Patent Publication Number: US-2012034400-A1

Title: Carbon fiber-reinforced carbon composite material and method for manufacturing the same

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
     This application claims priority from Japanese Patent Application No. 2010-174968, filed on Aug. 4, 2010, the entire subject matter of which is incorporated herein by reference. 
     BACKGROUND OF THE INVENTION 
     1. Field of the Invention 
     The present invention relates to a carbon fiber-reinforced carbon composite material and a method for manufacturing the same. 
     2. Description of the Related Art 
     Since carbon fibers have high heat resistance and strength, they are used as a carbon fiber reinforced carbon composite material (C/C composite material) including the carbon fibers and a carbon matrix in various fields requiring heat resistance, chemical stability and strength. The C/C composite material includes various kinds depending upon a compositing method of carbon fibers, and various carbon fiber molded bodies can be formed by using the same. 
     The C/C composite material is comprised of a matrix made of a carbide such as a pitch and a thermosetting rein, and carbon fibers. There are various C/C composite materials depending upon a fixing method of carbon fibers such as a cloth laminating method using a carbon fiber cloth, a filament winding method using carbon fiber filaments, a method using a carbon fiber felt, or a sheet-forming method using a carbon fiber sheet-formed body. 
     The cloth laminating method is a method of obtaining a C/C composite material by laminating a woven fabric made of carbon fibers, impregnating the woven fabric with a matrix precursor such as a pitch and a thermosetting resin, followed by curing and calcination (see JP-A-H11-60373). A C/C composite material in a plate form can be obtained by laminating planar woven fabrics and uniaxially pressing the laminate. Also, a C/C composite material in a complicated shape of the papier-mache form can be obtained by sticking small cut woven fabric pieces to a die in a three-dimensional shape. Furthermore, a C/C composite material in a cylindrical shape can also be obtained by winding a planar woven fabric in a roll form while applying a pressure thereto and laminating it (cloth winding method). 
     The filament winding method is a method of obtaining a C/C composite material by winding a strand of carbon fibers around a mandrel while applying a tension thereto and then impregnating the wound strand with a matrix precursor such as a pitch and a thermosetting resin, followed by curing and calcination (see JP-A-H10-152391). 
     The method using a carbon fiber felt is a method of obtaining a C/C composite material by laminating long fibers of carbon fibers in a felt-like form and impregnating the laminate with a matrix precursor such as a pitch and a thermosetting resin, followed by curing and calcination (see JP-A-2000-143360). Similar to the cloth laminating method, according to this method, a planar C/C composite material, a cylindrical C/C composite material and a C/C composite material having a complicated shape can also be obtained. In particular, a cylindrical C/C composite material can also be obtained by winding up a planar felt in a roll form while applying a pressure thereto, followed by lamination (cloth winding method; see, for example,  FIGS. 19A and 19B ). 
     According to the sheet-forming method, the C/C composite material of a sheet-forming method is obtained by suspending carbon fibers in a liquid to form a slurry, dipping a suction die having an aperture in this slurry, allowing the liquid in the slurry to pass into a rear surface of the suction die and depositing carbon fibers on the surface side of this suction die to form a molded material, following by drying and calcination (see JP-A-2002-68851 and JP-A-2002-97082). 
     The disclosures of JP-A-H11-60373, JP-A-H10-152391, JP-A-2000-143360, JP-A-2002-68851 and JP-A-2002-97082 are incorporated herein by reference. 
     SUMMARY OF THE INVENTION 
     An embodiment of the present invention provides the following: 
     A carbon fiber-reinforced carbon composite material comprising:
     carbon fibers; and   a carbonaceous matrix,   wherein the carbon fiber-reinforced carbon composite material is integrally formed;   wherein the carbon fibers are a substantially linear fiber existing in a bare-fiber state within the carbonaceous matrix and having an average fiber length of less than about 1.0 mm, and   wherein the carbon fiber-reinforced carbon composite material has a bulk density of about 1.2 g/cm 3  or more.   

     A method for manufacturing the above-described carbon fiber-reinforced carbon composite material, the method comprising:
     spreading substantially linear carbon fibers having an average fiber length of less than about 1.0 mm into a bare fiber;   forming a preform including the substantially linear carbon fibers and a precursor component of a carbonaceous matrix, in which the carbon fibers are present in a bare-fiber state;   integrally press molding the preform; and   calcining the press molded preform to form the carbonaceous matrix from the precursor component.   

    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
       The above and other aspects of the present invention will become more apparent and more readily appreciated from the following description of illustrative embodiments of the present invention taken in conjunction with the attached drawings, in which: 
         FIGS. 1A to 1D  are views showing a molded body of Embodiment 1 of the present invention, specifically,  FIG. 1A  is a perspective view;  FIG. 1B  is a sectional view;  FIG. 1C  is an enlarged view of a part of  FIG. 1B ; and  FIG. 1D  is a more enlarged view of a part of  FIG. 1C ; 
         FIGS. 2A to 2C  are conceptual views showing dynamic characteristic features of a C/C composite material, specifically,  FIG. 2A  is a conceptual view of a C/C composite material of an embodiment of the present invention;  FIG. 2B  is a conceptual view of a C/C composite material according to a conventional cloth laminating method; and  FIG. 2C  is a conceptual view of a C/C composite material according to a conventional method using a felt; 
         FIG. 3  is a step flow chart of a manufacturing method of a molded body of Embodiment 1; 
       FIGS.  4 A 1  to  4 D are outline views showing a manufacturing method of a molded body of Embodiment 1; 
         FIGS. 5A to 5D  are views showing a molded body of Embodiment 2, specifically,  FIG. 5A  is a perspective view;  FIG. 5B  is a sectional view;  FIG. 5C  is an enlarged view of a part of  FIG. 5B ; and  FIG. 5D  is a more enlarged view of a part of  FIG. 5C ; 
         FIGS. 6B to 6D  are outline views showing a manufacturing method of a molded body of Embodiment 2; 
         FIG. 7A  is a photograph of a section of a molded body of Example 1, and  FIG. 7B  is a photograph of a section of a molded body of Comparative Example 1; 
         FIG. 8A  is an enlarged photograph of the surface of a molded body of Example 1;  FIG. 8B  is a photograph of thin piece bodies observed on the surface of the molded body of  FIG. 8A ; and  FIG. 8C  is a photograph of thin piece bodies separated from the surface of the molded body of  FIG. 8A ; 
         FIG. 9A  is a scanning electron microscopic photograph of a section of a molded body of Comparative Example 1, and  FIG. 9B  is a schematic view of  FIG. 9A ; 
         FIGS. 10A to 10C  are a scanning electron microscopic photographs of a section of a molded body of Example 1, specifically,  FIG. 10A  is a photograph with a magnification of 100;  FIG. 10B  is a photograph with a magnification of 200; and  FIG. 10C  is a photograph with a magnification of 500; 
         FIGS. 11A to 11C  are scanning electron microscopic photographs of a section of a molded body of Comparative Example 1, specifically,  FIG. 11A  is a photograph with a magnification of 50;  FIG. 11B  is a photograph with a magnification of 200; and  FIG. 11C  is a photograph with a magnification of 500; 
         FIGS. 12A and 12B  are views showing a molded body of Embodiment 3, specifically,  FIG. 12A  is a perspective view, and  FIG. 12B  is a sectional schematic view; 
         FIGS. 13A to 13C  are outline views showing a manufacturing method of a molded body of Embodiment 3; 
         FIGS. 14A and 14B  are views showing a molded body of Embodiment 4, specifically,  FIG. 14A  is a perspective view, and  FIG. 14B  is a sectional schematic view; 
         FIGS. 15A and 15B  are outline views showing a manufacturing method of a molded body of Embodiment 4; 
         FIGS. 16A and 16B  are views showing a molded body of Embodiment 5, specifically,  FIG. 16A  is a perspective view, and  FIG. 16B  is a sectional schematic view; 
         FIGS. 17A to 17D  are views showing a molded body of Embodiment 6, specifically,  FIG. 17A  is a perspective view;  FIG. 17B  is a sectional view;  FIG. 17C  is an enlarged view of a part of  FIG. 17B ; and  FIG. 17D  is a more enlarged view of a part of  FIG. 17C ; 
       FIGS.  18 A 1  to  18 D are outline views showing a manufacturing method of a molded body of Embodiment 6; 
         FIGS. 19A and 19B  are views of a molded body of Comparative Example 1, specifically,  FIG. 19A  is a perspective view, and  FIG. 19B  is a sectional view; 
         FIG. 20  is a graph showing the results obtained by measuring a relation of elastic modulus and breaking strength of each of C/C composite materials of Examples and Comparative Examples; 
         FIG. 21  is a graph showing the results obtained by measuring a relation of elastic modulus and breaking strain of each of C/C composite materials of Examples and Comparative Examples; 
         FIGS. 22A and 22B  are schematic views showing a cut-out direction and a three-point bending test direction of a sample for measuring physical properties of each of C/C composite materials of Examples and Comparative Examples; and 
         FIG. 23A  is a polarizing microscopic photograph of a section of a molded body of Example 1, and  FIG. 23B  is a polarizing microscopic photographic of a section of a molded body of Comparative Example 1. 
     
    
    
