JPH081018B2 - Composite reinforcing material and method of manufacturing the same - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION (Industrial field of application) The present invention relates to a composite reinforcing material that can be manufactured by a loom,
And its manufacturing method. In particular, the present invention relates to a reinforcing material for a composite material suitable as a heat insulating material exposed to high heat such as outer wall material of a spacecraft.

(Prior Art) As a reinforcing material for a composite material, conventionally, a sheet-shaped woven fabric laminated to a predetermined thickness, or a three-dimensionally arranged and laminated yarn is used. Further, when weight reduction is important as in an aircraft, it is necessary to have strong strength. Only the direction is reinforced with fibers or threads, and efforts are being made to reduce the fiber content as much as possible. U.S. Pat. No. 327185 discloses such a lightweight stiffener. This reinforcing material is formed by connecting two woven fabrics of a warp yarn and a weft yarn, which are a front layer and a back layer, with a woven fabric of an intermediate layer therebetween. The middle layer has a zigzag shape by alternately connecting with the fabrics of the front and back layers, and triangular cells are formed in the longitudinal section of the reinforcing material.

In addition to this, the one currently used as the outer wall material of spacecraft is a honeycomb structure reinforcing material, which is filled with a heat resistant matrix such as ceramics, fired, and then cut into a required shape. It is a thing.

(Problems to be Solved by the Invention) In order to protect the main body from high heat and impact, the outer wall material of the spacecraft and the aircraft needs to have a thickness as well as a strength in the thickness direction. Therefore, in the case of a laminated sheet-like fabric, there is a risk of peeling between layers, and reliability is poor. A reinforcing material in which threads are three-dimensionally arranged and laminated has a large reinforcing effect, but it includes many threads up to unnecessary reinforcing directions, which hinders weight reduction, and requires special equipment for manufacturing.

The reinforcing material disclosed in U.S. Pat. No. 3,207,185 is thick and the cells inside form a space, which is a good reinforcing material for the time being. However, in terms of manufacturing, the intermediate layer has a zigzag shape and is longer than the front and back layers, so it cannot be woven with a normal loom, and a special winding mechanism for adjusting the position of the cloth fell,
Requires a beating mechanism.

Further, the above-mentioned reinforcing materials and honeycomb structural materials such as those currently used for the outer wall material of the space shuttle have serious drawbacks. That is the weakness between the main body and the outer wall material. Conventionally, the two have been joined with an adhesive. When ultra-high heat and impact were applied, it sometimes fell off due to insufficient adhesive strength and deterioration. If some kind of mechanical joining is performed in addition to the adhesive, the reliability is further improved, but bolts and the like cannot be used conditionally, and no improvement method has been found. The present invention is a reinforcing material for a composite material having the performance required for the outer wall material as described above, which can be continuously manufactured by using an ordinary loom, and which has dramatically improved jointability with the main body. And a manufacturing method thereof.

(Means for Solving Problems) The reinforcing material for composite material according to the first invention of the present application is a reinforcing material composed of a woven fabric having a multi-layer woven structure using warp and weft. A large number of cells having partition walls are formed. Furthermore, on one or more outer surfaces of the reinforcement,
It has a structure in which a loop of warp or weft is formed.

The second invention of this application is the method for manufacturing the reinforcing material for a composite material according to the first invention, wherein parts of the warp layers located above and below in the thickness direction are joined by warps to form a cross section of the fabric. In, the binding parts are arranged at equal intervals in each weft layer and are woven into a multi-layer weave so as to be arranged in a plurality of rows in the thickness direction. At the same time, a loop is formed by a part of the yarn forming the outer surface of the reinforcing material. After weaving, when the weft layers are stretched in the thickness direction and opened between the non-bonded portions of each weft layer, and the weft layers are zigzag-shaped in cross section, a large number of cells are formed, and the spaces within each cell are arranged in the warp direction. Continuously,
A reinforcing material having a loop on the surface is obtained.

Inorganic fibers having heat resistance, such as alumina fibers, SiC fibers, carbon fibers, and glass fibers are suitable for the warp and weft.

(Operation) This reinforcing material is woven by a normal loom so that the portion where the weft layer is bound by the warp and the portion where the weft layer is not bound are arranged in the thickness direction in the multi-layer weave design. It is stretched in the vertical direction. As a result, the weft layer bends in a zigzag shape at the binding portion, and a large number of cells having the weft layer as partition walls are formed in the cross section of the reinforcing material. In this way, a space can be obtained inside, but since the binding yarns are arranged in the thickness direction where strength is required, sufficient weight reduction and reinforcement can be achieved.

