibroin and hemp plant fibers, a fibroin fiber or hemp plant fiber reinforced polylactic acid resin system is utilized to prepare a green degradable bistable composite material structure, and a bidirectional fiber fabric is utilized, and a symmetrical layering design can be adopted for a composite material structure layering; with unidirectional fiber fabric, the composite structure plies may be in a antisymmetric ply design.
As shown in fig. 1, the bistable composite structure is comprised of two main stable configurations, namely an extended configuration and a crimped configuration. According to the invention, through the design of a composite material microscopic structure, the deformation characteristics of the composite material structure in the transformation process of two stable configurations are regulated and controlled by utilizing a fiber prestress technology, according to the expression form of the structural internal stress level, the intermediate configuration of the structure can be a stable configuration or exist in an unstable transition form, the folding configuration of the bistable structure is also a stable form, and the stable gradient of the folding configuration is closely related to the internal stress.
The bistable structure can be folded up progressively under large deformation, as shown in figure 4. The folding of the structure starts from elastic bending deformation, then generates the coupling effect of torsion and buckling, after reaching critical stress, the structure generates instantaneous jump, and then is gradually folded under the action of constant bending moment.
In the description of the present invention, the subscript 'p' in the ply sequence indicates that the corresponding fiber plies have been pre-stressed.
Example 1
This example is an elastic prestressed bistable composite structure made of plain weave fiber fabric.
Layering sequence: [ +/-45 p/+/-45 p ]
Composite material base material: the plain weave glass fiber cloth reinforces polypropylene resin.
The preparation method comprises the following steps:
step (1) prestress is applied to the fiber paving layer: applying prestress to the specific fiber layer through fiber prestress equipment;
layering in step (2): on the basis of maintaining the fiber prestress level, preparing a composite material layer according to the layer design requirement, placing the composite material layer in a compression molding die, and closing the die;
step (3), heating, pressurizing and curing: heating and pressurizing the mould for curing, wherein the curing temperature is 205 ℃, and the curing time is 4 hours;
step (4) unloading prestress: unloading the prestress of the fibers after the composite material is solidified and cooled;
step (5), demolding: demoulding to obtain the elastic prestress bistable composite material structure, and pretreating the product.
The elastic prestressed bistable composite material structure prepared by the embodiment has three deformation characteristics according to the elastic deformation level of the solidification locking in the composite material structure: when the elastic deformation is smaller or zero, the curling/folding process is passive, namely the intermediate configuration of the structure exists in an unsteady state transition form, and continuous and stable energy input is required until the second steady state configuration of the structure is reached; when the elastic deformation is changed into a medium level, the internal stress of the structural surface is zero, and the deformation characteristic of the structural surface in the curling/folding process is a neutral stable configuration, namely the intermediate state configuration of the structure exists in a stable state; when the elastic deformation is large, the curling/folding process of the structure is active, namely, the intermediate configuration of the structure exists in an unsteady state transition form, and the structure can be actively deformed to the second steady state configuration after starting to curl/fold.
Example 2: this example differs from example 1 in that a different fiber lay-up, [ + -45/0 p/+ -45], was used with unidirectional glass fiber cloth for the mid-plane of the structure and pre-stressed.
Example 3: this example differs from example 1 in that the fibrous reinforcement is a unidirectional glass fiber cloth, is antisymmetrically laid-up [45/-45/0p/45/-45], and is prestressed to the midplane fiber layers.
Example 4: this example differs from example 1 in that the composite material used is a plain carbon fiber cloth reinforced epoxy prepreg.
Example 5: this embodiment is a viscoelastic prestressed bistable composite structure prepared by using plain weave fiber fabric.
Layering sequence: [ + -45 p/+ -45 p ].
Composite material base material: the plain weave ultra-high molecular weight polyethylene fiber cloth reinforces polypropylene resin.
The preparation method comprises the following steps:
step (1) prestress is applied to the fiber paving layer: applying prestress to the specific fiber layer through fiber prestress equipment;
step (2) unloading prestress: after a certain time, unloading the prestress of the fibers;
layering in step (3): preparing a composite material layer according to the layer design requirement, and fixing the layer in a mould by using a heat shrinkable adhesive tape;
step (4), heating, pressurizing and curing: heating and pressurizing the mould for curing, wherein the curing temperature is 205 ℃, and the curing time is 4 hours;
step (5), demolding: demoulding to obtain the viscoelastic prestress bistable composite material structure, and pretreating the product.
The viscoelastic prestress bistable composite material structure prepared by the embodiment has three deformation characteristics according to the viscoelastic deformation level of the curing locking in the composite material structure: when the viscoelastic deformation is small or zero, the curling or folding process is passive, namely the intermediate configuration of the structure exists in an unsteady state transition form, and continuous and stable energy input is required until a second steady state configuration of the structure is reached; when the viscoelasticity deformation is changed to a medium level, the internal stress of the structural surface is zero, and the deformation characteristic of the structural surface in the curling or folding process is a neutral stable configuration, namely the intermediate state configuration of the structure exists in a stable state; when the viscoelastic deformation is large, the curling/folding process of the structure is active, i.e. the intermediate configuration of the structure exists in an unsteady state transition form, and the structure can be actively deformed to the second steady state configuration after starting to curl or fold.
