JP3376455B2 - Composite structural members with high bending strength - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION Related Application This application is a partial continuation application of US Patent Application No. 366,464 “Composite structural member having large bending strength and manufacturing method thereof” filed on June 14, 1989. Is.

BACKGROUND OF THE INVENTION The present invention relates to composite structural members having high flexural strength, and more particularly to composite structural members having unique layered arrangements and structures that impart high flexural strength.

Currently, a wide variety of composite materials known to those skilled in the art are used in parts that require light weight and high strength. Such materials have a monolayer or multilayer structure, at least a portion of which is composed of a polymer matrix with embedded fiber components. The arrangement of fiber components in each layer is a factor that determines properties such as strength of the final structure.

Many composite materials are vulnerable to excessive bending, compression, or torsional forces and easily cause structural failure. Therefore,
It is desired to develop a lightweight structure capable of withstanding a large force.

Accordingly, it is an object of the present invention to provide a composite structure having a layered arrangement that provides high strength, especially high bending strength. Another object of the present invention is to provide an elongated composite structural member having high strength and light weight. A further object of the present invention is to provide a simple and efficient method for producing such a composite structural member. Other objects of the present invention will be obvious from the following disclosure of the invention.

SUMMARY OF THE INVENTION The high strength composite structural member of the present invention is a tubular or hollow composite structure having various cross-sectional shapes such as an elongated shape, a circular shape, a rectangular shape, a square shape, or the like. An elongate tubular composite member having a plurality of layers, each layer being defined by a single fiber component disposed within a polymer matrix, wherein the elongate tubular composite member is ± 30 degrees to ± ± relative to a longitudinal axis of the tubular composite member. At least one inner layer having fibers arranged at an angle of 90 degrees, and at least one outer layer having fibers arranged at an angle of ± 30 degrees to ± 90 degrees with respect to the longitudinal axis of the tubular composite member;
A generally axially extending first fiber, a clockwise extending first braided fiber component, and a counterclockwise extending second braided fiber intermingled with the first braided fiber component. At least one intermediate layer having a component, wherein the fibers of the first braided fiber component and the second braided fiber component are ± with respect to the longitudinal axis of the tubular composite member.
It is characterized by being arranged at an angle of 5 degrees to ± 60 degrees.

The circumferential fibers provide crush strength and reinforce the axially extending fibers to prevent buckling failure. The resistance to crush strength is shown as a function of (cosin) ² or (sin) ² of the angle between the fiber direction and the longitudinal axis of the member.

The composite structure further comprises an axially extending second fiber, which is assembled in a plurality of circumferentially-spaced fibers so as to form a circumferential gap between each pair,
A first axially extending fiber is disposed in the circumferential gap. The combination of the axially extending first and second fibers is configured to provide a nearly uniform wall thickness throughout the composite.

Brief Description of the Drawings Figure 1 is manufactured using a removable mandrel,
FIG. 3 is a partially cutaway side view of a composite member according to the present invention.

FIG. 2 is a cross-sectional view showing the innermost layer of the composite in the process of forming the composite member of the present invention.

FIG. 3 is a cross-sectional view showing an axial first fiber which constitutes part of the innermost layer and the intermediate layer in the process of forming the composite member of the present invention.

FIG. 4 is a cross-sectional view showing the innermost layer and the intermediate layer in the process of forming the composite member of the present invention.

FIG. 5 is a cross-sectional view of a composite member of the present invention including an inner layer, an intermediate layer and an outer layer.

  FIG. 6 is a partial detailed cross-sectional view of the intermediate layer of FIG.

FIG. 7 is a schematic view of a sailboat mast manufactured from the composite member of the present invention.

FIG. 8 is a schematic view showing a method for manufacturing a composite structural member according to the present invention.

FIG. 9 is a graph showing the relationship between the length of a composite member and the maximum bending strain for various composite structures.

10 is a cross-sectional view of one of the axial blade filaments, with the cross section of the composite member of FIG. 6 rotated 90 degrees.

DETAILED DESCRIPTION OF THE INVENTION The composite structural member of the present invention is formed from multiple layers that include fiber components disposed within a polymer matrix. This unique layer arrangement of the composite is what gives the member great strength. The composite member is often a tubular structure having various cross-sectional shapes such as elongated, circular, elliptical, rectangular, square and polygonal shapes.

INDUSTRIAL APPLICABILITY The composite member according to the present invention is used for a part that is required to be lightweight and have high strength, for example, a mast or a boom of a sailboat, an antenna or the like.

FIG. 1 shows a fiber component array of a plurality of layered structures forming the composite member 10 of the present invention. As shown in FIG. 1, a composite member 10 manufactured on a removable mandrel.
Are formed from multiple layers that include fiber components embedded within a polymer matrix. Inner layer 16, also shown in FIGS. 2-5, comprises circumferential fiber components 18 arranged at an angle of ± 30 ° to ± 90 ° with respect to the longitudinal axis 20 of the composite member. This circumferential component gives the composite member circumferential strength, which is 90
It becomes maximum in the direction of ° and becomes smaller as the angle decreases. Therefore, the orientation angle of the fiber components 18 with respect to the longitudinal axis 20 is preferably ± 60 ° to ± 90 °.
, And more preferably between ± 80 ° and ± 90 °. The fiber component is preferably 4 to 10
It is configured to include a continuous unidirectional strand of books. For example, when manufacturing a small sailboat mast, the fiber component 18 is formed from about eight fiber strands. Further, a braided or woven fiber component 18 (not shown) may be used to improve circumferential stiffness and buckling strength.

The fiber component may be composed of any of the various fibers commonly used in the manufacture of composite structures, but it is preferred to use fibers having a coefficient of 10 million psi or more. As a desirable fiber material,
Aramid, carbon, graphite,
And, although glass may be mentioned, a particularly preferred material for many applications is glass fiber sold under the trademark E-Glass by the Owens-Calling Company. The preferred fiber diameter of fiber component 18 is about 0.007.
To 0.040 inches. The smaller the diameter, the greater the structural strength, but the larger the diameter, the better the workability.

Usually, the innermost layer 16 is a fiber component that extends in the circumferential direction.
Although it is constructed as a single inner layer containing 18 layers, if it is necessary to form a structural member having greater strength and rigidity, the inner layer should be composed of two or more layered structure having circumferential fibers. May be. When the inner layer is formed of multiple layers, the circumferential fibers of each layer may be arranged at the same angle within the above range with respect to the longitudinal axis 20 and in opposite directions. desirable.