     DETAILED DESCRIPTION 
     The related-art C/C composite materials as described in the above is considered to involve the following problems. 
     In the carbon fibers, since a hexagonal plane of graphite is strongly oriented in a longitudinal direction of the fibers, the carbon fibers are small in a coefficient of thermal expansion as about 1 PPM/° C. and high in an elastic modulus as compared with general graphite materials. C/C composite materials prepared using such carbon fibers as a major raw material are considered to take over properties of carbon fibers and have the same characteristic features as those of the carbon fibers such that they have a small coefficient of thermal expansion and a high elastic modulus. When a combination of such a C/C composite material with a general graphite material is, for example, used as a high-temperature member of a furnace, a difference in thermal expansion between the general graphite material having a coefficient of thermal expansion of from about 3 to about 5 PPM/° C. and the C/C composite material is likely to generate a thermal stress, thereby easily causing breakage of the graphite material and/or the C/C composite material. 
     Also, in the C/C composite material itself, there may be the case where an exposed portion thereof reacts with a reactive gas in a furnace, for example, silicon or the like and converts into a compound having a different coefficient of thermal expansion, such as SiC (coefficient of thermal expansion: about 4 PPM/° C.). In that case, a thermal stress is likely to be generated between the remaining C/C composite material and the reacted and converted carbide, thereby easily forming a crack on the side of the carbide and/or the C/C composite material, or causing separation. 
     An embodiment of the present invention provides a C/C composite material in which even when used in combination with other member such as a general graphite material, breakage to be caused due to an interaction of a difference in the coefficient of thermal expansion or the like is hardly generated, and even when a carbide is formed with a reactive gas, separation and/or breakage to be caused due to the generation of a thermal stress is hardly generated, and a method for manufacturing the same. 
     Illustrative embodiments of the present invention will be described by reference to the drawings. 
     Embodiment 1  
     A molded body (hereinafter referred to as “C/C composite material molded body”) of a carbon fiber-reinforced carbon composite material (hereinafter referred to as “C/C composite material”) of Embodiment 1 of the present invention is described on the basis of  FIGS. 1A to 1D . 
       FIG. 1A  is a perspective view of a C/C composite material molded body  100  of the present Embodiment 1.  FIGS. 1B to 1D  are a sectional view of  FIG. 1A , an enlarged view of a part thereof and a more enlarged view of a part, respectively. 
     The C/C composite material according to an embodiment of the present invention is an integrally formed material. That is, the C/C composite material according to the embodiment of the present invention is not a material formed by laminating preforms. 
     In this C/C composite material molded body, carbon fibers are present in a bare-fiber state within a carbonaceous matrix. The carbon fibers are a substantially linear fiber having an average fiber length of less than about 1.0 mm, and this C/C composite material molded body has a bulk density of about 1.2 g/cm 3  or more. 
     As shown in  FIGS. 1C and 1D , in this C/C composite material molded body  100 , in the majority of carbon fibers  1 , a longitudinal direction of the fibers is oriented in a surface direction of the molded body  100  within a carbonaceous matrix  2 , whereby thin piece bodies (sheet-like small pieces) 3 are formed. The C/C composite material molded body  100  according to an embodiment of the present invention is configured by a laminate of the thin piece bodies  3 . 
     According to this configuration, since the average fiber length of the carbon fibers is short as less than about 1.0 mm, a rate at which the matrix component receives a stress is likely to increase, a function of the carbon fibers to regulate deformation of the matrix within the C/C composite material can be easily weakened, and a degree of influence against an elastic modulus on the carbon fibers can be easily made larger than that on the matrix component, and therefore, the elastic modulus of the C/C composite material can be easily lowered. 
     Also, since the carbon fibers are present in a bare-fiber state, a bonding surface area to the matrix can be easily increased. Furthermore, when carbon fibers are bundled, a portion where the matrix is not filled between the carbon fibers is likely to be weak in strength; however, in the constitution of an embodiment of the invention in which the carbon fibers are present in a bare-fiber state, such a portion is considered not present. As a result, crack propagation hardly occurs in the C/C composite material of an embodiment, and high strength can be revealed. The bare-fiber state as referred to herein means a state where the carbon fibers do not form a strand. 
     Furthermore, since the C/C composite material according to an embodiment of the present invention is configured by a substantially linear (acicular) carbon fiber, the carbon fibers are easy to intersect with each other by means of piercing, and an adhesive force is likely to be strong. The substantially linear carbon fiber as referred to herein means that the carbon fiber extends substantially linearly without being bent. According to this, in view of the fact that the carbon fibers pierce at the time of sheet-forming and/or at the time of molding, the carbon fibers are likely to intersect with each other, whereby a C/C composite material with high strength can be easily obtained. 
     A characteristic feature of the C/C composite material according to an embodiment of the present invention resides in that very short carbon fibers having an average fiber length of less than about 1.0 mm are present in a bare-fiber state. Here, in general, carbon fibers are characterized by having properties of high strength and high elasticity. Such a dispersion state of carbon fibers is considered as influencing dynamic characteristic features of the C/C composite material. This point is described by reference to  FIGS. 2A to 2C . 
       FIGS. 2A to 2C  are conceptual views showing dynamic characteristic features of a C/C composite material, specifically,  FIG. 2A  is a conceptual view of the C/C composite material of an embodiment of the present invention;  FIG. 2B  is a conceptual view of a C/C composite material according to a conventional cloth laminating method; and  FIG. 2C  is a conceptual view of a C/C composite material according to a conventional method using a felt. In  FIGS. 2A to 2C ,  1  represents a carbon fiber, and F B  represents coupling by the matrix. Incidentally, the X-direction is a horizontal direction of the drawing; the Y-direction is a vertical direction of the drawing; and the Z-direction is a longitudinal direction of the drawing. 
     In the C/C composite material according to a related-art cloth laminating method shown in  FIG. 2B , since an extremely long fiber is used as the carbon fiber, the dynamic characteristic features of the C/C composite material are considered as being significantly influenced by the characteristic features of the carbon fibers but hardly influenced by those of the matrix. However, the characteristic features of the carbon fibers influence in two directions (X- and Y-directions) in which the longitudinal direction of the fibers is mainly oriented. In view of the fact that in a laminating direction (thickness direction, i.e., Z-direction), coupling between the carbon fibers is not present, but only coupling by the matrix is present, it may be considered that the characteristic features of the carbon fibers are hardly reflected. 
     Also, in the C/C composite material according to a related-art filament winding method shown in  FIG. 2C , similar to the cloth laminating method, a long fiber of carbon fiber is used, and therefore, the dynamic characteristic features of the C/C composite material are considered as being significantly influenced by properties of the carbon fiber itself. In that case, the characteristic features of the carbon fibers influence in one direction (X-direction) in which the longitudinal direction of the fibers is mainly oriented. However, characteristic features of the carbon fibers may also slightly influence in the Y-direction depending upon a winding manner of the fibers. Similar to the cloth laminating method, in view of the fact that in a laminating direction (thickness direction, i.e., Z-direction), coupling between the carbon fibers is not present, it may be considered that only coupling by the matrix is present, it may be considered that sufficient strength cannot be obtained. 
     On the other hand, the C/C composite material according to an embodiment of the present invention in which short carbon fibers are present in a bare-fiber state shown in  FIG. 2A  is different in the dynamic characteristic features from the C/C composite material composed of long carbon fibers shown in the foregoing  FIG. 2B  or  2 C. That is, in the C/C composite material according to an embodiment of the present invention, short carbon fibers are present in a bare-fiber state, and the matrix connecting the bare fibers to each other has a role as a binder. Also, different from the related-art C/C composite material shown in the foregoing  FIG. 2B  or  2 C, in the C/C composite material of an embodiment of the present invention shown in  FIG. 2A , since the carbon fibers are present in a bare-fiber state, a joint area connecting the carbon fibers to each other can be easily increased. As a result, there is hardly present a portion with weak strength in which the carbon fibers form a strand, whereby the matrix is not filled between the carbon fibers. Thus, crack propagation hardly occurs, so that the C/C composite material according to an embodiment of the present invention is able to reveal high strength. 
     It may be considered that the elastic modulus of the C/C composite material according to an embodiment of the present invention is influenced by the matrix portion rather than the carbon fibers. A resin, a pitch or the like serving as a raw material of the matrix generates a gas in a process of carbonization, and therefore, pores are formed in the matrix. It may be considered that when pores are formed, the pores absorb deformation, whereby the elastic modulus can be easily lowered. In consequence, even though carbon fibers with a high elastic modulus are used, a soft C/C composite material can be easily obtained. 
     Incidentally, according to the conventional methods described in JP-A-2002-68851 and JP-A-2002-97082, in which after the slurry of carbon fibers is directly filtered (sheet-formed), carbon is deposited in the inside of pores of the sheet-formed body, a hard and minute film is formed on the fiber surface and laminated, and therefore, a C/C composite material with high elasticity which is free from the formation of pores in the matrix is easily formed. On the other hand, in the C/C composite material according to an embodiment of the present invention, since a soft matrix component is filled, a C/C composite material with low elasticity is easily obtainable. 
     In the embodiment of the present invention, a fiber volume fraction is preferably from about 30% to about 50%. When the fiber volume fraction is about 30% or more, a fiber-to-fiber distance is not too far, so that sufficient strength can be revealed. Also, when the fiber volume fraction is not more than about 50%, the fibers can easily intersect with each other. On the other hand, when the fiber volume fraction exceeds about 50%, instead of the fact that a fiber-free portion is reduced, there may be the case where the direction of the fibers are made in the same direction, and a direction with weak strength is considered as being easily produced. The fiber volume fraction as referred to in the invention means one obtained by dividing a volume occupied by the carbon fibers, by a volume of the whole of the C/C composite material. A calculation method of the fiber volume fraction is described later. 
     Also, a bulk density of the C/C composite material according to the embodiment of the present invention is preferably about 1.2 g/cm 3  or more, and more preferably about 1.3 g/cm 3  or more. Since the C/C composite body has a bulk density of about 1.2 g/cm 3  or more, the pores are buried, and connection (bonding) between the fibers is likely to become strong. Incidentally, the bulk density of the C/C composite material is desirably not more than about 1.8 g/cm 3 . When the bulk density of the C/C composite material is not more than about 1.8 g/cm 3 , a gas generated at the time of calcination of the molded body is easy to come out, and swelling of the molded body or interlayer separation hardly occurs. As a result, tenacity is hardly lost, and when broken, the shape is considered as being easily kept. 
     The carbon fibers in the embodiment of the present invention are configured as a substantially linear fiber. Since the carbon fibers are configured as a substantially linear carbon fiber, the carbon fibers pierce at the time of sheet-forming and/or molding and are easy to intersect with each other. Thus, a C/C composite material with high strength is easily obtainable. Then, the carbon fibers form a thin piece body (as described later) in which a longitudinal direction of the fibers is oriented in a curved surface direction of the molded body within the carbonaceous matrix. The C/C composite material molded body is configured by a laminate of the thin piece bodies. 
     According to this configuration, the carbonaceous matrix  2  is filled and constituted so as to intervene between the carbon fibers  1  constituting the thin piece bodies  3 , thereby fixing the carbon fibers each other. Furthermore, since the thin piece bodies  3  are laminated in such a manner that fallen leaves are piled up at random, the ends of the thin piece bodies are dispersed in many places of the inside of the carbon fiber molded body. In other words, the thin piece bodies are disposed such that ends of the thin piece bodies adjoining in a laminating direction of the thin piece body to each other are deviated in the laminating direction. According to this, the ends of the thin piece bodies hardly overlaps, so that a defect (boundary of the thin piece body) which is structurally weak, thereby causing separation or formation of a crack is considered as being finely dispersed. In the meantime, in the case where a large defect is present in one place, the stress concentration tends to occur and this large defect becomes a notch, thereby easily causing a lowering of the strength. On the other hand, when a defective portion is likely to be finely dispersed as in an embodiment of the present invention, a stress to be applied to the defective portion can be easily dispersed. For that reason, a carbon fiber molded body which is apparently homogenous and free from a defect can be obtained. Since the C/C composite material molded body according to an embodiment of the present invention has such a structure, a C/C composite material molded body which is high in heat resistance and high in strength even at a high temperature can be easily obtained. 
     An average major axis diameter of the thin piece body is preferably from about 1 to about 10 mm, and more preferably from about 2 to about 5 mm. When the average major axis diameter of the thin piece body is about 1 mm or more, since the size of the corresponding flock piece is not likely to become small, the hydraulic resistance hardly becomes large at the time of sheet-forming, and a thick-walled C/C composite material molded body is easily obtainable. On the other hand, when the average major axis diameter of the thin piece body is about 10 mm or less, in laminating a flock serving as a base of the thin piece body in a manufacturing step as described later, in view of the fact that a central part and a peripheral part are different in easiness of aggregation from each other, segregation of a fiber and a binder hardly occur, and therefore, a binder component in the inside of the thin piece body is hardly cause segregation. Also, when the average major axis diameter of the thin piece body is about 10 mm or less, even when the binder is melted in subsequent molding and curing, the thin piece body can sufficiently flow, whereby the segregation is easily relieved. As a result, a portion which is thin in the binder is hardly formed, whereby the strength of the molded body is hardly lowered. 
     An average thickness of the thin piece body is preferably from about 0.05 to about 1.0 mm, and more preferably from about 0.1 to about 0.5 mm. When the average thickness of the thin piece body about 0.05 mm or more, the size of the corresponding flock hardly becomes small, the hydraulic resistance hardly becomes large, and a thick-walled C/C composite material molded body is easily obtainable. When the average thickness of the thin piece body is about 1.0 mm or less, a void is hardly formed in an end of the thin piece body, and stress concentration is hardly generated in the surroundings of the void, so that the strength of the molded body is hardly lowered. 
     Also, an average fiber length of the carbon fibers which are used for the C/C composite material is preferably less than about 1.0 mm, more preferably about 50 μm or more and less than about 1.0 mm, and still more preferably from about 50 to about 500 μm. When the average fiber length of the carbon fibers is not more than about 1.0 mm, since the carbon fibers hardly restrain the C/C composite material, the influence of the elastic modulus of the fibers also hardly appears on the C/C composite material. When the average fiber length of the carbon fibers is about 50 μm or more, the fibers can sufficiently get tangled with each other, so that the strength can be enhanced. 
     Also, it is preferable that the C/C composite material according to an embodiment of the present invention is molded by means of a sheet-forming method. However, in general, according to the sheet-forming method, a sheet-formed body is obtained by filtering fibers dispersed in water, or the like; whereas according to an embodiment of the present invention, by adding an aggregating agent to the carbon fibers dispersed in water and a binder powder (first binder) to form flocks, which are then subjected to sheet-forming to mold a sheet-formed body. Since the sheet-formed body is formed after forming flocks composed of carbon fibers and a binder powder, partial scattering in concentration between the carbon fibers and the binder powder within the flock is hardly generated, so that a uniform thick-walled sheet-formed body can be easily obtained. Different from the embodiment of the present invention, in the case of undergoing sheet-forming without forming a flock, the sheet-formed body is likely to become non-uniform due to a difference in sedimentation rate between the carbon fibers and the binder powder and a difference in sedimentation rate due to the fiber length or particle diameter, a defective portion with a weak bonding force and a site where only short fibers segregate are generated, and the strength is easily lowered. Therefore, a thick-walled sheet-formed bod with high strength is considered as hardly obtainable. 
     The C/C composite material according to an embodiment of the present invention preferably has an elastic modulus of from about 5 GPa to about 15 GPa. In the case where the elastic modulus of the C/C composite material is about 15 GPa or less, when used as a structural member of a furnace in combination with other member such as graphite, at the time of coming into contact with each other, a large stress is hardly generated because of an elastic modulus of the C/C composite material hardly becomes large due to a difference in thermal expansion from other member, thereby hardly causing breakage of the graphite member or the C/C composite material. In the case where the elastic modulus of the C/C composite material is about 5 GPa or more, not only the strength of the carbon fiber-reinforced carbon composite material is hardly lowered, but because of a non-small elastic modulus as compared with that of the graphite member, the C/C composite material hardly exceeds an elastic limit and is deformed. 
     The C/C composite material according to an embodiment of the present invention preferably has a tensile strength of about 50 MPa or more. In the case where the tensile strength of the C/C composite material is about 50 MPa or more, when used as a structural member of a furnace, the C/C composite material is hardly broken, and it can be safely used. In the C/C composite material according to an embodiment of the present invention, since the fibers and the binder are easily uniformly dispersed, even though short fibers having an average fiber length of less than about 1.0 mm are used, the C/C composite material forms flocks, uniformly disperses the binder in the flocks and hardly causes segregation of the carbon fibers. Thus, a defect-free C/C composite material with high strength can be obtained. 
     As shown in Examples (see  FIGS. 20 and 21 ) as described later, the C/C composite material according to an embodiment of the present invention is able to easily make a value of the elastic modulus relative to the strength low. A relation among elastic modulus, stress and strain can be expressed by the following equation (1). 
       Stress=(Elastic modulus)×(Strain)   (1)
 