Example 6: this example differs from example 5 in that a different fiber lay-up, [ + -45/0 p/+ -45], was used with unidirectional ultra high molecular weight polyethylene fibers in the mid-plane of the structure and pre-stressed.
Example 7: this example differs from example 5 in that the fibrous reinforcement was a unidirectional ultra high molecular weight polyethylene fiber cloth, and was antisymmetrically layered, [45/-45/0p/45/-45], and the midplane fiber layers were pre-stressed.
Example 8: the difference between this example and example 5 is that the composite material used is plain fibroin fiber cloth reinforced polylactic acid resin system, and is characterized by a green degradable bistable composite material structure.
Example 9: this example differs from example 5 in that the composite material used was a plain hemp plant fiber cloth reinforced polylactic acid resin system featuring a green degradable bistable composite structure.
The above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art will recognize that changes may be made in the form and details of the embodiments or may be made without departing from the spirit or scope of the invention; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Any embodiment disclosed herein above is meant to disclose, unless otherwise indicated, all numerical ranges disclosed as being preferred, and any person skilled in the art would understand that: the preferred ranges are merely those values which are obvious or representative of the technical effect which can be achieved. Since the numerical values are too numerous to be exhaustive, some of the numerical values are disclosed in the present invention to illustrate the technical solutions of the present invention, and the above-mentioned numerical values should not be construed as limiting the scope of the present invention.
If the invention discloses or relates to parts or structures which are fixedly connected to each other, the fixedly connected parts can be understood as follows, unless otherwise stated: a detachable fixed connection (for example using bolts or screws) is also understood as: non-detachable fixed connections (e.g. riveting, welding), but of course, fixed connections to each other may also be replaced by one-piece structures (e.g. manufactured integrally using a casting process) (unless it is obviously impossible to use an integral forming process).
In addition, terms used in any technical solutions disclosed in the present invention to indicate positional relationships or shapes include approximate, similar or approximate states or shapes unless otherwise stated.
Any part provided by the invention can be assembled by a plurality of independent components or can be manufactured by an integral forming process.
Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present invention and not to limit the same; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art will understand that: modifications to the specific embodiments of the invention or equivalent substitutions for parts of the technical features may be made; without departing from the spirit of the present invention, it is intended to cover all aspects of the invention as defined by the appended claims.
Claims (7)
1. The novel prestressed bistable composite shell structure is characterized by comprising a shell formed by hot pressing composite fiber layers, wherein the composite fibers comprise fiber layers processed by a prestressed technology, and the composite fiber layer material comprises long fiber fabrics and resin.
2. The novel prestressed bistable composite shell structure according to claim 1, wherein said prestressing technique is characterized in that the fiber lay-up is prestressed within the yield limit of the fiber, and after the prestressing is removed, the fiber undergoes elastic or visco-elastic recovery and generates a compressive stress inside the shell structure, so that the structural internal stress is transformed from a tensile stress to zero and then to a compressive stress.
3. The prestressed bistable thin shell structure according to claim 1, wherein said fiber fabric is brittle fiber or tough fiber, and said resin is any one of epoxy resin, unsaturated polyester, vinyl ester resin, polyethylene, polypropylene, and polylactic acid resin.
4. The prestressed bistable thin shell structure of claim 3, wherein said brittle fiber is one of glass fiber, carbon fiber, boron fiber or basalt fiber; the tough fiber is one of nylon fiber, polyethylene fiber, polypropylene fiber, cicada silk protein fiber or hemp plant fiber.
5. The prestressed bistable shell structure of claim 1, wherein when said fiber fabric is a bidirectional fiber fabric, the ply adopts a symmetrical ply structure; when the fiber fabric is a unidirectional fiber fabric, the layering adopts a antisymmetric layering structure.
6. The prestressed bistable shell structure of claim 2, wherein said shell structure is prepared as a tube with openings and is capable of being axially crimped to another stable configuration under external excitation in an extended state.