Immediately outside the inner layer 16 in the circumferential direction, one or more intermediate layers are formed. 1 and 3-6 show an embodiment including a single intermediate layer 22. The middle layer 22 comprises two independent fiber components 24 and 30 extending axially. The axially extending first fiber component 24 comprises a plurality of non-braided continuous fibers 24A, said fibers 24A being in each set 26 separated by a void 28, as shown in FIG. It is arranged around 10 laps. The individual fibers 24A extend the entire length of the composite member 10 and are positioned at an angle of about 0 ° with respect to the composite longitudinal axis 20. Each set 26 consists of two axial fibers 24A placed circumferentially adjacent to each other. Further, the groups 26 are separated from each other by a gap 28 in the circumferential direction, and are arranged at equal intervals on the circumference of the composite. Composite member 10
The gap 28 is defined to have a uniform width, the dimensions of which are selected according to the application site. The diameter of the composite structural member according to the present invention is often tapered wholly or partially. In such a case, the dimension of the void 28 is
It changes uniformly over the entire length of the tapered portion.

The second axial fiber component 30 is composed of a second axial fiber 32 that is arranged on the circumference of the composite body 10 with a gap 28 therebetween. Axial primary fiber 24A
Similarly, a second axial fiber 32 is also arranged in each set 34, each set typically including two independent fibers 32. In a given composite, the number of sets 34 may be the same as the number of sets 26. That is, in this case, the groups 26 and 34 of the first and second fibers 24A and 32 in the axial direction are alternately arranged on the circumference of the composite body 10, and each fiber group of the composite body 10 is formed. It is arranged at an angle of about 0 ° with respect to the longitudinal axis 20.

The first axial fiber that makes up a given composite member
The number of 24A is determined by the diameter of the composite and its end use. Axial fiber in a given composite
24A is 5% of the number of axial braided fibers 32
However, it is more preferably 40% to 100% of the number of the fibers 32 in the axial direction. In the tapered composite member 10, the number of fibers in each component 24 and 30 is such that the layer thickness remains uniform, or
It varies over the entire length of the taper to give the desired layer thickness.

Each set 26 of axial non-braided fibers 24A is separated from each other by a predetermined distance so that it combines with the axial fibers 32 to form a wall of substantially uniform thickness over the entire length of the composite. , Arranged on the circumference. For example, when making a 2 inch diameter composite tube containing 48 axial fibers 32 (eg, BASF G-500 12K fiber), make 2 pairs each, such as on the circumference of the composite. The preferred spacing between each set of 24 axial fibers 24A (eg, BASF G30-50012K fiber), which are spaced, is about 0.50 inches.

Further, as shown in FIGS. 1 and 4-6, the axial second fiber component 30 engages a braided fiber component 36 comprised of two helical yarns 36A and 36B. The yarns 36A, 36B are intermixed with the axial second fibers 32 such that each of the axial second fibers 32 is sandwiched between the braided yarns 36A, 36B. The braided yarns 36A, 36B do not mix with the axial first fiber 24A and pass over the surface of the fiber 24A, as shown in FIGS. 6 and 10.

As the second fiber 32 in the axial direction, it is desirable that the second fiber 32 be substantially straight and give maximum strength without causing folds such as waviness and bending even when mixed with the yarns 36A and 36B. Accordingly, the radial amplitude of each yarn must be large so that each braided yarn 36A, 36B can be twisted around the axial fiber 32 over the entire layer thickness.

It is desirable that each yarn 36A, 36B be continuous and extend over the entire length of the composite member 10. However, the non-continuous knitted yarns may be twisted and spliced or overlapped and used. Further, preferably, the yarns 36A, 36B are arranged at an angle of ± 5 ° to ± 60 ° with respect to the longitudinal axis 20. Figure 10
, The wavelength λ of the corrugated axial fiber 32 is equal to the distance between two braid fibers of the same type, eg, between two braid fibers 36A. The wavelength of the waveform is determined based on the axial diameter and the elastic coefficient of the second fiber 32, as well as the coefficient and strength of the material of the matrix 14. The longer the optimal wavelength, the more the fiber 32 and matrix 14 can withstand greater strain forces. The preferred wavelength λ is about 0.10 to 1.00 inches.

In a given composite structure according to the present invention, the axial first and second fibers 24A, 32 have the same diameter and are made of the same material. The diameter of these axial fibers is based in part on the diameter of the composite structure, with a preferred range of 0.07 to 0.040 inches. The axial first and second fibers 24A, 32 may be made of any of many fiber materials such as polyethylene, carbon, graphite, ceramics, boron, aramid, and glass. When particularly high strength is required, a fiber material such as carbon having a coefficient of 34 million psi or more, a maximum stress of 500 ksi and a minimum strain of 1.4% is preferably used. Carbon fibers having a filament count of about 12,000, a yield of about 615 yd / lb (0.807 g / m), and a coefficient of 30 million psi or more are preferably used in many application examples. One example of such a fiber is the fiber sold by BASF under the trademark Cerion Carbon Fiber G30-50012K.

The diameter of the braided yarns 36A, 36B is smaller than the diameter of the axial fibers 24A, 32, particularly preferably 25% or more smaller. That is, the diameter of the braided yarns 36A and 36B is about
The range is 0.005 to 0.015 inches. Braided yarn
36A and 36B may be made of any of many fiber materials such as aramid, glass, carbon and graphite. Preferred materials for the braided yarns 36A, 36B include, for example, glass fibers sold under the trademark S-2 Glass by Owen Corning. Furthermore, a coefficient of 10 million psi or more and
A fiber with a maximum stress of 600 ksi is desirable.

The composite structural member according to the present invention may have a single intermediate layer 22 in many applications, but more preferably two or more intermediate layers 22. For example, small sailboat masts typically incorporate three intermediate layers 22.
When manufacturing a highly flexible member 10 with three intermediate layers 22, it is advisable to make the outer two layers identical and reduce the number of axial fibers 24A, 32 by only the innermost layer.
With such a configuration, the rigidity in the axial direction, the bending strength, and the breaking strength in the circumferential direction can be increased.

As shown in FIGS. 1 and 5, the fiber-containing outer layer 38
Are affixed adjacent to and just outside the intermediate layer 22. Outer layer 38
Also includes a circumferential fiber component 40 embedded within a matrix of polymeric resin or the like (FIG. 1).
reference). The outer layer fiber component 40 is arranged at the same angle as the inner layer fiber component 18, but its winding direction is opposite to the winding direction of the fiber component 18. With this configuration, the member 10 can be given sufficient strength to withstand the radial load and the crushing load. It is preferable to form the fiber component 40 of the outer layer so as to have the same diameter as the fiber component 18 of the inner layer and from the same fiber material. Usually a single outer layer is used, but more than one outer layer can be used depending on the application.