     In particular, at a point of time of reaching the breakage, there is a relation expressed by the following equation (2). 
       (Breaking strength)=(Elastic modulus)×(Breaking strain)   (2)
 
     In consequence, from the equation (2), the breaking strain is in a relation expressed by the following equation (3). 
       (Breaking strain)=(Breaking strength)×(Elastic modulus)   (3)
 
     That is, a material having low elasticity and large breaking strain is not broken until a large displacement is applied. It may be considered that such a characteristic feature is able to increase a strain (breaking strain) at the time of reaching breakage, and in a member to be used at a high temperature at which a large strain is easily given, the member is hardly broken. 
     Also, in the case where the C/C composite material according to an embodiment of the invention is used and joined as a structural part of a furnace made of graphite, alumina, zirconia, SiC or the like, or a joining part such as a bolt, there is similarly obtainable an effect for hardly breaking the structural part of a furnace or the joining part. 
     Since the C/C composite material is small in a coefficient of thermal expansion as compared with the structural part made of graphite, alumina, zirconia, SiC or the like, when the structural part is fastened at room temperature (about 25° C.) using a joining part such as a C/C composite material-made bolt, and the temperature is then raised, the C/C composite material-made joining part is pulled, thereby easily generating a thermal strain. Since the C/C composite material according to an embodiment of the present invention is small in an elastic coefficient, it is easily able to make a stress against such a strain small, and therefore, the thermal strain can be easily relieved. 
     In order to prevent the thermal stress generated with such a rise of the temperature from occurring, it would be possible to previously provide a clearance corresponding to the thermal expansion between a member made of a conventional C/C composite material and other structural material such as graphite, alumina, zirconia and SiC. However, it is considered that the larger the temperature between room temperature and a furnace-operating temperature, the larger the clearance at the time of room temperature is. Therefore, not only assembling precision becomes worse, but a gas or heat is easy to flow out the structural material. Also, in an environment where a vapor of silicon or a metal is generated, there may be the case where the conventional C/C composite material and the structural member made of other material are bonded to each other, whereby a state substantially free from a clearance is produced. Therefore, even when a clearance is provided, it is difficult to prevent the generation of a thermal stress. In the C/C composite material according to an embodiment of the invention, since the elastic modulus is small, a clearance may not be provided. Therefore, the foregoing problem regarding the assembling precision is hardly caused, and even when bonded to other structural member, it is considered as possible to easily minimize the generation of a thermal stress. 
     In the present embodiment, a substantially cylindrical part is constituted, and in a section orthogonal to an axis of the cylindrical part, the carbon fibers are oriented along the inner surface thereof. Then, the C/C composite material is used by joining a graphite-made flange part (not shown) to or bringing it into contact with an end of this substantially cylindrical part. In this substantially cylindrical part, since short fibers of carbon fiber are oriented along the inner surface, the fibers are hardly disentangled, and even when subjected to cutting processing, a smooth surface can be easily formed. Furthermore, since the carbon fibers are oriented along the inner surface, continuous pores along the fibers from the surface are hardly formed. For that reason, in the case of using for a silicon single crystal pull-up apparatus or the like, even when pull-up is performed in a reactive gas atmosphere of SiO, Si or the like, it is possible to easily make it difficult to permeate the reactive gas into the inside of the composite material. 
     In consequence, in the silicon single crystal pull-up apparatus, even when used in a reactive gas, for example, SiO, Si or the like, it is possible to easily provide a C/C composite material molded body with a long life, in which a gas hardly permeates into the inside of the C/C composite material. Also, since the thin piece bodies are randomly laminated and formed, a smooth surface can be formed, and a substance with high wettability, such as silicon, is considered as hardly deposited. 
     In the C/C composite material according to an embodiment of the invention, the content of impurities can be decreased by using a halogen gas such as Cl 2  and F 2 , or a halogen based gas such as CF 4  and thermally treating it at a high temperature. For that reason, a C/C composite material with a high purity can be easily obtained. For example, the C/C composite material of the invention can be suitably utilized for a silicon single crystal pull-up apparatus, an SiC single crystal manufacturing apparatus, a polycrystalline silicon manufacturing apparatus, an epitaxial manufacturing apparatus of silicon, a compound, SiC or the like, and so on. 
     The carbon fibers which are used for the C/C composite material of the present Embodiment 1 are not particularly limited. Any of a PAN based or pitch based carbon fiber can be used. Above all, since the PAN based carbon fiber is low in elasticity among carbon fibers, it hardly stores therein a thermal stress or an internal stress by reaction conversion even in the case where the surface partially reacts with SiC or the like to deposit a reaction product. For that reason, it is possible to easily prevent breakage due to reaction conversion of the C/C composite material from occurring, and this C/C composite material can be suitably utilized. 
     Though this C/C composite material is preferably manufactured by adopting a sheet-forming method, it may also be manufactured by any method so far as it is possible to obtain a C/C composite material using short fibers. 
     In the present embodiment, the C/C composite material can be formed by adopting a sheet-forming method. 
     The formation of the C/C composite material is hereunder described in detail centering on the formation of a preform. 
     Outline views of the manufacturing method of a molded body of Embodiment 1 are shown in FIGS.  4 A 1  to  4 D. In these figures, the carbon fibers  1  are configured as a substantially linear fiber. As described later, the C/C composite material molded body according to an embodiment of the present invention is formed by aggregating carbon fibers and a binder in a liquid to form flocks and laminating (sheet-forming) the flocks. The flock as referred to herein means an aggregate of carbon fibers and a binder in which the randomly oriented carbon fibers and the binder are uniformly dispersed and is a base of the thin piece body in the C/C composite material molded body. In view of the fact that the carbon fibers  1  are configured as a substantially linear fiber, in filtering the flocks using a die in a laminating step of flocks (at the time of sheet-forming) as described layer, the carbon fibers pierce the flocks of a lower layer, which is already formed on the surface of the die, and get tangled, and therefore, a joining strength in a vertical direction (thickness direction) to the surface direction of the molded body is easily obtainable. The “substantially linear fiber” as referred to herein means a fiber which does not substantially have a bending part and is preferably an acicular fiber. In the case of using carbon fibers which hardly become a substantially linear fiber, such as carbon fibers having a long fiber length and soft carbon fibers, such a carbon fiber hardly pierces the already formed thin piece body, the longitudinal direction of almost all of the fibers is easily oriented along the surface direction, and the carbon fibers hardly get tangled with each other. Therefore, the joining strength in the thickness direction is considered to be hardly obtainable. 
     It is desirable that the molded body according to an embodiment of the present invention contains a carbon fiber component connecting the thin piece bodies adjoining in the laminating direction of the thin piece body (thickness direction of the molded body) to each other. Also, it is desirable that an orienting component in the thickness direction of the carbon fibers  1  is continuously present in the thickness direction of the molded body. As described above, flocks containing a substantially linear fiber are laminated in such a manner that the substantially linear carbon fiber pierces the already formed flock, and hence, the orienting component in the thickness direction is also continuously formed at a boundary between the flocks. According to this, a hardly separable C/C composite material molded body which does not have an interface in a vertical direction to the thickness direction of the molded body can be easily obtained. 
     An average fiber length of the carbon fibers is desirably less than about 1.0 mm. When the average fiber length of the carbon fibers is about 1.0 mm or more, fibers tends to get tangled together and repel each other at the time of sheet-forming, so that a sheet-formed body with a high bulk density is hardly obtainable. In the case where the bulk density of a laminate of flocks is low, when compression molding is performed using an autoclave or the like, the larger a difference in the bulk density before and after the compression, the higher a compressibility is, a wrinkle is generated in a compression process, and in particular, a corner part is easily lined with wrinkles, and a defect increases. When such a defect increases, a portion with low strength is likely to be generated in the corner part. When the average fiber length of the carbon fibers is less than about 1.0 mm, a void of the sheet-formed body is easily filled, and the carbon fibers become linear. Therefore, a sheet-formed body with a higher bulk density can be obtained, and hence, the compressibility can be made low in undergoing compression molding using an autoclave. According to this, the generation of a wrinkle in the corner part or the like can be suppressed, whereby a C/C composite material molded body with a less defect can be easily obtained. 
     Furthermore, when the average fiber length of the carbon fibers is about 1.0 mm or more, the carbon fibers are easily bent, and the longitudinal direction of the carbon fibers is oriented in the surface direction of the C/C composite material molded body at the time of sheet-forming. For that reason, tangling among fibers in the thickness direction is few, and separation is easy to occur. On the other hand, when the average fiber length of the carbon fibers is less than 1.0 mm, the carbon fibers are easy to become a substantially linear fiber and easy to pierce the already formed flock of a lower layer at the time of sheet-forming, and the joining strength in the thickness direction of the molded body is easily obtainable. Further, when the average fiber length of the carbon fibers is about 1.0 mm or more, the fibers oriented in the vertical direction to the die is easy to break at the time of pressure molding in addition to that the orienting component in the vertical direction to the die surface at the time of sheet-forming is few. Therefore, the interlaminar strength is hardly obtainable and the interlaminar separation easily occurs. 
     The average fiber length of the carbon fibers is desirably in the range of about 0.05 mm or more and less than about 0.5 mm. When the average fiber length of the carbon fibers is less than about 0.5 mm, not only the strength in the thickness direction of the carbon fiber-reinforced carbon composite material molded body can be more increased, but since short fibers are easily filled in a high density, the density especially at the time of laminating flocks can be increased, and the compressibility at the time of molding can be easily increased. When the average fiber length of the carbon fibers is about 0.05 mm or more, an effect of the carbon fibers reinforcing the matrix is hardly lost, and the fibers hardly lose the property of the fibers, whereby a molded body with high strength is obtainable. 
     An average fiber diameter of the carbon fibers is preferably from about 1 to about 20 μm. Also, an aspect ratio of the carbon fibers is preferably from about 10 to about 1,000. When the average fiber diameter and the aspect ratio of the carbon fibers fall within the foregoing ranges, respectively, the fiber diameter can be made sufficiently thin relative to the fiber length, and the fibers are hardly drawn out from the matrix, and hence, high strength is obtainable. 
     As the carbon fibers, any of a pitch based carbon fiber or a PAN based carbon fiber can be suitably used. In particular, the PAN based carbon fiber is preferably used as having lower elastic modulus compared with that of the pitch based carbon fiber. Since the PAN based carbon fiber is low in elastic modulus as compared with the pitch based carbon fiber, it can be suitably used for applications requiring flexibility, for example, a crucible for single crystal pull-up apparatus, a heat insulating cylinder, a crucible receptacle, a heater, etc. 
     The C/C composite material according to an embodiment of the present invention preferably has a bulk density of about 1.2 g/cm 3  or more. When the bulk density of the molded body is about 1.2 g/cm 3  or more, since a void of the C/C composite material is few, joining among the carbon fibers by the matrix is likely to become dense, and the carbon fibers hardly leave. For that reason, a dense C/C composite material molded body with higher strength can be easily obtained. Further, the C/C composite material according to an embodiment of the present invention preferably has a bulk density of about 1.8 g/cm 3  or less. When the bulk density of the molded body is about 1.8 g/cm 3  or less, a gas generated at the time of calcination after molding is easily removed, whereby expansion or interlaminar separation hardly occurs. 
