AU2020101411A4 - Multistage winding technique of composite material - Google Patents

Multistage winding technique of composite material Download PDF

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Publication number
AU2020101411A4
AU2020101411A4 AU2020101411A AU2020101411A AU2020101411A4 AU 2020101411 A4 AU2020101411 A4 AU 2020101411A4 AU 2020101411 A AU2020101411 A AU 2020101411A AU 2020101411 A AU2020101411 A AU 2020101411A AU 2020101411 A4 AU2020101411 A4 AU 2020101411A4
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AU
Australia
Prior art keywords
sandwich structure
winding technique
composite material
inner layer
utilizing
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AU2020101411A
Inventor
Jianzhong Chen
Li Huang
Yong LV
Xiaoyu Zhang
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Wuhan University of Technology WUT
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Wuhan University of Technology WUT
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Priority to AU2020101411A priority Critical patent/AU2020101411A4/en
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Classifications

    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/56—Winding and joining, e.g. winding spirally
    • B29C53/58—Winding and joining, e.g. winding spirally helically
    • B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
    • B29C53/62—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels rotatable about the winding axis
    • B29C53/66—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels rotatable about the winding axis with axially movable winding feed member, e.g. lathe type winding
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/56—Winding and joining, e.g. winding spirally
    • B29C53/58—Winding and joining, e.g. winding spirally helically
    • B29C53/60—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels
    • B29C53/62—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels rotatable about the winding axis
    • B29C53/66—Winding and joining, e.g. winding spirally helically using internal forming surfaces, e.g. mandrels rotatable about the winding axis with axially movable winding feed member, e.g. lathe type winding
    • B29C53/665—Coordinating the movements of the winding feed member and the mandrel
    • 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
    • B29C70/06—Fibrous reinforcements only
    • B29C70/10—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres
    • B29C70/16—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length
    • B29C70/22—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure
    • B29C70/222—Fibrous reinforcements only characterised by the structure of fibrous reinforcements, e.g. hollow fibres using fibres of substantial or continuous length oriented in at least two directions forming a two dimensional structure the structure being shaped to form a three dimensional configuration
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/14—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers
    • B32B37/15—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state
    • B32B37/153—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers with at least one layer being manufactured and immediately laminated before reaching its stable state, e.g. in which a layer is extruded and laminated while in semi-molten state at least one layer is extruded and immediately laminated while in semi-molten state
    • 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
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/03—3 layers
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/20—All layers being fibrous or filamentary
    • 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
    • B32B2250/00—Layers arrangement
    • B32B2250/40—Symmetrical or sandwich layers, e.g. ABA, ABCBA, ABCCBA
    • 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
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B32B2260/046—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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/10—Fibres of continuous length

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Textile Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

The present invention discloses a multistage winding technique of a composite material, and relates to the technical field of fabrication of composite materials. The multistage winding technique of a composite material comprises the following steps: firstly, fabricating an inner layer of a sandwich structure by utilizing a winding technique; before the inner layer of the sandwich structure is cured, fabricating an interlayer of the sandwich structure at the exterior of the inner layer of the sandwich structure by utilizing a multistage winding technique; before the interlayer of the sandwich structure is cured, fabricating an outer layer of the sandwich structure at the exterior of the interlayer of the sandwich structure by utilizing the winding technique. The present invention can fully exert the high efficiency of the winding technique, and can efficiently fabricate the sandwich structure or a lattice structure of the composite material. Additionally, the inner layer and the outer layer of the fabricated sandwich structure are reliably connected, and is unlikely to separate. 90° Wrap Angle Ov Mandrel 90° Axis Translates Fiber Placement otationHead Fibers Resin Bath (Continuous) FIG. 1 C) Roving Rack Release Film Drive Unit Finished Pipe Panel -Curing Oven With Exhaust Fan Mixing Tanks Surface Mat ~ Top View Winding Equipment MeteringPumps FIG. 2 LG LL LL LLLLL FIG. 3