The inner layer 16 and the outermost layer 38 are each configured to have a tensile modulus of elasticity of less than 25% of the total axial modulus of elasticity of the composite (measured in the 0 degree direction). One or multiple intermediate layers 22
The balance is adjusted by combining with.

When exposed to extreme external conditions, e.g., where it may be impacted by debris or other high velocity objects, the fiber component 18 should have a modulus of about 43.5 million psi and 1.
Carbon yarn, such as BASF G40-700, which has a maximum strain of 66%, and a fiber component 38 of 500,000 (500,
DuPont Kevlar HT or Kevlar with a maximum stress of 000) psi or more and a tensile modulus of 12 million psi or more
It is desirable to use 29 aramid fiber. Further, by mixing, knitting, or weaving the fibers of the outer layer, it is possible to give a larger impact strength.

As mentioned above, each layer of composite member 10 is comprised of a matrix 14 of polymer or the like and the fiber components arranged therein. The matrix is usually the same for all layers, and the material is capable of penetrating and bonding with multiple fiber components 18, 24, 30, and 40 to provide a strong and reliable composite member. Anything will do. Well-known thermosetting or thermoplastic polymers having high strength can be preferably used as the polymer matrix material. Examples of thermosetting polymers include epoxies, vinyl esters, which can be cured with known curing agents such as anhydrides, polyamides, aliphatic amines,
Examples thereof include polyester. Examples of thermoplastic polymers include polyphenylene sulfide, polyether sulfone, polyethylene terephthalate, nylon, polypropylene, polycarbonate, acetal,
Examples thereof include polyether ether ketone. A particularly preferred polymer matrix material is a low viscosity epoxy resin that is cured with an anhydrous compound. For example, Dow
Epoxy resins manufactured by Chemical Company and sold under the trademark DER330 epoxy resin can be used. Further, methyl tetrahydrophthalate anhydride can be used as such an anhydrous curing agent for epoxy resin, that is, as a catalyst.

One of the advantages of the layered structure of the composite structural member of the present invention is that the layer arrangement of the intermediate layer 22 allows for uniform wall thickness throughout the composite 10. The first axial fiber component 24 is replaced by the second axial fiber
The voids formed between each set 34 of 32 are effectively filled. The presence of such voids results in a non-uniform surface and its thickness, resulting in a decrease in flexural strength, torsional strength, and radial strength of the composite. The graph of FIG. 9 shows the relationship between the composite length and the maximum strain in the composite manufactured according to the present invention and the other structures. Curve A shows the bending strength of the composites produced according to the invention, which again clearly shows that the structure according to the invention improves the bending strength. Curve B
Indicates the flexural strength of a similarly constructed composite, except that it does not include the axial first fiber component 24. Curve C shows the flexural strength of a composite constructed similarly to the composite of curve A, except that it does not include circumferential fiber components 18, 38 and axial fiber component 24.

The composites produced according to the invention have a high wall thickness uniformity and, as a result, a high bending strength. Furthermore,
The braided fiber component 36, which is a component in the Z direction, that is, the radial direction and the thickness direction, strengthens the bond between the layers and contributes greatly to the increase in the strength of the composite. Also,
By reducing the pleats of the axial fibers having a large modulus, the stresses on the matrix are reduced compared to other mixed or braided composite structures.
Thus, the structure of the present invention can increase the bending strength of the composite member without increasing the weight, and the lightweight and high-strength composite manufactured according to the present invention is
It can be applied to various parts.

The composites of the invention are particularly suitable for sites that have to withstand a bending strain of 0.25% or more (defined by the change in the ratio of the total length to the original length, usually measured with a strain gauge). For example, the composite structural members of the present invention include ski poles, yacht spars, golf club shafts, pole vault rods, fishing rods, fishing boat overhangs, oar shafts, paddle shafts, hockey stick shafts, and baseball bats. , Glider structure members, etc., and is suitably used for parts that are lightweight and have high strength, and particularly high bending strength. Further, such a composite material can also be used for structural piping, structural members of aircraft and aerospace vehicles, structural members of automobiles, tubular containers, torsion springs,
It can also be used for manufacturing leaf springs, robots and the like. In addition, communication antennas, marine structures, wheelchairs, canes,
It can also be used for medical accessories such as stretchers and prostheses.
Particularly preferred applications of the composite of the invention include mast structures for sailboats and small sailboats.

FIG. 7 illustrates a spar 42 manufactured in accordance with the techniques of the present invention and used in the fabrication of sail columns such as sailboat masts. Spar 42
Is an upright tubular post supporting a sail (not shown)
With 44. The spar 42 is constructed of a composite as described above, including a single inner layer, a three-layered middle layer, and a single outer layer. The diameter of the post 44 is the same for about half the total length of the spar, and tapers at a uniform rate over the other half. The diameter of the tapered portion of the spur varies from about 2.0 to 0.85 inches. Post 4
In addition to the layers and matrix that make up 4, spar 42,
Further, it may be configured to be covered with an environmental protection paint such as polyurethane. In this case, in order to prevent deterioration of the matrix material due to direct sunlight, an ultraviolet absorber may be added to the paint.

The spar 42 is provided with a reinforced intermediate boom portion 46 to withstand excessive bending forces applied locally, such as attaching a boom (not shown). Post 44 to accommodate different boom positions and sail designs
Is reinforced over a length of approximately 40 inches (Fig. 7
reference). The reinforced boom section 46 is impregnated with resin and is bonded to the spar with molding tape, approximately 8.75 oz / yard ²
The outside is covered with a glass fabric (eg, E-glass).
The diameter of the boom portion 46 is approximately 0.065 inches without reinforcement, which increases wall thickness by approximately 0.015 inches. By reinforcing the boom portion, the rigidity of the spar in the circumferential direction is increased, and it becomes possible to withstand the local load caused by the attachment of the boom to the spar. Also,
The reinforcing fabric used for the boom portion 46 has the advantage of being able to withstand a larger local load because it disperses the load compared to non-woven mixed fiber layers of the same type and having the same layer thickness. However, the reinforced boom portion 46 shown in FIG. 7, although useful in some applications, is not necessary for all sailboat masts made from the composite according to the present invention.