     The manufacturing method of the C/C composite material molded body according to an embodiment of the present invention is hereunder described.  FIG. 3  is a flow chart of manufacturing steps of the molded body according to an embodiment of the present invention; and FIGS.  4 A 1  to  4 D are outline views showing a manufacturing method of the molded body. 
     1. Step (A): Flock Forming Step SA 
     First of all, as shown in  FIG. 3  and FIGS.  4 A 1  to  4 A 2 , the carbon fibers  1  and a binder that is a precursor component of a carbonaceous matrix are suspended in a liquid to spread the carbon fibers into bare fibers, and thereafter, an aggregating agent is added to aggregate the carbon fibers  1  and the binder, thereby forming flocks  5 . As shown in FIG.  4 A 1 , the carbon fibers  1  are first dispersed in a liquid to form a slurry, and as shown in FIG.  4 A 2 , the slurry is then aggregated with a lapse of time, thereby forming the flocks  5 . Herein, the fiber spreading as referred to means disentangling the bundle of carbon fibers into respective fibers. Generally, carbon fibers are bundled into several hundreds to several thousands of fibers with a sizing material being coated to form a strand. In the step of spreading fibers, each fiber is disentangled from the bundle of fibers. 
     2. Step (B): Step SB of Forming a Laminate of Flocks 
     Subsequently, as shown in of  FIG. 3  and  FIG. 4B , the liquid having the flocks  5  formed therein is filtered by the die  20  having the porous die face  21 . The porous die face  21  has a large number of openings  21 A on a side surface thereof. According to this, the flocks  5  are laminated on the surface of the porous die face  21 , thereby forming a laminate  50  of flocks (perform, a first molded body). 
     Different from a conventional technique of direct filtration (sheet-forming) of a slurry having carbon fibers suspended therein, the manufacturing method according to an embodiment of the present invention is characterized in that the carbon fibers are once aggregated together with the binder to form flocks, which are then filtered (formed). According to this, even when lamination of the flocks  5  onto the porous die face  21  proceeds, the liquid is able to permeate between the flocks  5 , and therefore, the thick laminate  50  of flocks which hardly blocks the permeation of the liquid is easily obtainable. Also, as shown an enlarged view of  FIG. 4C , even in the case of making the average fiber length of the carbon fibers  1  smaller than the openings  21 A of the porous die face  21  for the purpose of making the passing resistance of water small, the flocks  5  can be formed larger than the opening  21 A. In consequence, the laminate  50  of flocks (perform) can be easily formed without allowing the carbon fibers  1  to pass through the opening  21 A at the time of filtration. 
     3. Step (C): Step SC of Molding a Laminate of Thin Piece Body Precursor (Second Molded Body) 
     Subsequently, as Step (C), as shown  FIG. 3  and  FIG. 4C , the laminate  50  of flocks (perform) is integrally pressurized. The “integrally” as referred to herein means molding is performed without laminating a plurality of molded body. According to this, the longitudinal direction of the carbon fibers  1  is oriented substantially in parallel to the surface direction of the porous die face  21 . Then, the flocks  5  are converted into a thin piece, thereby forming a thin piece body precursor  6  as shown in  FIG. 4D . In this way, a laminate  6  of thin piece body precursor (pressured molded perform) is formed. 
     4. Step (D): Calcination Step SD 
     Then, as Step (D), as shown in  FIG. 3  and  FIG. 4D , the laminate  60  of thin piece body precursor is calcined. According to this, a binder  4  is carbonized to form the carbonaceous matrix  2  as shown in  FIG. 1D , whereby the laminate  6  of thin piece body precursor becomes the thin piece body  3 . In this way, a laminate of the thin piece bodies  3 , namely the C/C composite material molded body  100  according to an embodiment of the present invention, is obtained. 
     Next, each of the steps is hereunder described in more detail. 
     [Regulation of Carbon Fiber] 
     It is preferable that the carbon fibers are regulated so as to agree with the molded body according to an embodiment of the present invention. On the surface of a carbon fiber for a carbon fiber-reinforced plastic (hereinafter also referred to as “CFRP”) which is used for generally widely circulated fishing rods or aircraft parts or the like, a coating film of a sizing agent or the like is formed, and therefore, such a carbon fiber is hardly dispersed in water at the time of sheet-forming. For that reason, a carbon fiber which is free from a coating film of a sizing agent or the like is chosen, or the sizing agent or the like is removed by thermally treating such a carbon fiber in a reducing atmosphere using a hydrocarbon gas generated from an organic material, hydrogen or carbon monoxide gas. Other than the reducing atmosphere, inert gas atmosphere using a nitrogen gas, a noble gas or the like can be also used. Incidentally, scraps generated in a process of manufacture of CFRP may also be used. Such a coating film can be removed by means of thermal treatment at about 500° C. or higher. Subsequently, it is preferable that the carbon fiber is regulated so as to have an average fiber length of less than about 1.0 mm. When the average fiber length of the carbon fiber is less than about 1.0 mm, as described above, the bulk density can be easily increased at the stage of a laminate of flocks (sheet-formed body); the generation of a wrinkle at the time of molding can be easily suppressed; the generation of a portion having weak strength can be easily suppressed; joining strength in the thickness direction of the molded body is obtainable; and a hardly separable molded body with high strength is easily obtainable. The carbon fiber having an average fiber length of less than about 1.0 mm can be obtained by pulverizing commercially available carbon fibers or scraps of cloths, strands or the like generated in a process of manufacture of CFRP. By pulverizing scraps of cloths, strands or the like of carbon fibers, a raw material of carbon fiber having an average fiber length of less than about 1.0 mm, which does not leave traces of cloths, strands or the like and which is easily utilized in the invention, can be obtained. Incidentally, pulverization can be achieved by means of dispersion in water and uniform pulverization using a mixer. 
     [Flock Forming Step (A)] 
     For forming flocks, it is desirable to use water as the liquid. This is because a large amount of the liquid is used, and therefore, not only water can be safely used as compared with organic solvents, but the treatment of a waste liquid is easy. 
     As the binder including a precursor component of the carbonaceous matrix (hereinafter also referred to as a “first binder”), any material is useful so far as it is insoluble in the foregoing liquid in which the carbon fibers are suspended and is carbonized. In view of avoiding formation of voids in the inside of the C/C composite material, the first binder is preferably powdery and preferably has a particle diameter of from about 3 to about 100 μm. As the first binder, for example, at least one selected from thermosetting resins such as phenol resins, furan resins and imide resins can be suitably utilized. As the phenol resin, for example, Bell Pearl (registered trademark), manufactured by Air Water Inc. can be suitably utilized. Bell Pearl is a powdery phenol resin, and a hydrophobic coating film is formed on the surface thereof. Thus, Bell Pearl keeps the powdery state without being dissolved even in water, so that it is able to aggregate together with the carbon fibers. 
     An addition amount of the first binder is preferably from about 50 to about 200 parts by weight based on 100 parts by weight of the carbon fiber. When the addition amount of the first binder is about 50 parts by weight or more, the amount of carbonaceous matrix hardly becomes smaller and the strength of the molded body is hardly lowered. When it is about 200 parts by weight or less, a gas generated during the manufacturing process of a C/C composite material hardly causes an expansion of interlaminar separation in the C/C composite material. 
     As the aggregating agent which is used in an embodiment of the present invention, any material is useful so far as it is able to aggregate the carbon fibers and the binder while utilizing a change of electric charges. Preferably, a material capable of regulating a ζ-potential so as to fall about within about ±10 mV is desirable. By lowering the ζ-potential, the repulsive force between the binder particles and the carbon fibers can be reduced, so that the aggregation easily occurs. For example, an inorganic aggregating agent material, an organic polymer aggregating agent and the like can be utilized. Specifically, Percol 292 (registered trademark, manufactured by Allied Colloid Company) that is an organic polymer aggregating agent and the like can be suitably utilized. When the flock is formed, the state of a slurry colored black with the carbon fibers changes into a state of a mixed liquid in which the black flock floats in a transparent liquid. The organic polymer aggregating agent can be preferably used in view of the fact that it has a large molecular weight, has a crosslinking action and is able to obtain a large flock. 
     An addition amount of the aggregating agent is preferably from about 0.01 to about 5 parts by weight based on 100 parts by weight of the carbon fibers and more preferably about 0.5 to about 1 parts by weight based on 100 parts by weight of the carbon fibers. When the addition amount of the aggregating agent falls within the foregoing range, a favorable flock which hardly collapses can be formed. 
     Also, although a size of the opening of the porous die face is not particularly limited, it is preferably from about 0.5 to about 10 mm, and more preferably from about 1 to about 3 mm. When the size of the opening of the porous die face is about 0.5 mm or more, the carbon fibers hardly cause clogging, so that the passing resistance of water hardly becomes large. When the size of the opening of the porous die face is about 10 mm or less, since a suction force obtained by multiply an opening area by a negative pressure is hardly generated in the opening, even a flock having such a size that it does not originally pass is hardly sucked and allowed to pass. The size of the flock is preferable to be substantially equal to or more than the size of the opening of the porous die face used for filtration. Since the size of the flock has a distribution, when a flock having a large diameter is trapped by the die face, deposition of flocks on the porous die face starts. When an average diameter of the flock is largely lower than the size of the opening of the porous die face, the majority of flocks tend to pass through the die face, so that the flocks hardly deposit on the die face. The average diameter of the flock in the mixed liquid is preferably from about 0.5 to about 10 mm, and more preferably from about 1 to about 5 mm. The size of the flock can be regulated by an amount of the aggregating agent, a type of the aggregating agent, aggregation time or strength of stirring. 
     It is preferable that a second binder is further added in the liquid for forming a flock. Since the foregoing first binder component is powdery at a sheet-forming stage, it is not able to keep the shape of the laminate of flocks (sheet-formed body). The second binder is a component which is added for the purpose of keeping the shape of the laminate of flocks (sheet-formed body) to be obtained subsequently until a subsequent calcination step. As the second binder, any material may be used so far as it is able to keep the shape of the laminate of flocks. Any material having an action to physically couple the carbon fibers and the first binder, and also the carbon fibers each other at a stage of forming the laminate of flocks may be used, and examples thereof include viscous liquids and organic fibers. As the viscous liquid, starch, latexes and the like can be suitably utilized. When the latex is mixed with water, it becomes cloudy to form a suspension. A droplet of the finely dispersed latex has an action to couple the carbon fibers with the first binder by an adhesive action. As the organic fiber, pulp or the like can be suitably utilized. The pulp has a good affinity with water and tangles with the carbon fibers to reveal an action to couple the carbon fibers with the first binder. In the case where a viscous liquid is used as the second binder, for example, as shown in  FIG. 4C , in view of the fact that a second binder  7   a  intervenes between the carbon fiber  1  and the first binder  4 , and a second binder  7   b  intervenes between the carbon fibers  1 , the shape of the laminate  50  of flocks is kept. 
     Incidentally, in forming the flocks, the addition order of the foregoing carbon fibers, first binder, aggregating agent and second binder is not particularly limited, and they may be added in the liquid simultaneously or successively. However, from the viewpoint of forming the flocks uniformly and stably, it is preferable to undergo the preparation in the following order.
     (a) The carbon fibers are added in water and dispersed with stirring. When stirring is too strong, bubbles are formed, and hence, such is not preferable. As stirring means, a propeller type, a paddle type or the like can be used. A stirring time of the carbon fibers is preferably about 3 minutes.   (b) Subsequently, the first binder is added, and stirring is continued until the first binder is dispersed. A stirring time is preferably from about 0.5 to about 5 minutes.   (c) Subsequently, the second binder is added, and stirring is continued until the second binder is dispersed. A stirring time is preferably from about 0.5 to about 5 minutes.   (d) Finally, the aggregating agent is added. When stirring is few, the aggregating agent is not mixed, whereas when stirring is excessive, the formed flocks are broken. A stirring time is regulated while confirming a degree of formation of flocks. The stirring time is preferably from about 20 to about 30 seconds.   