7. A method for manufacturing a bistable thin-shell structure according to any of claims 1 to 6, characterized in that the manufacturing method comprises two manufacturing methods of an elastically prestressed bistable composite structure and a viscoelastically prestressed bistable composite structure based on the principle of prestressing different fiber materials:
the manufacturing steps of the elastic prestressed bistable composite material structure are as follows:
(1) pre-stressing a particular fibre lay within the yield limit of the fibre;
(2) under the premise of keeping the prestress level, preparing a composite material layer according to the design requirement, and placing the composite material layer in a forming mold;
(3) heating and pressurizing the mould to solidify and form the mould;
(4) unloading the fiber prestress;
(5) demolding and pretreating the product;
the manufacturing steps of the viscoelastic prestress bistable composite material structure are as follows:
(1) pre-stressing a particular fibre lay within the yield limit of the fibre;
(2) unloading the prestress to enable the fiber to be in a viscoelasticity recovery stage;
(3) preparing a composite material layer according to design requirements, and placing the composite material layer in a forming mold;
(4) heating and pressurizing the mould to solidify and form the mould;
(5) demolding and pre-treating the product.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010473673.4A CN111559141A (en) | 2020-05-29 | 2020-05-29 | Prestressed bistable composite material structure and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010473673.4A CN111559141A (en) | 2020-05-29 | 2020-05-29 | Prestressed bistable composite material structure and manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111559141A true CN111559141A (en) | 2020-08-21 |
Family
ID=72069259
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010473673.4A Pending CN111559141A (en) | 2020-05-29 | 2020-05-29 | Prestressed bistable composite material structure and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111559141A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113276440A (en) * | 2021-05-24 | 2021-08-20 | 哈尔滨工业大学 | Preparation method and unfolding and recycling method of thin-wall column shell structure |
| CN114852372A (en) * | 2022-07-06 | 2022-08-05 | 沈阳建筑大学 | Aerospace variant aircraft with folding wing function and launching system thereof |
| CN114889164A (en) * | 2022-05-09 | 2022-08-12 | 福州大学 | Composite material tape and laminated plate structure prestress regulating device |
| CN114889276A (en) * | 2022-04-24 | 2022-08-12 | 东华大学 | Flexible bistable thin film mechanism based on photoresponse and preparation method and application thereof |
-
2020
- 2020-05-29 CN CN202010473673.4A patent/CN111559141A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113276440A (en) * | 2021-05-24 | 2021-08-20 | 哈尔滨工业大学 | Preparation method and unfolding and recycling method of thin-wall column shell structure |
| CN114889276A (en) * | 2022-04-24 | 2022-08-12 | 东华大学 | Flexible bistable thin film mechanism based on photoresponse and preparation method and application thereof |
| CN114889276B (en) * | 2022-04-24 | 2023-02-24 | 东华大学 | Flexible bistable film mechanism based on photoresponse and preparation method and application thereof |
| CN114889164A (en) * | 2022-05-09 | 2022-08-12 | 福州大学 | Composite material tape and laminated plate structure prestress regulating device |
| CN114889164B (en) * | 2022-05-09 | 2023-11-21 | 福州大学 | Composite tape and laminated board structure prestress regulating device |
| CN114852372A (en) * | 2022-07-06 | 2022-08-05 | 沈阳建筑大学 | Aerospace variant aircraft with folding wing function and launching system thereof |
| CN114852372B (en) * | 2022-07-06 | 2022-09-09 | 沈阳建筑大学 | Aerospace variant aircraft with folding wing function and launching system thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111559141A (en) | Prestressed bistable composite material structure and manufacturing method thereof | |
| EP2441571B1 (en) | Proces for manufacturing a composite component | |
| Li et al. | A review on the tooling technologies for composites manufacturing of aerospace structures: materials, structures and processes | |
| Cheng et al. | 3D printed continuous fiber reinforced composite lightweight structures: A review and outlook | |
| Liu et al. | A novel free-hanging 3D printing method for continuous carbon fiber reinforced thermoplastic lattice truss core structures | |
| EP2357075B1 (en) | Method for manufacturing a complex-geometry panel with pre-impregnated composite material | |
| CN110510103B (en) | Aircraft flexible composite material skin and preparation method thereof | |
| US20140166208A1 (en) | Preforming pre-preg | |
| Khosravani | Composite materials manufacturing processes | |
| CN104589672A (en) | Preparation method of shape memory composite material | |
| CN102092135A (en) | Method for improving rigidity of wing surface structure of composite material | |
| CN113427793B (en) | High-strength high-temperature-resistant composite material air inlet channel and forming method thereof | |
| EP2909009A1 (en) | An integrated curved structure and winglet strength enhancement | |
| CN102924741A (en) | Method for enhancing surface abrasion resistance of liquid molding composite material | |
| CN105189093A (en) | Multi-component composite structures | |
| CN108908964B (en) | Method for manufacturing fiber reinforced resin matrix composite laminated board | |
| Balasubramanian | Introduction to composite materials | |
| Nallusamy et al. | Influence of 2–10 wt% of SMA Nitinol Reinforcement on the Mechanical Properties of Glass–Epoxy Composites Manufactured Through the VARTM Process | |
| CN102653133B (en) | Folded structure of pre-impregnated fabric and forming method thereof | |
| GB2500699A (en) | Composite morphing skin for an aircraft | |
| DE102014119160A1 (en) | molding compound | |
| EP2644361A1 (en) | Composite material suitable for a morphing skin | |
| Ahmad et al. | Introduction to polymer composites | |
| US20220009128A1 (en) | Method for manufacturing a fibre preform | |
| Sun et al. | Cotton-bamboo composite material and structure applications |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20200821 |