Then, at the time of weaving, a loop is formed on one or more surfaces of the warp or weft constituting the outer surface of the reinforcing material.

The obtained reinforcing material is filled with a heat resistant matrix and fired to obtain a heat resistant composite material. However, the loop is projected outside.

This structural material is used like outer wall material of spacecraft and aircraft,
When using by joining to the body, the surface with loops is the joining surface. Hook each loop on the hook or pin manufactured on the main body surface, or provide a loop on the main body, and connect it with the loop of the reinforcing material with wires, pins, etc. Here, an adhesive similar to the conventional one can be used together.
It is also possible to form loops on the upper surface and the lower surface of the reinforcing material and stack and join them in the thickness direction. It is also possible to form loops on the side surfaces and end surfaces of the reinforcing material and join them laterally. it can.

(Embodiment) An embodiment of the present invention will be described with reference to the drawings.

FIG. 1 shows an embodiment of the present invention. The heat-resistant composite reinforcing material (20) is composed of wefts (1), (2), (3) and (4) and warp (5), and a loop (9) is formed by a part of the warp (5) appearing on the upper surface. ) Is formed. The cell (30) formed in the cross section has a substantially rectangular shape. A-A in FIG.
Sectional views taken along the line B-B are shown in FIGS. 2 and 3, respectively. This reinforcing material (20) is woven as follows. Regarding the weft, a weft quadruple weave consisting of a first layer (1), a second layer (2), a third layer (3) and a fourth layer (4). In the cross section of the woven fabric, each weft layer has portions that are bound at regular intervals by the weft layers and warps that are located above and below in the thickness direction. That is, the first weft layer (1) and the second weft layer (1) located below the first weft layer (1)
The warp yarn (5) is partly connected to the weft yarn layer (2). In this case, the knots (13) and (13) have a weft double weave as shown in FIG. 2 and are formed at equal intervals in the lateral direction.

The second weft layer (2) and the third weft layer (3) are similarly bound by the warp (5). This connection (14),
(14) is located in the middle of the joints (13), (13) of the first and second weft layers (1), (2), and therefore the joints (13) (14) of both Is relatively laterally displaced. The connecting portion (1) of the third and fourth weft layers (3) and (4)
5) and (15) are arranged in the same row in the thickness direction as the connecting portions (13) and (13) of the first and second weft layers (1) and (2).

The other non-bonded portions (16) which are not bonded are a single weave as shown in FIG. In this manner, the binding portions (13), (14), (15) and the non-binding portion (16) of each weft layer are woven so as to be arranged in a plurality of rows in the same row in the thickness direction. However, the first
Since the layer and the wefts (1) and (4) of the fourth layer are the uppermost layer and the lowermost layer, the number of binding portions is smaller than that of the wefts (2) and (3) of the second and third layers.

On the other hand, for the loop, a part of the warp yarns (5) is selected and the loop (9) is manufactured. When weaving, the wire is driven in the weft direction to form a loop (9),
After that, the wire is removed in the same manner as the pile weave. The wire used here includes not only circular wire but also flat wire.

When the multi-layer woven fabric thus obtained is stretched in the thickness direction and each weft layer is opened at the non-knotting portion, as shown in Fig. 1, the cell (30) is formed in the part where the weft of each layer is separated. Is formed. When extending, a mandrel or a pipe corresponding to the shape is inserted into the cell (30) as a forming tool to fix the form of the reinforcing material (20). After that, remove the molding tool,
Fill with a heat resistant matrix such as ceramics.

In the embodiment shown in FIG. 1, a square cell (30) is formed in the upper surface.
Although the loop (9) is formed at the apex of the above, another loop may be provided at another portion of the upper surface by using another warp (5). Also, loops can be manufactured on both upper and lower surfaces, and can also be manufactured on side surfaces and end surfaces. To form a loop on the end face, the warp yarn is extended on the end face (transverse cross section) of the reinforcing member and folded back to bind the yarn end into the tissue. When forming a loop on the side, use a shuttlecock loom and use the weft folds as loops.

In the embodiment of FIG. 1, the non-knotted portion (16) is a plain weave, but twill weave, satin weave, etc. can also be applied to the knotted portion (13), (1
Similar changes are possible in 4) and (15). Further, each weft layer is not limited to a single weft layer, but may be multiple layers. Furthermore, the density, thickness, and material of the warp and weft may be changed wholly or partially depending on the required performance. Also,
The weight can be further reduced by arranging the warp threads only at the binding portion and the other threads only by the weft threads. Similarly, the number of loops, size, and distribution are determined so that they match the purpose.