     [Forming Step (B) of Laminate of Flocks] 
     The die  20  is dipped in the liquid containing the thus formed flocks  5 . As shown in  FIG. 4B , the die  20  is provided with the porous die face  21  having a substantially cylindrical shape and a vacuum chamber  22 . The porous die face  21  is provided with the openings  21 A. The vacuum chamber  22  is connected to a suction pump (not shown) by a conduit  23 . In consequence, when the suction pump is actuated, air within the vacuum chamber  22  is discharged, thereby presenting a vacuum state. Then, the flocks  5  are suctioned on the side of the die  20 . Since the size of the flock  5  is larger than the size of the opening  21 A, the flocks  5  do not pass through the openings  21 A but are laminated as a continuous layer on the surface of the porous dye surface  21  in the surface direction of the porous die face. On that occasion, the flocks  5  are laminated such that carbon fibers pierce the already formed laminate. The laminated flocks  5  become slightly flat from a spherical shape due to an influence of the suction force, and the longitudinal direction of the carbon fibers  1  within the flocks is oriented substantially in parallel to the surface direction of the porous die face  21 . On the other hand, the liquid passes through the openings  21 A and is discharged out through the conduit. In this way, the laminate  50  of flocks (perform, first molded body) can be formed. 
     As the porous die face  21 , any material having plural openings through which the liquid is able to pass is useful, and examples thereof include nets, punching metals, woven fabrics and nonwoven fabrics. When using water as the liquid, the openings of the porous die face preferably has a diameter of about 1 to about 3 mm which water can easily pass through. 
     Incidentally, although the shape of the die is described later, a plane and/or a combination of plural planes, a three-dimensional curved surface and/or a combination of curved surfaces, a substantially cylinder having a flange, a substantially cone, a bottomed body, a substantially circular cylinder and so on can be properly chosen. 
     Also, at the time of suction filtration, any material may be used for undergoing the pressure reduction. In addition to air, other liquid can be suctioned together, and hence, a self-suction type centrifugal pump, an aspirator or the like can be suitably utilized. 
     Incidentally, as a method of filtration, in addition to the foregoing suction filtration, pressure filtration, centrifugal filtration or other method may be adopted. The pressure filtration is, for example, a method in which the outer surface side of the porous die face is pressurized by a pressurized gas to laminate flocks on the outer surface of the porous die face, thereby forming a laminate of flocks. The centrifugal filtration is, for example, a method in which a flock-containing mixed liquid is supplied into the inside of a die of a rotary body having a porous die face placed on the inner surface thereof, the rotary body is rotated to laminate flocks on the inner surface of the porous die face, thereby forming a laminate of flocks. 
     [Drying Step] 
     Subsequently, in order to remove water remaining in the laminate of flocks obtained in the preceding step, it is preferable to dry the laminate together with the die. Drying is preferably performed at about 40° C. or higher for the purpose of removing water. Also, in order to prevent melting and curing of the first binder, it is preferable to perform drying at a temperature of not higher than a melting temperature of the first binder. For example, in the case of using Bell Pearl (registered trademark) as the first binder, taking into consideration the fact that the hydrophobic coating film is melted at about 70° C., drying is performed at not higher than about 60° C. while ventilating air, whereby water can be easily removed. 
     [Pressurizing Step] (Molding Step (C)) 
     In the case where the molded body has a plane or a shape close to a plane, a pressurizing method by means of uniaxial molding can be utilized as a molding method. However, this method can be utilized only for a limited structure in which an upper die and a lower die are constituted on the both sides of a cavity. Therefore, when the molded body has a three-dimensional shape, as shown in  FIG. 4C , it is preferably that the laminate  50  of flocks is covered by a sealing film  24  and molded by applying heat and pressure using an autoclave  26 . First all, air within the sealing film  24  is suctioned to draw a vacuum, and a pressure is then applied. A molding pressure is not limited but preferably about 1 MPa or more. When the molding pressure is about 1 MPa or more, it is possible to easily prevent expansion of the sheet-formed body pressurized by a gas generated in curing reaction of a thermosetting resin. At that time, it is preferable to undergo molding while supporting the both sides (inner side or outer side) of the die  20  of the laminate  50  of flocks by a support material  25 . Since there is a concern that the laminate of flocks is softened and deformed by heating, when the laminate is supported by the support material  25 , deformation can be easily prevented from occurring. Different from that of the die  20  used in the forming step (B) of the laminate of flocks, the support material  25  as used herein is one not having a porous die face but having a smooth surface. The molding is performed integrally without laminating laminates (without joining laminates) regardless of the uniaxial molding or the molding using autoclave. Although the laminate itself hardly causes an interlaminar separation, if the molding is performed by laminating, an interlaminar separation tends to occur since fibers hardly couple adjoining laminates once the molded body is dried. 
     [Curing Step] 
     Since the first binder is a thermosetting resin, it is preferable that after sufficiently increasing the pressure in the foregoing pressure molding step, the molded body is heated, thereby melting and curing the thermosetting resin contained in the flocks. According to this, the shape can be easily fixed in such a manner that the laminate  60  of a thin piece body precursor (second molded body) is not deformed. It is necessary to increase a curing temperature to the curing temperature of the thermosetting resin or higher. For example, in general, curing can be performed at from about 150° C. to about 200° C. When the curing temperature is about 150° C. or higher, the curing of the thermosetting resin sufficiently proceeds. When the curing temperature is about 200° C. or lower, foam due to gas generated at the curing of the thermosetting resin can be easily prevented. In the case where the foregoing molding step is performed in an autoclave or other cases, so far as heating can be sufficiently performed in the molding step, the curing step can also be performed simultaneously with the molding step. 
     [Degreasing Step] 
     In order to volatilize an organic component in the inside of the laminate  60  of a thin piece body precursor (second molded body), it is preferable to perform degreasing prior to the calcination step. By way of this degreasing step, the first binder is carbonized, and the majority of the second binder is separated and vaporized. For that reason, the carbide derived from the first binder component is a material having a coupling action after the degreasing step. Any degree of temperature is adaptable for a temperature of the degreasing. In the case where pitch impregnation and resin impregnation are performed after the degreasing step, it is preferable to form pores, and hence, it is preferable to perform the degreasing at about 500° C. or higher. When the temperature is about 500° C. or higher, carbonization of the resin sufficiently proceeds, and pores having a sufficiently large size such that the resin or pitch is impregnated therein in the subsequent impregnation step can be easily formed. Although an upper limit of the degreasing temperature is not particularly limited so far as it is not higher than a temperature of the subsequent calcination temperature. However, the degreasing temperature is preferably about 1,000° C. or lower. By the temperature of about 1,000° C., the majority of degreasing can be completed, so that pores to be impregnated is easily and sufficiently formed. In order to prevent oxidation of the carbon fibers or binder from occurring, it is preferable to perform the degreasing in a reducing atmosphere. In addition to the reducing atmosphere using a hydrocarbon gas generated from an organic material or hydrogen, an inert gas atmosphere using a nitrogen gas, a noble gas or the like can also be applied. 
     [Impregnation Step] 
     It is preferable to impregnate a resin, a pitch or the like in the inside of the pores of the laminate of a thin piece body precursor after the degreasing, thereby realizing a high density. The laminate of a thin piece body precursor after the degreasing is placed in the autoclave, and after drawing a vacuum, a liquid resin or pitch is introduced into the autoclave and dipped, followed by applying a pressure. The liquid resin may be a solution of the resin in water or an organic solvent, or may be a melted material obtained by applying heat. In the case of a solution, even when the use is repeated, polymerization hardly proceeds, so that the solution can be stably used. In the case of a pitch, the pitch is used after being converted into a liquid upon heating the autoclave at a melting point or higher. 
     After completion of the impregnation, similar to the foregoing degreasing step, degreasing is performed, whereby a molded body with a higher density can be obtained. 
     [Calcination Step (D)] 
     By further applying heat to the laminate of a thin piece body precursor to perform calcination, the first binder is thoroughly carbonized, thereby forming a carbonaceous matrix. According to this, the thin piece body precursor becomes a thin piece body, whereby the C/C composite material molded body  100  according to an embodiment of the present invention which is constituted of a laminate of thin piece bodies can be obtained. 
     In the calcination step, the support material thermally expands with an increase of the temperature, and the laminate  60  of a thin piece body precursor (press molded perform, second molded body) thermally shrinks In order to avoid a stress to be caused due to a difference in thermal expansion generated in the calcination step, it is preferable that the support material  25  is removed from the laminate  60  of a thin piece body precursor and heated in a non-oxidizing atmosphere such as a reducing atmosphere or an inert atmosphere. A reducing atmosphere using a hydrocarbon gas generated from an organic material, hydrogen or carbon monoxide gas or an inert gas atmosphere using a nitrogen gas, a noble gas or the like can be used. A desired temperature of the calcination step is from about 1,500 to about 2,800° C. When the calcination temperature is about 1,500° C. or higher, a functional group in the C/C composite material, such as hydrogen, can be easily and sufficiently removed. When a functional group such as hydrogen remains, a hydrocarbon gas or the like is likely to be generated at the time of using the C/C composite material molded body. When a molded body which is not calcined at a calcination temperature of about 1,500° C. or higher is used in a semiconductor manufacturing apparatus or the like, such a hydrocarbon gas is likely to be incorporated into a semiconductor, thereby lowering the purity. When the calcination temperature is not higher than about 2,800° C., the progress of crystallization of the C/C composite material can be easily suppressed, and the strength can be kept. A more desired range of the calcination temperature is from about 1,800 to about 2,500° C. It is preferable that the calcination is performed at a heating rate of about 500° C./hour. 
     According to an embodiment of the present invention, by forming the shape of the porous die face  21  into a shape along the shape of the desired molded body, molded bodies having various three-dimensional shapes in addition to the foregoing shape can be manufactured by means of integral molding. Additionally, it is possible to uniformly disperse carbon fibers, easily, so that a structurally weak part cannot be formed even at a joining part of surfaces. 
     Incidentally, in order to increase the density of the C/C composite material, the impregnation step and the degreasing step may be repeated plural times prior to the calcination step. 
     Incidentally, it is desirable that the dried sheet-formed body obtained in the drying step after sheet-forming is heated at from about 150 to about 200° C. and pressured, and then kept for about 5 minutes or more to achieve curing. Also, it is preferable that the molded body which has been cured in the curing step is heated at about 500° C. or higher to carbonize the first binder component, thereby obtaining a degreased body, and furthermore, the degreased body is calcined at about 1,500° C. or higher in the calcination step. 
     (Average Fiber Length and Fiber Volume Fraction) 
     In the invention, an average fiber length &lt;L&gt; of the carbon fibers may be measured by any method. So far as the carbon fibers are at a stage of raw material, the average fiber length is obtainable by directly measuring a dispersed carbon fiber powder by a scanning electron microscope or the like. As to a calculation method, the average fiber length of the carbon fibers can be determined by measuring all lengths L i  of the carbon fibers existent in an arbitrary region and dividing them by a number n of the carbon fibers as expressed by the following equation (thickness and density of the carbon fibers do not take part in the average fiber length). 
     