FIG. 8 shows a composite assembly apparatus 49 for manufacturing composite structural members according to the present invention. The various layers forming the composite structural member of the present invention are wrapped around a mandrel or mold 50 to make the member, the shape of the mandrel being determined by the composite. The mandrel 50 used in the manufacturing process of the present invention may or may not be tapered, and is made of a material such as aluminum, steel, plastic or rubber. It may be hollow or solid, but a hollow mandrel is preferred.

As shown in FIG. 8, various fiber and polymer matrix layers are applied around the mandrel 50 and across a series of stations for wrapping,
The mandrel 50 is placed in the composite manufacturing line. First,
Stations 52 wrap the fibers 18 of inner layer 16 onto mandrel 50. Station 52 rotates about an axis parallel to transverse direction 56 of mandrel 50,
Multiple fiber packages 54 (eg 4 to 8)
A device for holding the package). Traverse speed of mandrel 50 and fiber package of station 52
The ratio to the rotational speed (rpm) of 54 determines the amount of fiber in the inner layer 16 and its direction. For example, when manufacturing a sailboat mast, the mandrel 50 traverses within the assembler 49 at about 4 feet per minute and the rotational speed of the eight yarn packages at station 52 is determined by the specified design requirements and combined Vary from 40 to 175 rpm depending on the diameter of a given part of the body. Immediately after the station 52, a liquid polymer resin such as epoxy is poured from the device 58A to penetrate and impregnate the entire fiber component 18 of the inner layer. In this case, the volume ratio of the resin to the fiber is preferably 50% or less.

As the mandrel 50 moves further across the manufacturing apparatus 49, the filament winding station 60 then winds the fiber component of the first intermediate layer. Yarn
The package 62A allows the axial first fiber 24 to
The yarn package 62B then wraps the axial second fiber 32. In addition, station 60
In, the knitting yarn components 36A, 36B are wrapped by a mixing device (not shown). Where yarn
It is desirable that the number of packages 62A, 62B be the same as the number of axial fibers 24, 43 present in each layer. At this time, the resin coating device 58 forming part of the station 60
The resin is poured from B to form the matrix of the first intermediate layer.

In a manner similar to that described above, second and third intermediate layers are formed at filament winding stations 61 and 64, respectively. Further, the polymer resin forming the matrix is poured by the resin coating devices 58C and 58D forming part of the stations 61 and 64.

The mandrel 50 then passes through the same filament winding station 66 as station 52. Station 66 winds the fiber components of outer layer 38 in a manner similar to station 52. However, in this case, the station 66 rotates in the direction opposite to the station 52. After winding the circumferential fiber layer, the device 58E
Resin material is poured. If desired, additional stations (not shown) may be added here and the circumferential fiber layer may be further wrapped and coated with resin.

At each filament winding station, the fiber tension is adjusted so that the fiber does not loosen or move after being wound and is taut.
Also, the tension of the braided fiber 36 is adjusted using a mixing device that maintains a pulling force of about 1 lb / fiber or less.

Finally, the mandrel 50 passes through a tape wrapping device 68 that wraps the thermoplastic tape 41 about 1/2 to 3/4 inch wide around the mandrel 50, or layer. It is desirable to keep the pulling force on the tape at a value between 3 and 15 pounds. The pulling force of the tape molds the filament and resin wrapped around the mandrel, removing excess resin and expelling the air trapped between the filament and resin. An example of a tape that is particularly useful in the manufacture of sailboat masts is 2 1/2 inch wide.
Mention may be made of mm-thick, silicon-coated polyester films.

A drive mechanism 70 is used to move the mandrel 50 along the manufacturing apparatus 49. As such a mechanism, one that can change the traversing speed of the mandrel 50 is desirable.

After applying the thermoplastic tape, the structure is placed in a vertical convection oven at a temperature of about 300 ° F for about 2 hours to cure the resin. After taking it out of the oven and cooling the structure,
Remove the mandrel 50 from the cured composite. When removing the mandrel, the composite shrinks as the resin changes from liquid to solid, so it is necessary to pull with a force of 1,000 lbs or more. Next, the thermoplastic molding tape 41 is rewound and removed from the layered structure.

After removing the tape, the glass may be removed from the cured resin so that the polyurethane paint can be applied and treated with a sand polishing machine to make the outer diameter of the composite uniform. In particular, when manufacturing a sailboat mast, it is desirable to polish the layered structure.

The structure and manufacturing process of the present invention are described in more detail in the following examples, but the present invention is not limited to the following examples.

Example 1 In this example, a sailboat mast having the above structure will be described in detail. The structure of the sailboat mast is as follows.

Overall length: 460 cm Outer diameter: Tapered from 5.3 cm to 3.0 cm Wall thickness: Range from 0.18 cm to 0.24 cm Layers: 5 layers The following materials were used to manufacture the mast of this example. It was

Component (drawing reference number): Inner circumferential fiber (18) Material: E-Glass Type: 675 Type 30 Robbing Source: Owens-Corning Properties: Coefficient = 10.5 × 10 ⁶ psi Density = 2.5g / cm ³ Component ( Reference number): Axial fiber (24A) Material: Carbon fiber Type: 12k G30500 Supplier: BASF Properties: Coefficient = 34MSI Density = 1.77g / cm ³ Component (reference number): Axial fiber (32) Material: Carbon fiber type: 12k G30500 Supplier: BASF Property: Coefficient = 34MSI Density = 1.77g / cm ³ composition (reference number): Braided yarn (36A) Material: S2-Glass type: S2CG1501 / 3 Supplier: Owens-Corning properties : Coefficient = 12.0MSI Density = 2.48g / cm ³ Component (reference number): Braided yarn (36B) Material: S2-Glass type: S2CG1501 / 3 Supplier: Owens-Corning Properties: Coefficient = 12.0MSI Density = 2.48g / cm ³ component (reference number): circumferential fiber (40) Material: E-Glass Type: 675 Type 30 Robbing Source: Owens-Corning Properties: Coefficient = 10.5 × 10 ⁶ psi Density = 2.50 g / cm ³ Component (reference number): Matrix material (14) Material: Epoxy resin, tetrahydro Methyl phthalate anhydride, N, N-dimethylbenzylamine (100: 80: 2 parts by weight) Type: DER330, AC-75 Supplier: Dow Chemical Co., Ltd. When manufacturing the mast of this example, FIG. The mandrel is moved at a speed of 4 feet / minute in the apparatus shown in. The mandrel is made from anodized aluminum,
It has six tapers, as shown in Table 1 below.