Description

90° Wrap Angle
Ov Mandrel
90° Axis
Translates Fiber Placement
otationHead Fibers Resin Bath (Continuous)
FIG. 1
C) Roving Rack
Release Film
Drive Unit
Finished Pipe Panel -Curing Oven With Exhaust Fan
Mixing Tanks Surface Mat
~ Top View Winding Equipment
MeteringPumps
FIG. 2
LG LL LL LLLLL
FIG. 3
AUSTRALIA
Patents Act 1990
COMPLETE SPECIFICATION
Invention title:
"MULTISTAGE WINDING TECHNIQUE OF COMPOSITE MATERIAL"
Applicant:
WUHAN UNIVERSITY OF TECHNOLOGY
Associated provisional applications:
The following statement is a full description of the invention, including the best method of performing it known to me:
"MULTISTAGE WINDING TECHNIQUE OF COMPOSITE MATERIAL"
Field of the Invention
[0001] The present invention relates to the technical field of fabrication of composite materials, and in particular, to a multistage winding technique of a composite material.
Background to the Invention
[0002] Composite materials are widely applied to various fields based on their lightweight performance and high strength, and their fabrication techniques are very flexible. Currently, there are a dozen common composite material fabrication techniques, such as techniques of hand lay-up, spraying, winding, pultrusion, autoclave molding, vacuum assisted molding, mold pressing, resin transfer molding (RTM), laying, and the like. Each technique has advantages and disadvantages to different composite material requirements. There are also composite techniques, such as a pultrusion and winding combined technique.
[0003] The winding technique is an important composite material molding technique. It can fully exert the strength of long fibers and fabricate products with lower strength, higher efficiency and wider applications. So, it can be used for fabricating the traditional cylindrical shell structure and some abnormal structures. The winding technique may be classified into a fixed length winding technique and a continuous winding technique.
[0004] The fixed-length winding technique is a method for fabricating a composite material product on a length-fixed pipe mold within the length of the mold from interior to exterior layer by layer in a spiral and/or annular winding manner, as shown in FIG. 1.
[0005] The continuous winding technique is a method for fabricating a composite material product, specifically, continuously laying up the resin, the continuous fibers, the chopped fibers, and the quartz sands on a continuous output mold in an annular winding manner according to the specified requirements, curing, and then cutting into the composite materials with the specified length, as shown in FIG. 2.
[0006] The composite material has a lightweight structure which is a sandwich or lattice structure, as shown in FIG. 3 and 4. Such structure can fully exert the high strength of the composite material and overcome the low rigidity of the composite material. So, it is widely applied to the fields of aerospace, transport, wind turbine blades, etc.
[0007] The traditional sandwich structure is fabricated by firstly respectively fabricating an inner layer, an outer layer, and an interlayer and secondly conducting secondary adhesion by using the adhesive. The fabrication efficiency is low. Especially, such fabrication method cannot be used for fabricating a nonplanar structure, such as a cylindrical shell structure. Furthermore, in the traditional composite material sandwich structure, the inner layer, the outer layer, and the interlayer utilize different materials; so, they have poor adhesion effect and are easy to separate in use.
Summary of the Invention
[0008] A The present invention seeks to propose a multistage winding technique of a composite material which addresses some problems in the prior art. The present invention can fully exert the high efficiency of the winding technique, and can efficiently fabricate a sandwich structure or a lattice structure of the composite material. Additionally, the inner layer and the outer layer of the fabricated sandwich structure are reliably connected, and is unlikely to separate.
[0009] To achieve the above objective, the present invention provides the following solution: the present invention proposes a multistage winding technique of a composite material , which comprises the following steps: step 1: firstly, fabricating an inner layer of a sandwich structure by utilizing a winding technique; step 2: before the inner layer of the sandwich structure is cured, fabricating an interlayer of the sandwich structure at the exterior of the inner layer of the sandwich structure by utilizing a multistage winding technique; step 3: before the interlayer of the sandwich structure is cured, fabricating an outer layer of the sandwich structure at the exterior of the interlayer of the sandwich structure by utilizing the winding technique.
[0010] Preferably, in step 1, fibers and/or fiber fabrics impregnated with the resin are wound around a rotating cylindrical mold to fabricate the inner layer of the sandwich structure by utilizing a fixed-length or continuous winding technique.
[0011] Preferably, in step 2, the interlayer of the sandwich structure is fabricated by winding the fibers and/or the fiber fabrics around a framework structure by utilizing a two-stage winding technique, and there is one or multiple interlayers of the sandwich structure.