       
      
       &lt;L&gt;=ΣL 
       i 
       /n  
      
     
     Also, an average fiber length of the carbon fibers in a state where they are contained in the C/C composite material may be measured by any method. Though it is not easy to extract only the carbon fibers solely, the average fiber length of the carbon fibers can be measured using a method by, for example, a focused ion/electron beam system (FB-SEM) or the like. Specifically, an individual fiber length can be determined by confirming a three-dimensional disposition of fibers by SEM while processing the C/C composite material step-by-step from the surface using a focused ion/electron beam or the like. Furthermore, a fiber volume fraction can be calculated by calculating an area occupied by the carbon fibers every time of processing. 
     Also, in addition to the direct analysis of the C/C composite material, the fiber volume fraction can be determined by dividing a volume of the carbon fibers calculated from a mass and a true density of the carbon fibers used at the manufacturing stage, by a mass and an apparent density (bulk density) of the C/C composite material. 
     Embodiment 
     A molded body of Embodiment 2 of the present invention is described on the basis of  FIGS. 5A to 5D . 
       FIGS. 5A to 5D  are views showing the molded body of Embodiment 2, specifically,  FIG. 5A  is a perspective view;  FIG. 5B  is a sectional view;  FIG. 5C  is an enlarged view of a part of  FIG. 5B ; and  FIG. 5D  is a more enlarged view of a part of  FIG. 5C . Also,  FIGS. 6B to 6D  are outline views showing a manufacturing method of the molded body of Embodiment 2. A C/C composite material molded body  200  of Embodiment 2 is characterized by having a bottom surface and is the same as the molded body  100  of Embodiment 1, except for the matter that it has a bottom surface. 
     In order to manufacture the C/C composite material molded body  200  of Embodiment 2, as shown in  FIG. 6B , the flocks  5  are filtered using a die  30  having a porous die face  31  on each of a side surface and a bottom surface thereof at the time of forming a laminate (preform) of flocks. Also, as shown in  FIG. 6C , a support material  35  in a pressurizing step is made bottomed. Other points are the same as those in the manufacturing method of Embodiment 1. The flocks  5  are laminated along a curved surface direction of the porous die face  31 . Then, as shown in  FIG. 5B , the longitudinal direction of the carbon fibers  1  is oriented in a direction of a surface  200 S of the molded body  200 . According to this, in the resulting molded body  200 , the thin piece bodies are also oriented along the surface  200 S of the molded body  200  in a boundary region between the bottom surface and the side surface, and thus, the boundaries of the thin piece bodies are easily dispersed, thereby easily forming a uniform molded body. 
     In this C/C composite material molded body, the carbon fibers are present in a bare-fiber state within a carbonaceous matrix. Also, the carbon fibers are a substantially linear fiber having an average fiber length of less than about 1.0 mm, and the C/C composite material molded body has a fiber volume fraction of from about 30 to about 50%. Further, the C/C composite material molded body has a bulk density of about 1.2 g/cm 3  or more. 
     Also, in this C/C composite material molded body, it is preferable that a tensile strength of the C/C composite material molded body is about 50 MPa or more, and an elastic modulus of the C/C composite material molded body is from about 5 GPa to about 15 GPa. 
     Embodiment 3  
     A molded body according to Embodiment 3 of the present invention is described on the basis of  FIGS. 12A to 13C .  FIG. 12A  is a perspective view of a C/C composite material molded body of Embodiment 3, and  FIG. 12B  is a sectional view thereof and  FIGS. 13A to 13C  are diagrammatic views showing manufacturing steps of the C/C composite material molded body of Embodiment 3. 
     A C/C composite material molded body  300  of Embodiment 3 is the same as the C/C composite material molded body  100  of Embodiment 1, except for the matter that a flange part  300 T is provided in a lower end of a substantially cylindrical part  300   a.  In this way, in view of the fact that the flange part  300 T is provided, a curved surface constituting the substantially cylindrical surface and a donut-shaped plane are integrally formed adjoiningly in a continuous manner. Here, the thin piece bodies  3  are also oriented along a surface  300 S in a boundary region  300 R between the curved surface constituting the cylindrical surface and the donut-shaped plane, thereby constituting a uniform continuous surface with high strength, and therefore, extremely high strength is easily revealed. Also, the boundaries of the thin piece bodies  3  are easily dispersed in this boundary region  300 R, thereby easily forming a uniform molded body. 
     In manufacturing this C/C composite molded body  300 , the same procedures as those in the foregoing Embodiment 1 are followed. However, a part of the surface of an end  30 E of the die  30  is masked so as to not form the porous die face, thereby depositing no flock. 
     According to this configuration, as shown in  FIG. 13B , flocks are filtered using the die  30  having the porous die face  31  on the side surface and the bottom surface thereof. The flocks are laminated as a continuous body along a curved surface direction of the porous die face  31 . In this way, a thin piece body laminate configured by the cylindrical part  300   a  which is constituted of a first curved surface  300   i  along an outer wall of the die  30  and a second curved surface  300   o  opposing to this first curved surface  300   i  and which has the flange part  300 T is formed, whereby a desired shape can be obtained. 
     Then, similar to the foregoing Embodiments 1 and 2, by way of the drying step, pressurizing step, degreasing step, impregnation step and calcination step, the C/C composite material molded body  300  composed of a cylinder having a flange part as shown in  FIGS. 12A and 12B  can be obtained. In this C/C composite material molded body  300 , the thin piece bodies are also oriented along the first and second surfaces  300   i  and  300   o  in a boundary part, namely a joint part between the flange part and the cylindrical part, and the boundaries of the thin piece bodies are dispersed, thereby forming a molded body having a uniform continuous composition. 
     In the C/C composite material molded body of Embodiment 3, the carbon fibers are present in a bare-fiber state within a carbonaceous matrix. Also, the carbon fibers are a substantially linear fiber having an average fiber length of less than about 1.0 mm, and the C/C composite material molded body has a fiber volume fraction of from about 30 to about 50%. Further, the C/C composite material molded body has a bulk density of about 1.2 g/cm 3  or more. 
     Also, in the C/C composite material molded body of Embodiment 3, it is preferable that a tensile strength of the C/C composite material molded body is about 50 MPa or more, and an elastic modulus of the C/C composite material molded body is from about 5 GPa to about 15 GPa. 
     Embodiment 4  
     A molded body according to Embodiment 4 of the present invention is described on the basis of  FIGS. 14A to 15B .  FIG. 14A  is a perspective view of a C/C composite material molded body of Embodiment 4, and  FIG. 14B  is a sectional view thereof; and  FIGS. 15A and 15B  are diagrammatic views showing manufacturing steps of the C/C composite material molded body of Embodiment 4. 
     A C/C composite material molded body  400  of Embodiment 4 is the same as the C/C composite material molded body  100  of Embodiment 1, except for that a substantially truncated conical cylindrical part  400   b  is provided in a lower end of a substantially cylindrical part  400   a.  In this way, in view of the fact that the substantially truncated conical cylindrical part  400   b  is provided, a curved surface constituting the substantially cylindrical surface and a curved surface constituting the substantially truncated cylindrical part are integrally formed adjoiningly in a continuous manner. Here, the thin piece bodies  3  are also oriented along a surface  400 S in a boundary region  400 R between the curved surface constituting the cylindrical surface and the truncated conical cylindrical part, thereby easily constituting a uniform continuous body with high strength, and therefore, extremely high strength is revealed. Also, the boundaries of the thin piece bodies  3  are easily dispersed in this boundary region  400 R, thereby easily forming a uniform molded body. 
     In manufacturing this C/C composite molded body  400  of Embodiment 4, the same procedures as those in the foregoing Embodiment 3 are followed, except for using a die  40  having an outer surface having a substantially columnar shape and a substantially conical shape. 
     According to this configuration, as shown in  FIG. 15B , flocks are filtered using the die  40  having a porous die face  41  on the side surface thereof. The flocks are laminated as a continuous body in a curved surface direction of the porous die face  41 . In this way, a thin piece body laminate composed of the substantially cylindrical part  400   a  and the substantially truncated conical cylindrical part  400   b,  which is constituted of a first curved surface  400   i  along an outer wall of the die  40  and a second curved surface  400   o  opposing to this first curved surface  400   i,  is formed, whereby a desired shape can be obtained. 
     Then, similar to the foregoing Embodiments 1, 2 and 3, by way of the drying step, pressurizing step, degreasing step, impregnation step and calcination step, the C/C composite material molded body  400  composed of a substantially cylinder having a flange part as shown in  FIGS. 14A and 14B  can be obtained. In this C/C composite material molded body  400 , the thin piece bodies are also oriented along the first and second surfaces  400   i  and  400   o  in a boundary part, namely a joint part between the substantially cylindrical part  400   a  and the substantially truncated conical cylindrical part  400   b,  and the boundaries of the thin piece bodies are dispersed, thereby forming a molded body having a continuously uniform composition in the surface  400 S. 