At station 58A, the liquid epoxy resin and catalyst mixture described above is cast onto the mandrel at the location where the inner layer circumferential fiber component 18 is wrapped. By changing the winding speed of the fiber 18 around the mandrel, the circumferential rigidity and the crush strength can be adjusted. Also, by varying the amount of fibers 18, the circumferential stiffness can be adjusted according to various structure diameters and design load requirements. The fiber wrap 52 is then fitted with eight distribution packages and rotated around the mandrel. Table 2 below shows the fibers that are wrapped around the mandrel in this process.
18 shows the change in quantity.

As the mandrel traverses the braid 60, the following fiber components are wrapped. (1) 12 fibers 32 equally spaced around the braid (2) Rotate clockwise on the braid, 24 fibers 36A (3) Rotate counterclockwise on the braid , 24 fibers 36B.
Fibers 36A, 36B rotate at 3.85 rpm.

At the same time, at station 58B, liquid epoxy resin is poured into the fibers as they are assembled around the mandrel.

As the mandrel traverses the braid 61, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid 32 (3) Rotate clockwise on the braid, 24 fibers 36A (4) Rotate counterclockwise on the braid , 24 fibers 36B. The fibers 36A, 36B rotate at a constant speed of 3.85 rpm on the assembly.

At the same time, at station 58C, liquid epoxy resin is cast into the fibers as they are assembled around the mandrel.

As the mandrel traverses the braid 64, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid 32 (3) Rotate clockwise on the braid, 24 fibers 36A (4) Rotate counterclockwise on the braid , 24 fibers 36B. The rotation speed of the device holding the fibers 36A, 36B is 3.85 rpm.

At the same time, at station 58D, liquid epoxy resin is poured into the fibers as they are assembled around the mandrel.

The fiber component 40 is then wrapped around the mandrel at a speed set to provide adequate circumferential stiffness and crush strength. By varying the amount of fibers 40, the circumferential stiffness can be adjusted according to the diameter and design load of the structure. The fiber wrapping device 66 is fitted with eight dispensing packages and is rotated about the mandrel as it traverses the device. Table 3
Shows the variation in the amount of fiber 40 wrapped around the mandrel in this process.

At station 58E, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 40 is wrapped.

The fiber layer impregnated with the mandrel and uncured liquid epoxy resin then passes through a tape former 68. Two 1/2 inch wide cellophane tapes (sold by Century Design Inc. of San Diego, Calif.) Are wrapped around a mandrel at a speed of 60 rpm.

After removing the mandrel and the uncured layer from the transverse feed device 70, suspend them vertically in a hot air convection oven and place them at 140 ° C for 8 hours.
Allow to harden for hours.

After curing is complete, the mandrel is removed from the structure and the cellophane tape is wound as described above according to the mandrel removal method well known to those skilled in the art.

The finishing step is then entered and the mast is cut to a length of 4.6 meters (but one inch from the bottom of the structure, with the remaining extra length trimmed from the tip). The structure is abraded with a 80 grit finish file using a centerless wet polisher. After polishing, a 40 inch long, 14 inch wide glass fiber plain weave (8.75 ounces / yard ² E-glass) impregnated with epoxy resin and catalyst is wrapped around the composite structure. Cover the mast 30 inches from the base to 70 inches from the base. After wrapping the tape in a spiral around the reinforced glass fiber,
The composite structure is cured at 140 ° C.

  After curing, remove the tape and repolish the structure.

In the final step, the structure is coated with a polyurethane paint mixed with 2% by weight of iron oxide pigment.

  The properties of the resulting structure were as follows.

Example 2 In this example, a sailboat mast having the above structure will be described in detail. The structure of the sailboat mast is as follows.

Overall length: 480 cm Outer diameter: 5.3 cm to 3.0 cm Taper wall thickness: 0.18 cm to 0.24 cm Range: 6 layers The following materials were used to manufacture the structure of this example. Was given.

Ingredient (Refer to Drawing): Inner Circumferential Fiber (18) Material: E-Glass Type: 675 Type 30 Robbing Source: Owens-Corning Properties: Coefficient = 10.5 × 10 ⁶ psi Density = 2.50g / cm ³ Component ( Reference Number): Axial Fiber (24A) (In this example, Fiber 24A is a combination of two separate fibers) Material: Carbon Fiber E-Glass Mold: 12k G30500 450 Model 30 Robbing Source: BASF Owens-Corning Properties: Coefficient = 34 MSI 10.5 Density = 1.77 g / cm ³ 2.5 g / cm ³ Component (reference number): Axial fiber (32) (In this example, the fiber 32 is two separate fibers. Material: Carbon Fiber E-Glass Type: 12k G30500 450 Type 30 Robbing Supplier: BASF Owens-Corning Properties: Coefficient = 34MSI 10.5Msi Density = 1.77g / cm ³ 2.5g / cm ³ composition (reference) Number): Braid Over emissions (36A) Materials: S2- glass mold: S2CG1501 / 3 supplier: Owens - Corning Properties: Factor = 12.0MSI Density = 2.48 g / cm ³ components (reference number): knitting yarns (36B) Materials: S2- glass Mold: S2CG1501 / 3 Supplier: Owens-Corning Properties: Coefficient = 12.0MSI Density ＝ 2.48g / cm ³ Component (reference number): Circumferential Fiber (40) Material: E-Glass Mold: 675 Model 30 Robbing Supplier : Owens-Corning Properties: Coefficient = 10.5 x 10 ⁶ psi Density = 2.50 g / cm ³ Component (reference number): Matrix material (14) Material: Epoxy resin, tetrahydrophthalic acid methyl anhydride, N, N-dimethylbenzylamine (100: 80: 2 parts by weight) Type: DER330, AC-75 Supplier: Dow Chemical Company In the sailboat mast of this example, fibers 24A and 32 are composed of a combination of two types of fiber materials, As a result, detailed description will be given to the first embodiment. Compared to it are materials that, impact resistance and overall bending strength is improved.

The structure of Example 1 was a five-layer structure, but this embodiment is a structure of six layers.

The mandrel is made from Teflon anodized aluminum and has the desired stiffness distribution and profile,
It has 6 tapers (see Table 5).

A sailboat mast is manufactured by passing the mandrel through the apparatus shown in FIG.

The mandrel 50 moves in the assembly device at a speed of 4 feet / minute.

At station 58A, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 18 is to be wrapped.