[0012] Preferably, in step 2, the two-stage winding technique comprises: the first-stage winding technique: a roving rack base plate is connected with the framework structure, the fibers and/or the fiber fabrics are arranged on the roving rack base plate, and the fibers and/or the fiber fabrics are wound around the framework structure through the rotation of the roving rack base plate and the forward movement of the framework structure; the second-stage winding technique: the framework structure wound with the fibers and/or the fiber fabrics are impregnated with the resin, and then is wound around the exterior of the inner layer of the sandwich structure.
[0013] Preferably, the framework structure comprises a core and side layers. The side layers utilize continuous sheets or thin strips, and there are two sheets or thin strips respectively arranged on the upper side and the lower side of the core. The core is a continuous space material or discontinuous space material.
[0014] Preferably, the framework structure comprises a core and aside layer. The side layer utilize a continuous sheet or a thin strip, and there is one sheet or thin strip arranged on the upper side or the lower side of the core. The core is a continuous space material, and incisions are discontinuously formed in one side of the core away from the side layer.
[0015] Preferably, the framework structure is a solid rectangular structure.
[0016] Preferably, the framework structure is a hollow thin-walled rectangular structure.
[0017] Preferably, the framework structure is a grid structure.
[0018] Preferably, the core utilizes a lightweight material, an inflatable structure or a phase change material.
[0019] The present invention achieves the following technical effects compared with the prior art: The present invention utilizes the multistage winding technique to fully exert the high-efficiency characteristic of the winding technique and largely accelerate the fabrication of the composite material sandwich structure. Additionally, the winding structure layer of the interlayer utilizes the same material with the inner layer and the outer layer, and they are wet in the winding process; so, the inner layer and the outer layer are tightly connected to form a whole body, and they are not separated due to the problems of the prior art, such as secondary adhesion, different materials, and the like.
Brief Description of the Drawings
[0020] To describe the technical solutions in the embodiments of the present invention or in the prior art more clearly, the following briefly introduces the accompanying drawings required for describing the embodiments. The accompanying drawings in the following description show merely some embodiments of the present invention, and a person of ordinary skill in the art may still derive other drawings from these accompanying drawings without creative efforts.
[0021] FIG. 1 is a schematic diagram of a fixed-length winding technique in the prior art.
[0022] FIG. 2 is a schematic diagram of a continuous winding technique in the prior art.
[0023] FIG. 3 is a schematic diagram of a sandwich structure in the prior art.
[0024] FIG. 4 is a schematic diagram of another sandwich structure in the prior art.
[0025] FIG. 5 is a schematic diagram of a multistage winding technique in the present invention.
[0026] FIG. 6 is a schematic structural diagram of a cylindrical shell wall of a composite material sandwich structure in the present invention.
[0027] FIG. 7 is a schematic diagram showing a longitudinal section of a single-layer framework sandwich structure in the present invention.
[0028] FIG. 8 is a schematic diagram showing a longitudinal section of a double-layer framework sandwich structure in the present invention.
[0029] FIG. 9 is a schematic diagram of fabrication and winding of a framework structure in the present invention.
[0030] FIG. 10 is a schematic diagram of the first framework structure in the present invention.
[0031] FIG. 11 is a schematic diagram of the second framework structure in the present invention.
[0032] FIG. 12 is a schematic diagram of the third framework structure in the present invention.
[0033] FIG. 13 is a schematic diagram of the fourth framework structure in the present invention.
[0034] FIG. 14 is a schematic diagram of the fifth framework structure in the present invention.
[0035] FIG. 15 is a schematic diagram of the sixth framework structure in the present invention.
[0036] In the drawings: 1-inner layer of sandwich structure, 2-interlayer of sandwich structure, 3-outer layer of sandwich structure, 4-framework structure, 41-upper side layer, 42-lower side layer, 43-core, 5-framework structure winding layer, 6-roving rack base plate, 7-continuous fiber yarns, 8 space material, 9-continuous space material, and 10-incision.
Detailed Description of Preferred Embodiments
[0037] The following clearly and completely describes the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are merely a part rather than all of the embodiments of the present invention. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.
[0038] To make the foregoing objective, features, and advantages of the present invention more apparent and more comprehensible, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.
Embodiment 1
[0039] As shown in FIG. 5 to 13, the embodiment provides a multistage winding technique of a composite material, comprising the following steps:
[0040] Step 1: firstly, fabricating an inner layer 1 of a sandwich structure by utilizing a winding technique; specifically, winding fibers and/or fiber fabrics impregnated with the resin around a rotating cylindrical mold by utilizing the existing fixed-length or continuous winding technique;