     In the C/C composite material molded body of Embodiment 4, the carbon fibers are present in a bare-fiber state within a carbonaceous matrix. Also, the carbon fibers are a substantially linear fiber having an average fiber length of less than about 1.0 mm, and the C/C composite material molded body has a fiber volume fraction of from about 30 to about 50%. Further, the C/C composite material molded body has a bulk density of about 1.2 g/cm 3  or more. 
     Also, in the C/C composite material molded body of Embodiment 4, it is preferable that a tensile strength of the C/C composite material molded body is about 50 MPa or more, and an elastic modulus of the C/C composite material molded body is from about 5 GPa to about 15 GPa. 
     Embodiment 5  
     A molded body according to Embodiment 5 of the present invention is described on the basis of  FIGS. 16A and 16B .  FIGS. 16A and 16B  are views showing a molded body of Embodiment 5, specifically,  FIG. 16A  is a perspective view, and  FIG. 16B  is a sectional view. 
     A C/C composite material molded body  500  of Embodiment 5 is configured by a substantially rectangular cylindrical part  500   a  having a bottom part  500   b.  The C/C composite material molded body  500  of this embodiment is the same as the C/C composite material molded body  100  of Embodiment 1, except for the shape of the C/C composite material molded body. In this way, in the present Embodiment 5, four planes constituting the substantially rectangular cylindrical surface and a bottom surface are positioned vertical to each other and integrally formed in a continuous manner. Here, in a boundary region  500 R between the planes substantially orthogonal to each other, the thin piece bodies  3  are also oriented along a surface  500 S, thereby constituting a uniform continuous surface with high strength, and hence, extremely high strength is revealed. Also, in this boundary region  500 R, boundaries of the thin piece bodies  3  are also easily dispersed, thereby easily forming a uniform molded body. 
     In the C/C composite material molded body of Embodiment 5, the carbon fibers are present in a bare-fiber state within a carbonaceous matrix. Also, the carbon fibers are a substantially linear fiber having an average fiber length of less than 1.0 mm, and the C/C composite material molded body has a fiber volume fraction of from about 30% to about 50%. Further, the C/C composite material molded body has a bulk density of about 1.2 g/cm 3  or more. 
     Also, in the C/C composite material molded body of Embodiment 5 of the invention, it is preferable that a tensile strength of the C/C composite material molded body is about 50 MPa or more, and an elastic modulus of the C/C composite material molded body is from about 5 GPa to about 15 GPa. 
     Embodiment 6  
     A molded body according to Embodiment 6 of the present invention is described on the basis of  FIGS. 17A to 18D .  FIG. 17A  is a perspective view of a molded body  600  of the present Embodiment 6 composed of a C/C composite material.  FIG. 17B  is a sectional view of  FIG. 17A ;  FIG. 17C  is an enlarged view of a part of  FIG. 17B ; and  FIG. 17D  is a more enlarged view of a part of  FIG. 17C . The molded body  600  of Embodiment 6 is the same as the C/C composite material molded body  100  of Embodiment 1, except for that the shape is a substantially plate-like shape. 
     FIGS.  18 A 1  to  18 D are outline views showing a manufacturing method of a molded body of Embodiment 6. A manufacturing method of the molded body of Embodiment 6 is hereunder described in detail. 
     [Flock Forming Step (A)] 
     A step (A) of forming flocks can be performed in the same manner as that in the step (A) in Embodiment 1. 
     [Forming Step (B) of Laminate of Flocks] 
     Subsequently, as a step (B) of forming a laminate of flocks, as shown in  FIG. 18B , a liquid having the flocks  5  formed therein is filtered by the die  40  having the porous die face  41 . The porous die face  41  has a large number of openings  41 A on the upper surface thereof. When the liquid is pressurized from an upper surface thereof by a pressure plate  42 , the liquid passes through the openings  41 A and is discharged out from a water storage chamber  44  via a valve  43 . Since the size of the flock  5  is larger than the size of the opening  41 A, the flocks  5  do not pass through the openings  41 A but are laminated as a continuous layer on the surface of the porous dye surface  41  in the surface direction of the porous die face. On that occasion, the flocks  5  are laminated so as to pierce the already formed laminate. The laminated flocks  5  become slightly flat from a spherical shape due to an influence of the suction force, and the longitudinal direction of the carbon fibers  1  within the flocks is oriented in the surface direction of the porous die face  41 . In this way, a laminate  50 F of flocks (preform, i.e., a first molded body) is formed. 
     As the porous die face  41 , any material having plural openings through which the liquid is able to pass is usable, and examples thereof include nets, punching metals. woven fabrics and nonwoven fabrics. In the case of using water as the liquid, a size of the opening is preferably from about 1 to about 3 mm in terms of a diameter at which water is easy to pass therethrough. 
     Also, the filtration may be performed by any method. For example, in the case of suction filtration, in addition to air, the liquid is also suctioned together, and hence, a self-suction type centrifugal pump, an aspirator or the like can be suitably utilized. 
     Incidentally, as a filtration method, in addition to the foregoing suction filtration, pressure filtration or a method of filtration by means of simple gravity may be adopted. The pressure filtration is, for example, a method in which the outer surface side of the porous die face is pressurized by a pressurized gas to laminate flocks on the outer surface of the porous die face, thereby forming a laminate of flocks. 
     [Pressurizing Step] (Molding Step (C)) 
     Then, by integrally compressing the laminate  50 F of flocks without being laminated, the longitudinal direction of the carbon fibers is oriented in a surface direction orthogonal to the laminating direction, thereby forming a molded body  60 F. In the case where the molded body is in a plate-like shape, a pressurizing method by means of uniaxial molding can be utilized as a pressure molding method. As shown in  FIG. 18C , the laminate  50  of flocks is interposed by press plate materials  45  and then pressurized. A molding pressure is preferably about 1 MPa or more. When the molding pressure is 1 MPa or more, since the laminate of flocks can be sufficiently compressed, a C/C composite material with high density and high strength can be easily obtained. Although there is no particular upper limit of the molding pressure, since the first binder is softened by applying heat, when a pressure of 10 MPa is applied, a molded body with sufficiently high density and high strength can be obtained. According to this, the longitudinal direction of the carbon fibers  1  is oriented substantially in parallel to the surface direction of the porous die face  41 . Then, the flocks  5  are converted into a thin piece, thereby forming a thin piece body precursor. In this way, there is molded the laminate (press molded preform, i.e., a second molded body) of the thin piece body precursor. 
     With respect to the resulting molded body  60 F of the thin piece body precursor, similar to Embodiment 1, a molded body  600  of Embodiment 6 is obtained by way of the curing step, degreasing step, impregnation step and calcination step (D). 
     Incidentally, the surface direction of the molded body as referred to herein means a principal surface constituting the molded body and means that an end surface is not included. A surface which after the calcination, is newly formed by means of polishing, boring or mechanical processing of the surface is not included. As described above, by taking a configuration in which the longitudinal direction of the carbon fibers is continuously oriented along the outer surface at the time of molding by the sheet-forming method, a C/C composite material molded body having extremely high mechanical strength and excellent heat resistance can be obtained. 
     EXAMPLES  
     The present invention is hereunder described in more detail with reference to the following Examples and Comparative Examples, but it should not be construed that the invention is limited to these Examples. 
     Example 1  
     (1) Carbon Fiber Preparation Step 
     PAN based carbon fibers for CFRP having an average fiber diameter of 7 μm were prepared. Here, after a sizing agent coated on the fiber surface for the purpose of improving dispersibility into water was calcined in a reducing atmosphere at 550° C. and removed, the carbon fibers were dispersed in water and pulverized to an average fiber length of 150 μm using a mixer, followed by dehydration and drying. Then, the resulting carbon fibers were heated together with an organic material powder capable of generating a large amount of a hydrocarbon gas in a sealed vessel, and the inside of the sealed vessel was purged with a hydrocarbon gas generated from the organic material, thereby forming a reducing atmosphere. 
     (2) Flock Forming Step
     (a) The carbon fibers obtained in the preceding carbon fiber preparation step were thrown into water and dispersed while stirring. Stirring was performed for about 3 minutes.   (b) Subsequently, a phenol resin (“Bell Pearl” (registered trademark) S890, manufactured by Air Water Inc.) (200 parts by mass) was added as a first binder to 100 parts by mass of the carbon fibers, and the mixture was similarly stirred for one minute.   (c) Subsequently, a latex (5 parts by mass) was added as a second binder, and the mixture was similarly stirred for one minute.   (d) Furthermore, a cationic aggregating agent (“Percol” (registered trademark) 292, manufactured by Allied Colloid Company) (0.3 parts by mass) was added as an aggregating agent, and the mixture was stirred for 20 seconds, thereby forming flocks.   