The fiber component 18 is wrapped around the mandrel at a speed adjusted to provide adequate circumferential stiffness and crush strength. By changing the amount of the fibers 18 according to the variation of the diameter or the design load of the structure, the rigidity in the circumferential direction can be maintained at an appropriate value. The fiber wrapping device 52 is fitted with eight distribution packages and rotated around a mandrel that moves laterally within the device. Fibers wrapped around the mandrel are shown in Table 6 below.
18 shows the change in quantity.

The mandrel then passes through four assembly stations that have the same yarn composition and fiber arrangement.
The details of the assembling device 61 shown in FIG. 8 will be described below.
62 and 63 are similarly configured.

At station 58C, the fibers are assembled around the mandrel and the liquid matrix component is cast into the fibers.

As the mandrel traverses the braid 61, the following fiber components are wrapped. (1) A total of 24 fibers arranged in pairs around the mandrel in equal intervals.
24A: 450 type 30 lobing E-glass 18 pieces and 12k G30500
6 carbon fibers (2), 48 fibers in total, equally spaced around the braid 32: 450 type 30 lobing E-glass 36 and 12k G30500 12 carbon fibers (3) on the braid Twenty-four fibers 36A (4) that rotate in a clockwise direction at (24) Twenty-four fibers 36B that rotate in a counterclockwise direction on the assembly machine. The rotation speed of the fibers 36A and 36B is set to a constant speed of 3.85 rpm.

Next, at station 58D, the fibers are assembled around the mandrel and the liquid matrix component is cast into the fibers.

The fiber component 40 is then wrapped around the mandrel at a speed set to provide adequate circumferential stiffness and crush strength. By varying the amount of fibers 40, the circumferential stiffness can be adjusted according to the diameter and design load of the structure. The fiber wrapping device 66 is fitted with eight dispensing packages and is rotated about the mandrel as it traverses the device. Table 7
Fiber 40 wrapped around the mandrel
Shows the change in the amount of.

At station 58E, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 40 is wrapped.

The fiber layer impregnated with the mandrel and uncured liquid epoxy resin then passes through a tape former 68. Two 1/2 inch wide cellophane tapes (sold by Century Design Inc. of San Diego, Calif.) Are wrapped around a mandrel at a speed of 60 rpm.

After removing the mandrel and the uncured layer from the transverse feed device 70, suspend them vertically in a hot air convection oven and place them at 140 ° C for 8 hours.
Allow to harden for hours.

Using the mandrel removal device, remove the mandrel from the structure and wind the cellophane tape as described above.

Cut the finished mast to a length of 480 centimeters (but one inch from the bottom of the structure, and the remaining extra length from the tip).

The mast is sanded with 80 grit finishing sandpaper using a centerless wet sander. 2% by weight after polishing
The mast is coated with a polyurethane paint mixed with the black iron oxide pigment of.

  The properties of the resulting structure were as follows.

Final mast weight = 5.4lbs Center of gravity = 45% (from structure base) Crush strength = 5501bs (2 inch cross section from base) Load and maximum deflection in column buckling test = 3301bs: 48 inch Mast base material coefficient (0 degree) = 6.1Msi coefficient (90.0 degree) = 2.3Msi coefficient (45 degree) = 4.1Msi density = 2.05g / cm ³ Example 3 Curved structural member: sailboat boom In this example, a method for manufacturing a circular pipe having a curved cross section Also, the design will be described.

The dimensions of the tubular body manufactured in this example are as follows.

  Tube total length: 180 cm   Inner diameter of tube: 2.67 cm   The tubular body is composed of the following three integrally molded parts.

(1) Straight line portion = length 42 cm (2) Curved portion = radius 16 inches: angle 41 ° (3) Straight line portion = length 12 inches The structure of this example is made of the same material as the structure of example 1. It is configured.

The mandrel used in this example is made from 80 durometer silicone rubber cord and has a constant outer diameter of 1.05 inches.

When manufacturing a curved pipe for a sailboat boom or the like, the mandrel moves in an apparatus similar to that of FIG. 8 except that only two assembling tools 61 and 64 are incorporated.

The mandrel 50 moves in the assembly device at a speed of 4 feet / minute.

At station 58A, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 18 is to be wrapped.

The fiber component 18 is wrapped around the mandrel clockwise at a speed of 50 rpm. Fiber winding device 52
Attach 8 dispensing packages to the and rotate it around a mandrel that moves laterally within the device.

As the mandrel traverses the braid 61, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid (3) rotate clockwise on the braid, 24 fibers 36A (4) rotate counterclockwise on the braid , 24 fibers 36B. In this case, fiber 36A,
The rotation speed of 36B is set to a constant speed of 3.85 rpm.

At the same time, at station 58C, the liquid matrix components are cast into the fibers as they are assembled around the mandrel.

As the mandrel traverses the braid 64, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid 32 (3) Rotate clockwise on the braid, 24 fibers 36A (4) Rotate counterclockwise on the braid , 24 fibers 36B. The rotation speed of the fibers 36A and 36B is set to a constant speed of 3.85 rpm.

At the same time, at station 58D, a liquid matrix material is cast into the ascending fibers around the mandrel.

Then, the fiber component 40 is wound around the mandrel counterclockwise at a speed of 50 rpm.

At station 58E, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 40 is wrapped.

The fiber layer impregnated with the mandrel and uncured liquid epoxy resin then passes through a tape former 68. Two 1/2 inch wide cellophane tapes (sold by Century Design Inc. of San Diego, Calif.) Are wrapped around a mandrel at a speed of 60 rpm.

After removing the mandrel and the uncured layer from the transverse feeding device 70, the mandrel and the uncured layer are fixed to a jig or a mold that determines the outer shape of the curved portion. The jig is placed in a hot air convection oven and cured at 140 ° C for 8 hours.

Using a mandrel removal device well known to those skilled in the art, remove the silicone mandrel from the structure and wind the cellophane tape as described above.

  The properties of the resulting structure were as follows.

Final tube weight = 1.2lbs Material coefficient (0 degree) = 12.2Msi coefficient (90.0 degree) = 2.4Msi coefficient (45 degree) = 5.9Msi Density = 1.5g / cm ³ Example 4 Below, bending load and torsion load An example of a composite structural member designed to withstand the above combination will be described.

  The dimensions of the final composite structure are as follows.

Overall length: 365 cm Outer diameter: 3.1 cm Wall thickness: 0.3 cm Number of layers: 6 layers The structure of this example is made of the same material as the structure of example 1.