(Effect of the invention) In the reinforcing material for a composite material of the present invention, the weft layers are arranged in a zigzag form in a plurality of layers on the upper and lower surfaces and in the middle cross section, and moreover, a large number of cells are equally spaced between the layers. Formed in
These cells have a plurality of layers in the thickness direction, and with this configuration, the weft content in the thickness direction of the reinforcing material can be reduced, the weight can be reduced, and the zigzag-shaped weft layer and the weft layer can intersect. With the woven warp, it is possible to exert strength in all directions against external force acting on the reinforcing material. Moreover, since each weft layer is connected at equal intervals by the warp, the connecting portion It is possible to avoid overlapping of warp yarns in the above and reduce the weight, and also to prevent delamination,
Furthermore, since the loop is formed on one or more surfaces of the outer surface of the reinforcing material, when it is used as the outer wall material of the spacecraft, it can be easily joined to the main body and can be firmly joined.

Thus, the heat-resistant composite reinforcing material according to the present invention,
Although it has a structure in which cells are formed in the cross section, it can be woven in the same way as a multi-layer woven fabric by using warps and wefts and devising its structure. Therefore, it can be continuously manufactured by a conventional loom that has been conventionally used, the productivity is high, and the loop on the outer surface can be easily formed by the conventional pile weaving method. As a result of the loop, a strong mechanical bond with the main body can be achieved as an outer wall material for spacecraft and aircraft, and defects that were difficult to avoid, such as defective bonding and falling off, are eliminated. Further, by changing the number of healds, the heddle movement, and the length of the loom, various reinforcing material thicknesses and cell sizes can be obtained, and the optimal reinforcing material can be easily manufactured according to the necessary conditions.

In this way, it is a reinforcing material with significantly superior properties to the conventional one.

BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 ... Transverse cross-sectional view showing an embodiment of the present invention FIG. 2 ... Cross-sectional view taken along the line AA of FIG. -Cross section along line B (1) (2) (3) (4) …… Weft (5) …… Warp, (9) …… Loop (13) (14) (15) …… Knot (16) …… No connection, (30) …… Cell

Claims (7)

[Claims] 1. A reinforcing material made of a woven fabric having a multi-layer weave structure, which is woven from warp yarns and weft yarns and arranged in a plurality of layers in the thickness direction, wherein the weft yarn layers located above and below in the thickness direction of the woven fabric are evenly spaced. When the weft layers are bound in the thickness direction and stretched in the thickness direction, each weft layer forms a zigzag shape, and each weft layer serves as a partition wall between each binding portion and is continuous in the warp direction, It is characterized by having cells formed in a plurality of layers in the vertical direction and further having a loop formed by pulling out a part of yarns constituting a woven fabric on one surface or a plurality of surfaces of the outer surface of the reinforcing material. Reinforcement material for composite materials. 2. The reinforcing material for a composite material according to claim 1, wherein the loop is formed by warp. 3. The reinforcing material for a composite material according to claim 1, wherein the loop is formed of weft. 4. The reinforcing material for a composite material according to claim 1, wherein the loop is formed on the upper surface or the upper and lower surfaces. 5. When manufacturing a reinforcing material made of a woven fabric having a multi-layer woven structure, which is woven from warp yarns and weft yarns and arranged in a plurality of layers in the thickness direction, (a) the weft yarns located above and below in the thickness direction of the woven fabric. Connecting the layers with warp yarns, (b) arranging the connecting portions at equal intervals in each weft layer in the transverse section of the fabric, and arranging in multiple rows in the thickness direction, (c) forming the fabric Forming a loop on one or more surfaces of the outer surface of the woven fabric with a part of the constituent yarns; (d) after weaving the woven fabric, opening between the non-bonded portions of each weft layer,
A method of manufacturing a reinforcing material for composite material, comprising forming a large number of cells by forming the weft layer in a zigzag shape in a cross section of the reinforcing material. 6. The reinforcing material for a composite material according to claim 5, wherein a wire is driven in the weft direction during weaving, the wire is then removed, and a loop is formed by the warp appearing on the outer surface. Production method. 7. The method for producing a reinforcing material for a composite material according to claim 5, wherein a loop is formed by warp threads on the upper surface or the upper and lower surfaces.