[0041] Step 2: before the inner layer 1 of the sandwich structure is cured, winding an interlayer 2 of the sandwich structure around the exterior of the inner layer of the sandwich structure by utilizing the existing fixed-length or continuous winding technique. The interlayer 2 of the sandwich structure is fabricated by winding fibers or fiber fabrics around a specified framework structure 4. A multi-stage winding process is utilized. The interlayer 2 of the sandwich structure is fabricated by utilizing two-stage winding. FIG. 5 shows the conveyance direction of the framework structure 4, the rotation direction of the fiber winding plate (namely, the winding direction of the fibers around the framework), the relative movement direction of the frame winding device and the core, and the rotation direction of the core (namely the winding direction of the interlayer). The two-stage winding specifically comprises: (1) A rotatable roving rack base plate 6 is arranged on the framework structure 4. The fibers and/or the fiber fabrics are arranged on the roving rack base plate. In the embodiment, continuous fiber yarns 7 are preferably arranged. The continuous fiber yarns 7 are wound around the framework structure 4 through the rotation of the roving rack base plate and the forward movement of the framework structure 4. (2) The framework structure 4 wound with the fibers and/or the fiber fabrics are impregnated with the resin, and then is wound around the exterior of the inner layer 1 of the sandwich structure.
[0042] Step 3: before the fiber winding layer on the interlayer 2 of the sandwich structure is cured, fabricating an outer layer 3 of the sandwich structure at the exterior of the interlayer of the sandwich structure; specifically, winding the fibers and/or the fiber fabrics impregnated with the resin around a rotating cylindrical mold by utilizing the above fixed-length or continuous winding technique.
[0043] The present invention utilizes the multistage winding technique to fully exert the high-efficiency characteristic of the multistage winding technique and largely accelerate the fabrication of the composite material sandwich structure. Additionally, the winding structure layer on the interlayer framework structure 4 utilizes the same material with the inner layer and the outer layer, and they are wet in the winding process; so, the inner layer and the outer layer are tightly connected to form a whole body, and they are not separated due to the problems of the prior art, such as secondary adhesion, different materials, and the like.
[0044] As shown in FIG. 7 and 8, there is one or multiple interlayers 2 of the sandwich structure.
[0045] As shown in FIG. 10 and 11, in the embodiment, the framework structure 4 comprises an upper side layer 41 and a lower side layer 42, that is, upper and lower continuous sheets or thin strips are provided, and a discontinuous space material 8 is arranged therebetween as a core 43. Or, the framework structure 4 comprises upper and lower sheets or thin strips, and a continuous space material 9 is arranged therebetween as the core 43, and incisions 10 may be fabricated at a certain interval as required.
Embodiment 2
[0046] The embodiment is an improvement based on Embodiment 1. The improvement is: as shown in FIG. 12 and 13, the framework structure 4 comprises a sheet or a thin strip, the upper part is the continuous space material 9, and the incisions 10 may be fabricated on the continuous space material at a certain interval as required. Or, the framework structure 4 comprises a sheet or a thin strip, the lower part is the continuous space material 9, and the incisions 10 may be fabricated on the continuous space material at a certain interval as required.
Embodiment 3
[0047] The embodiment is an improvement based on Embodiment 1. The improvement is: as shown in FIG. 14, the framework structure 4 is a solid rectangular structure, that is, the framework in Embodiment 1 and Embodiment 2 does not use the sheet or the thin strip. As shown in FIG. 15, the framework structure 4 may further be a hollow thin-walled rectangular structure, a grid structure, or other structures meeting the working requirements.
Embodiment 4
[0048] The embodiment is an improvement based on Embodiment 1. The improvement is: no matter that the discontinuous space material 8 or the continuous space material 9 is utilized, the common lightweight material, such as various foam materials, can be utilized and can be reserved in the structure. Or an inflatable material or a phase-change material may also be utilized. Such material generates the phase change to be the liquid by deflation or temperature change and is not reserved in the structure; so, there is a hollow structure.
Embodiment 5
[0049] The embodiment is an improvement based on Embodiment 1. The improvement is: the sheet or the thin strip is fabricated by composite materials, high polymer materials, or metal materials.
[0050] Several examples are used for illustration of the principles and implementation methods of the present invention. The description of the embodiments is merely used to help illustrate the method and its core principles of the present invention. In addition, a person of ordinary skill in the art can make various modifications in terms of specific embodiments and scope of application in accordance with the teachings of the present invention.
In conclusion, the content of this specification shall not be construed as a limitation to the present invention.