Also in this embodiment, the same apparatus as the manufacturing apparatus shown in FIG. 8 is used, but it is modified as follows.

(1) Four braces are used instead of three braces.

(2) Except for the braiding unit 60 and the packages 62B and 62A, the two braiding units and the yarn package have an axis of up to 56 degrees.
It can rotate around 100.

The method of manufacturing the structure of this example will be described in detail with reference to FIG.

The mandrel used in this example is made from Teflon anodized aluminum and has a constant diameter of 1.00 inches.

The mandrel 50 moves within the assembly device at a speed of 2 feet / minute.

At station 58A, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 18 is to be wrapped.

The fiber component 18 is wrapped around the mandrel counterclockwise at a speed of 7.5 rpm. Fiber winding device
Attach 16 distribution packages to 52 and rotate around a mandrel that moves laterally within the device.

As the mandrel traverses the braid 60, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid (3) rotate clockwise on the braid, 24 fibers 36A (4) rotate clockwise on the braces, 24 fibers 36B. The rotation speed of the fibers 36A and 36B is set to a constant speed of 1.9 rpm.

At the same time, at station 58B, the liquid matrix components are poured into the fibers as they are assembled around the mandrel.

As the mandrel traverses the braid 61, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid 32 (3) Rotate clockwise on the braid, 24 fibers 36A (4) Rotate counterclockwise on the braid , 24 fibers 36B. The rotation speed of the fibers 36A and 36B is set to a constant speed of 1.9 rpm. In addition, the entire assembly rotates clockwise at a speed of 7.5 rpm.

At the same time, at station 58C, the liquid matrix components are cast into the fibers as they are assembled around the mandrel.

As the mandrel traverses the second braid 61, the following fiber components are rewound. (1) 24 fibers 24A arranged in pairs around the mandrel and equally spaced (2) Evenly spaced around the braid 4
8 fibers 32 (3) 24 fibers 36A rotating clockwise on the assembly, 4 fibers 36A (4) 24 fibers 36B rotating counterclockwise on the assembly. Fiber 36A, 36
The rotation speed of B is set to a constant speed of 1.9 rpm.

At the same time, at the second station 58C, the liquid matrix components are poured into the fibers as they are assembled around the mandrel.

As the mandrel traverses the braid 64, the following fiber components are wrapped. (1) 24 fibers 24A arranged in pairs around the mandrel and arranged at equal intervals.
(2) 48 fibers 32 equally spaced around the braid 32 (3) Rotate clockwise on the braid, 24 fibers 36A (4) Rotate counterclockwise on the braid , 24 fibers 36B. The rotation speed of the device holding the fibers 36A and 36B is set to a constant speed of 1.9 rpm. Furthermore, the entire assembly rotates counterclockwise at a speed of 7.5 rpm.

Although not shown in FIG. 8, the second assembling unit 61 added in the apparatus of this embodiment is the same as the assembling unit 60.

Further, at station 58D, the liquid matrix components are poured into the fibers as they are built around the mandrel.

Then, the fiber component 40 is wound around the mandrel clockwise at a speed of 1.9 rpm.

At station 58E, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 40 is wrapped.

The fiber layer impregnated with the mandrel and uncured liquid epoxy resin then passes through a tape former 68. Two 1/2 inch wide cellophane tapes (sold by Century Design Inc. of San Diego, Calif.) Are wrapped around a mandrel at a speed of 30 rpm.

After removing the mandrel and the uncured layer from the transverse feed device 70, suspend them vertically in a hot air convection oven and place them at 140 ° C for 8 hours.
Allow to harden for hours.

Remove the mandrel from the structure using the mandrel removal device.

  Next, the tape is wound by the method described above.

  The properties of the resulting structure were as follows.

Final tube weight = 4.5 lbs Material coefficient (0 degree) = 12.5 Msi coefficient (90.0 degree) = 4.6 Msi coefficient (45 degree) = 12.9 Msi density = 1.57 g / cm ³ Example 5 1 is an example of a composite structural member designed to withstand a combination of torsional loads. The structure is manufactured continuously.

The following materials were used for manufacturing the structure of this example.

Component (drawing reference number): Inner layer circumferential fiber (18) Material: Carbon fiber 12K Type: Toray T700S Supplier: Toray Property: Coefficient = 33.5Msi Density = 1.8g / cm ³ Maximum strain = 2.1% Component (reference number) ): Axial fiber (24A) Material: Carbon fiber Type: 12k G30500 Supplier: BASF Property: Coefficient = 34MSI Density = 1.77g / cm ³ component (reference number): Axial fiber (32) Material: Carbon fiber Type: 12k G30500 Supplier: BASF Property: Coefficient = 34MSI Density = 1.77g / cm ³ Component (reference number): Braided yarn (36A) Material: S2-Glass Mold: S2CG1501 / 3 Supplier: Owens-Corning Property: Coefficient = 12.0MSI Density = 2.48g / cm ³ Component (reference number): Braided yarn (36B) Material: S2-Glass type: S2CG1501 / 3 Supplier: Owens-Corning Properties: Coefficient = 12.0MSI Density = 2.48g / cm ³ Component (reference number): Circumferential fiber (40 Materials: Carbon Fiber 12K Type: Toray T700S Supplier: Toray properties: The coefficient = 33.5Msi density = 1.8 g / cm ³ maximum strain = 2.1% present embodiment, while the composite body is moved over the die assembly device, the matrix A curing accelerator is added as a catalyst so that the can be sufficiently cured. The resins used in this example are as follows.

Epoxy resin: Der 330 (manufactured by Dow Chemical Co.) Catalyst: AC-DP-1 (manufactured by Anhydrides & Chemicals Co.) The die used in this example is made of tool steel and its inner diameter is 3.1 cm. The inner surface of the die is chrome plated and finished to 25 RMS. The die length is 75c
m, which is maintained at a temperature of 150 ° C. throughout the manufacturing process.

The dimensions of the composite structure manufactured in this example are as follows.

Inner diameter: 2.5 cm Outer diameter: 3.2 cm Wall thickness: 0.35 cm Number of layers: 7 layers Also in this embodiment, the same manufacturing apparatus as shown in FIG. 8 is used, but changed as follows. Has been done.

(1) One assembly device is arranged in front of the winding station 52.

(2) One assembly unit installed after station 52
Rotate clockwise at a speed of 7.5 rpm. After that, the third
And the fourth braid is installed.

(3) Assembly device # 5 rotates counterclockwise at a speed of 7.5 rpm.

(4) A filament winding station similar to the station 66 shown in FIG. 8 is incorporated.

(5) Instead of the tape forming machine 68, a heating die having a length of 75 cm is used.

(6) A chop saw for cutting the composite portion into a desired length is incorporated.

  The composite structure of the present invention is manufactured as follows.

The mandrel used in this example is made from Teflon anodized aluminum and has a constant diameter of 1.00 inches. Further, the mandrel is supported by a cantilever in front of the first assembling device.

The composite material moves through the heating die at a rate of 2 feet / minute.

A mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber components 24A, 32, 36A, 36B are wrapped.

The following fiber components are wrapped as the mandrel traverses the first braid # 1. (1) 24 fibers 24A arranged in pairs around the mandrel and equally spaced (2) Evenly spaced around the braid 4
8 fibers 32 (3) 24 fibers 36A rotating clockwise on the assembly, 4 fibers 36A (4) 24 fibers 36B rotating counterclockwise on the assembly. Fiber 36A, 36
The rotation speed of B is set to a constant speed of 1.9 rpm. In addition, the entire assembly # 1 rotates clockwise at a speed of 7.5 rpm.

At station 58A, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 18 is to be wrapped.

The fiber component 18 is wrapped around the mandrel counterclockwise at a speed of 7.5 rpm. Fiber winding device
Attach 16 distribution packages to 52 and rotate around a mandrel that moves laterally within the device.

The following fiber components are wrapped as the mandrel traverses the second braid # 2. (1) 24 fibers 24A arranged in pairs around the mandrel and equally spaced (2) Evenly spaced around the braid 4
8 fibers 32 (3) 24 fibers 36A rotating clockwise on the assembly, 4 fibers 36A (4) 24 fibers 36B rotating counterclockwise on the assembly. Fiber 36A, 36
The rotation speed of B is set to a constant speed of 1.9 rpm.

At the same time, the liquid epoxy resin is poured into the fibers which are assembled around the mandrel by the assembly machine.

The following fiber components are wrapped as the mandrel traverses braiders # 3 and # 4. (1) 24 fibers 24A arranged in pairs around the mandrel and equally spaced (2) 48 fibers 32 evenly spaced around the braid (3) clockwise on the braid Twenty-four fibers 36A (4) Twenty-four fibers 36B that rotate counterclockwise on the assembly. Fiber 36A,
The rotation speed of 36B is set to a constant speed of 1.9 rpm.

At the same time, the liquid epoxy resin is poured into the fibers which are assembled around the mandrel by the assembling machines # 3 and # 4.

The following fiber components are rewound as the mandrel traverses braid # 5. (1) 24 fibers 24A arranged in pairs around the mandrel and equally spaced (2) equally spaced around the braid 48
24 fibers 36A, which rotates clockwise on the fiber 32 (3) braid, and 24 fibers 36B, which rotates counterclockwise on the braid 32 (3). Fiber 36A, 36
The rotation speed of B is set to a constant speed of 1.9 rpm. In addition, the entire assembly # 5 rotates counterclockwise at a speed of 7.5 rpm.

At the same time, the liquid epoxy resin is poured into the fibers which are assembled around the mandrel by the fifth assembling device # 5.

Then, the fiber component 40 is wound clockwise around the mandrel at a speed of 7.5 rpm.

At station 58E, a mixture of liquid epoxy resin and catalyst is cast onto the mandrel where the fiber component 40 is wrapped.

The fiber layer impregnated with the mandrel and uncured liquid epoxy resin is then passed through a steel die well known to those skilled in the art. The die has holes with a diameter of 3.2 cm and is heated to 150 ° C. Allow the layered composite to fully cure as it moves through the die. After ensuring that the structure is fully integrated, it is cut to the desired length with a cutoff saw well known to those skilled in the art.

Further, it is placed in a heating oven and heated at 150 ° C. for 2 hours so as to give a sufficient catalytic effect to the matrix material.

  The properties of the resulting structure were as follows.

Final tube weight = 0.42lbs / ft Material coefficient (0 degree) = 14.5Msi coefficient (90.0 degree) = 4.4Msi coefficient (45 degree) = 13.4Msi Density = 1.5g / cm ^{3 As is} clear from the above explanation, With the construction of the present invention, the above objects (including those described clearly and those which can be read from the detailed description of the invention) are achieved. Further, it goes without saying that the manufacturing process and the configuration of the composite structure can be variously changed without departing from the gist of the present invention, and the above-mentioned embodiments and the accompanying drawings do not limit the present invention in any way. However, they are merely described as specific examples of the present invention.

The following claims set forth the general and certain features of the invention from which the gist of the invention may be read.

  The claims of the present invention will be described below.

─────────────────────────────────────────────────── ─── Continuation of the front page (58) Fields surveyed (Int.Cl. ⁷ , DB name) B32B 1/00-35/00 B29C 70/16 B63B 15/02

Claims (5)

(57) [Claims] 1. An elongate tubular composite member having a plurality of layers, each layer being defined by a single fiber component disposed within a polymer matrix, wherein the elongate tubular composite member has a longitudinal axis relative to the longitudinal axis of the tubular composite member. At least one inner layer having fibers arranged at an angle of ± 30 degrees to ± 90 degrees, and at least having fibers arranged at an angle of ± 30 degrees to ± 90 degrees with respect to the longitudinal axis of the tubular composite member. One outer layer, a first fiber that extends generally axially, a first braided fiber component that extends clockwise, and a counterclockwise stretch that is intermixed with the first braided fiber component. A second braided fiber component, at least one intermediate layer having, wherein the fibers of the first braided fiber component and the second braided fiber component are Wherein arranged at an angle of 5 degrees to ± 60 degrees ± respect to the longitudinal axis of the tubular composite member, the composite member, characterized in that. 2. A circumferential gap is formed between each pair,
A second fiber extending in the axial direction, which is a combination of a plurality of fibers spaced apart in the circumferential direction, is further provided, and the first fiber extending in the axial direction is arranged in the circumferential gap. Item 2. The tubular composite member according to Item 1. 3. The tubular composite member according to claim 4, comprising at least one axially arranged innermost layer disposed inside the inner layer. 4. The tubular composite member of claim 1, further comprising a polymer matrix that extends through the first and second braided fiber components and is bonded to the axially extending first fiber. 5. The tubular composite member of claim 1, wherein the axially extending first fibers are arranged at an angle of less than 57 degrees with respect to the longitudinal direction of the composite member.