Claims (5)

  1. Claims 1. A multistage winding technique of a composite material, including the following steps: step 1: firstly, fabricating an inner layer of a sandwich structure by utilizing a winding technique; step 2: before the inner layer of the sandwich structure is cured, fabricating an interlayer of the sandwich structure at the exterior of the inner layer of the sandwich structure by utilizing a multistage winding technique; step 3: before the interlayer of the sandwich structure is cured, fabricating an outer layer of the sandwich structure at the exterior of the interlayer of the sandwich structure by utilizing the winding technique.
  2. 2. The multistage winding technique of a composite material according to claim 1, wherein in step 1, fibers and/or fiber fabrics impregnated with the resin are wound around a rotating cylindrical mold to fabricate the inner layer of the sandwich structure by utilizing a fixed-length or continuous winding technique.
  3. 3. The multistage winding technique of a composite material according to claim 1 or claim 2, wherein in step 2, the interlayer of the sandwich structure is fabricated by winding e fibers and/or fiber fabrics around a framework structure by utilizing a two-stage winding technique, and there is one or multiple interlayers of the sandwich structure.
  4. 4. The multistage winding technique of a composite material according to claim 3, wherein in step 2, the two-stage winding technique comprises: the first-stage winding technique: a roving rack base plate is connected with the framework structure, the fibers and/or the fiber fabrics are arranged on the roving rack base plate, and the fibers and/or the fiber fabrics are wound around the framework structure through the rotation of the roving rack base plate and the forward movement of the framework structure; the second-stage winding technique: the framework structure wound with the fibers and/or the fiber fabrics are impregnated with the resin, and then is wound around the exterior of the inner layer of the sandwich structure.
  5. 5. The multistage winding technique of a composite material according to claim 3 or claim 4, wherein the framework structure comprises a core and side layers; the side layers utilize continuous sheets or thin strips, and there are two sheets or thin strips respectively arranged on the upper side and the lower side of the core; the core is a continuous space material or discontinuous space material; or, wherein the framework structure comprises a core and a side layer; the side layer utilize a continuous sheet or a thin strip, and there is one sheet or thin strip arranged on the upper side or the lower side of the core; the core is a continuous space material, and incisions are discontinuously formed in one side of the core away from the side layer.
    WUHAN UNIVERSITY OF TECHNOLOGY
    P2366AU00
AU2020101411A 2020-07-20 2020-07-20 Multistage winding technique of composite material Ceased AU2020101411A4 (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112209170A (en) * 2020-10-28 2021-01-12 常州市新创智能科技有限公司 Method for automatically winding glass fiber of metal bolt based on servo control
CN114561864A (en) * 2022-03-11 2022-05-31 中国人民解放军63983部队 High-bearing-capacity integrally-formed composite material joint and manufacturing method thereof
WO2022265486A1 (en) * 2021-06-17 2022-12-22 Valdes De La Garza Xavier Process for manufacturing large-sized, non-circular composite bodies through continuous or discontinuous glass fibre-reinforced resin winding and product obtained
CN117799192A (en) * 2024-02-26 2024-04-02 太原理工大学 Transition method and device between spiral-circumferential winding layers of multiple bundles of fibers

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112209170A (en) * 2020-10-28 2021-01-12 常州市新创智能科技有限公司 Method for automatically winding glass fiber of metal bolt based on servo control
CN112209170B (en) * 2020-10-28 2021-09-07 常州市新创智能科技有限公司 Method for automatically winding glass fiber of metal bolt based on servo control
WO2022265486A1 (en) * 2021-06-17 2022-12-22 Valdes De La Garza Xavier Process for manufacturing large-sized, non-circular composite bodies through continuous or discontinuous glass fibre-reinforced resin winding and product obtained
CN114561864A (en) * 2022-03-11 2022-05-31 中国人民解放军63983部队 High-bearing-capacity integrally-formed composite material joint and manufacturing method thereof
CN114561864B (en) * 2022-03-11 2023-12-29 中国人民解放军63983部队 High-bearing-capacity integrally-formed composite material joint and manufacturing method thereof
CN117799192A (en) * 2024-02-26 2024-04-02 太原理工大学 Transition method and device between spiral-circumferential winding layers of multiple bundles of fibers
CN117799192B (en) * 2024-02-26 2024-04-26 太原理工大学 Transition method and device between spiral-circumferential winding layers of multiple bundles of fibers

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