     (3) Flock Laminate Forming Step (Sheet-Forming Step) 
     Water having flocks formed therein was sucked from the inside of a cylindrical die provided with a wire net having an opening of 1 mm on an outer surface thereof to laminate the flocks on the surface of the wire net, thereby forming a cylindrical laminate. Though the wire net had an opening of 1 mm, the carbon fibers formed the flocks, and hence, almost all of the carbon fibers did not pass through the net. After standing for a while as it was and removing water by means of a gravitational force, the resultant was dried by a dryer at 60° C. 
     (4) Molding Step (Formation of Laminate of Thin Piece Body Precursor) 
     A wire net-free cylindrical die was inserted into the inside of the laminate obtained in the preceding step, and the surface was further covered by a sealing film. The resultant was placed in an autoclave without laminating the laminates and pressurized while applying heat at 150° C. A pressurizing pressure was set to 2 MPa. 
     (5) Curing Step 
     Subsequent to the preceding step, the laminate was allowed to stand for 2 hours as it was under a maximum pressure in the autoclave. According to this step, the first binder (phenol resin) was cured. 
     (6) First Degreasing Step 
     The die of the laminate obtained in the preceding curing step was removed, and the resultant was heated in a reducing atmosphere furnace. Heating was performed at a temperature rise rate of 70° C/hour, and at a point of time when the temperature reached a maximum temperature of 550° C., the resulting laminate was kept for one hour and then allowed to stand for cooling to room temperature. Here, the reducing atmosphere is formed by heating the laminate with an organic material powder which can generate a large amount of hydrocarbon gas in a closed container, and purging the closed container with the hydrocarbon gas from the organic material. 
     (7) (Impregnation Step) 
     In the case where a desired bulk density is not obtained until the first degreasing step, impregnation is further performed. 
     In this Example, the laminate after degreasing was placed in an autoclave heated at 200° C., and after drawing a vacuum, a pitch having a softening point of about 80° C. was allowed to flow in. The laminate was pressurized at 4 MPa, thereby impregnating the pitch thereinto. 
     (8) (Second Degreasing Step) 
     The laminate having gone through the impregnation step is again subjected to degreasing. The degreasing was performed under a condition the same as the condition in the first degreasing step of (6). The impregnating step and the second degreasing step can be performed repeatedly. 
     (9) Calcination Step 
     The laminate having been subjected to the impregnation and the second degreasing step was finally calcined. The laminate was heated at a temperature rise rate of 150° C/hour in a reducing atmosphere, and at a point of time when the temperature reached a maximum temperature of 2,000° C., the resulting laminate was kept for 15 seconds and then allowed to stand for cooling to room temperature. The reducing atmosphere is formed by a mixed gas of hydrogen, carbon monoxide gas and hydrocarbon gas generated by heating while putting the laminate in carbon powders in a state of preventing oxide from the outside. According to this calcination step, a matrix was formed from the first binder. According to the presence of the matrix, a bonding force of carbon fibers is strengthened, and strength can be revealed. In this way, there was obtained a cylindrical structure having an inner diameter of 1,000 mm, a height of 1,000 mm, a thickness of 25 mm. 
     Example 2  
     A C/C composite material molded body was obtained in the same manner as that in Example 1, except for changing the average fiber length of the carbon fibers to 800 μm. 
     Comparative Example 1  
     A molded body of Comparative Example 1 made of a C/C composite material having felts laminated therein was manufactured. First all, PAN based carbon fibers were cut into a size of 30 mm, thereby forming a sheet-like felt. Subsequently, the felt was dipped in a methanol solution of a phenol resin, from which was then formed a carbon fiber sheet prepreg having a thickness of 3 mm by using a roll press. The thus formed carbon fiber sheet prepreg was allowed to revolve around a mandrel, thereby forming a molded body having felt-like sheets laminated thereon. 
     Subsequently, the molded body molded in the preceding step was kept at 150° C. to cure the phenol resin, thereby fixing the shape. 
     Subsequently, degreasing, impregnation, degreasing and calcination were performed in the same manner as that in Example 1, thereby obtaining a cylindrical molded body having an inner diameter of 600 mm, a height of 600 mm and a thickness of 25 mm. 
     Comparative Examples 2 to 11  
     A C/C composite material molded body of Comparative Example 2 was manufactured in the same manner as that in Example 1, except that the pressurizing pressure in the molding step (4) was changed to 0.8 MPa. 
     Molded bodies of commercially available C/C composite materials shown in Table 2 were prepared as Comparative Examples 3 to 11. Comparative Example 3 is manufactured by means of filament winding; Comparative Examples 4 to 10 are manufactured by means of cloth lamination; and Comparative Example 11 is manufactured by means of felt lamination. 
     &lt;Evaluation of Physical Properties&gt; 
     Bulk Density and Bending Strength 
     Two samples for measuring physical properties of a rectangular parallelepiped shown in  FIG. 22A , each of which was longer in a height direction of the cylinder, were obtained from the structure obtained in each of Example 1 and Comparative Example 1. The sample for measuring physical properties was measured with respect to a bulk density and a bending strength. The bulk density of the molded body was calculated by dividing the mass of the C/C composite material by the volume thereof. The bending strength was measured by performing a three-point bending test using an autograph (AG-IS Model: 0 to 5 kN), manufactured by Shimadzu Corporation.  FIGS. 22A and 22B  are schematic views showing a method of cutting out a sample for measuring physical properties and a test direction of a three-point bending test. The three-point bending test was performed from two directions of a vertical direction (laminating direction of thin piece body) V and a parallel direction P relative to a surface direction of the structure, as shown in  FIG. 22B . 
     Table 1 shows measuring results of the bulk density and the bending strength of the C/C composite material molded body according to Example 1 and Comparative Example 1. 
     
       
         
           
               
               
               
               
             
               
                   
                 TABLE 1 
               
               
                   
                   
               
               
                   
                   
                 Bending strength 
                 Bending strength 
               
               
                   
                   
                 in the vertical 
                 in the parallel 
               
               
                   
                 Bulk density 
                 direction * 1   
                 direction * 2   
               
               
                   
                 (g/cm 3 ) 
                 (MPa) 
                 (MPa) 
               
               
                   
                   
               
             
            
               
                   
               
            
           
           
               
               
               
               
            
               
                 Example 1 
                 1.28 
                 69.0 
                 75.7 
               
               
                 Comparative 
                 1.35 
                 19.6 
                 47.2 
               
               
                 Example 1 
               
               
                   
               
               
                 * 1  Three-point bending test from the surface direction and the vertical direction of the molded body 
               
               
                 * 2  Three-point bending test from the surface direction and the parallel direction of the molded body 
               
            
           
         
       
     
     In Examples 1 and 2 and Comparative Examples 1 to 11, the following physical properties were determined. 
     Fiber Volume Fraction 
     A mass and a true density of the used carbon fibers were measured, and a volume of the carbon fibers was calculated by dividing the mass of the carbon fibers by the true density of the carbon fibers. A mass and an apparent density (bulk density) of the C/C composite material were measured, and a volume of the C/C composite material was calculated by dividing the mass of the C/C composite material by the bulk density of the C/C composite material. Incidentally, four samples of 10 mm×10 mm×60 mm were processed from the C/C composite material molded body, and values calculated from the measured volume and mass were averaged. A fiber volume fraction was calculated by dividing the volume of the carbon fibers by the volume of the C/C composite material. 
     Elastic Modulus, Breaking Strength and Breaking Strain 
     The measurement was performed using an autograph (AG-IS Model: 0 to 5 kN), manufactured by Shimadzu Corporation. Incidentally, the breaking strength was determined as a tensile strength. 
     The manufacturing method of each of the composite materials of Examples 1 and 2 and Comparative Examples 1 to 11 is shown in Table 2 along with the measurement results of the average fiber length, fiber volume fraction, bulk density, elastic modulus, breaking strength (tensile strength) and breaking strain thereof. 
     
       
         
           
               
               
               
               
               
               
               
               
             
               
                 TABLE 2 
               
               
                   
               
               
                   
                   
                   
                 Fiber  
                   
                   
                 Breaking  
                   
               
               
                   
                   
                 Average 
                 volume 
                 Bulk  
                 Elastic 
                 strength 
                 Breaking 
               
               
                   
                 Manufacturing 
                 fiber 
                 fraction  
                 density 
                 modulus  
                 (tensile strength) 
                 strain  
               
               
                   
                 method 
                 length 
                 (%) 
                 (g/cm 3 ) 
                 (GPa) 
                 (MPa) 
                 (ppm) 
               
               
                   
               
             
            
               
                   
               
            
           
           
               
               
               
               
               
               
               
               
            
               
                 Example 1 
                 Sheet-forming 
                 150 μm 
                 35 
                 1.3 
                 11 
                 98 
                 8909 
               
               
                 Example 2 
                 Sheet-forming 
                 800 μm 
                 37 
                 1.3 
                 14 
                 124 
                 8857 
               
               
                 Comparative 
                 Felt lamination 
                  30 mm 
                 41 
                 1.4 
                 41 
                 183 
                 4463 
               
               
                 Example 1 
                   
                   
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Sheet-forming 
                 150 μm 
                 26 
                 1.1 
                 6 
                 31 
                 5000 
               
               
                 Example 2 
                   
                   
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Filament winding 
                 Continuous  
                 — 
                 1.5 
                 100 
                 300 
                 3000 
               
               
                 Example 3 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination  
                 Continuous  
                 — 
                 1.6 
                 80 
                 350 
                 4375 
               
               
                 Example 4 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination 
                 Continuous  
                 — 
                 1.4 
                 30 
                 60 
                 2000 
               
               
                 Example 5 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination 
                 Continuous 
                 — 
                 1.5 
                 55 
                 185 
                 3364 
               
               
                 Example 6 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination 
                 Continuous  
                 — 
                 1.6 
                 50 
                 170 
                 3400 
               
               
                 Example 7 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination  
                 Continuous  
                 — 
                 1.5 
                 46 
                 140 
                 3043 
               
               
                 Example 8 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination  
                 Continuous  
                 — 
                 1.5 
                 42 
                 130 
                 3095 
               
               
                 Example 9 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Cloth lamination 
                 Continuous  
                 — 
                 1.5 
                 45 
                 140 
                 3111 
               
               
                 Example 10 
                   
                 fibers 
                   
                   
                   
                   
                   
               
               
                 Comparative 
                 Felt lamination 
                 About  
                 — 
                 1.6 
                 65 
                 98 
                 1508 
               
               
                 Example 11 
                   
                  50 mm 
                   
                   
                   
                   
                   
               
               
                   
               
            
           
         
       
     
       FIG. 20  shows the results obtained by measuring a relation of elastic modulus and breaking strength (tensile strength) on the physical analysis of the C/C composite material and is a graph of a relation of elastic modulus and tensile strength of the Examples and Comparative Examples.  FIG. 21  shows the results obtained by measuring a relation of elastic modulus and breaking strain and is a graph of a relation of elastic modulus and breaking strain of the Examples and Comparative Examples. It is noted from Table 2 and the graphs of  FIGS. 20 and 21  that according to the C/C composite material of Examples, not only the high breaking strength but the low elastic modulus can be easily kept. 
     Observation of Surface and Section 
     The surface and section of the molded body obtained in each of Example 1 and Comparative Example 1 were observed by various photographs. 
     (Preparation Method of Samples for Polarizing Microscopic and Scanning Electron Microscopic (SEM) Photographs) 
     The sample of the C/C composite material of each Example 1 and Comparative Example 1 was embedded in an epoxy resin, and a section was fabricated by means of a mechanical polishing method, followed by performing a flat milling treatment (at 45° for 3 minutes). A section having been subjected to Pt—Pd sputtering was observed by FE-SEM and a polarizing microscope. Here, the epoxy resin is one used for fixing a sample for cutting out a flat surface from a soft sample, an easily deformable sample, a fine sample or the like. For example, though an end surface of a powder, a section of a fiber or the like is in general hardly subjected to section processing, it becomes possible to achieve the observation by fixing with a fixing agent such as an epoxy resin in such a way. 
     (Analysis Apparatus and Measurement Condition) 
     [Flat Milling] 
     
         
         Apparatus: Hitachi, E-3200 
         Output: 5 kV, 0.5 mA 
       
    
     [FE-SEM] 
     
         
         Apparatus: JEOL, JSM-7001F 
         Accelerating voltage: 5 kV 
         Observation image: Secondary electron image 
       
    
     [Polarizing Microscope] 
     
         
         Apparatus: manufactured by Nikon 
       
    
       FIG. 7A  is a photograph of a section of the molded body of Example 1, and  FIG. 7B  is a photograph of a section of the molded body of Comparative Example 1. The vertical direction in the photograph is a thickness direction (laminating direction) of the molded body, and the horizontal direction in the photograph is a surface direction. In the molded body of Example 1, it is noted that a uniform molded body in which thin piece bodies oriented in a surface direction of the molded body are formed, and boundaries of the thin piece bodies are dispersed is formed. In the molded body of Comparative Example 1, it is noted that a layer structure of annual rings is formed. 
       FIG. 8A  is an enlarged photograph of the surface of the molded body of 
     Example 1 (inner surface of cylindrical molded body).  FIG. 8B  is a photograph of thin piece bodies observed on the surface of the molded body of  FIG. 8A .  FIG. 8C  is a photograph of thin piece bodies separated from the surface of the molded body of  FIG. 8A . A solid line region in  FIG. 8B  shows each of the thin piece bodies  3 .  FIG. 8C  shows a photograph of the thin piece bodies separated from the surface of the molded body of  FIG. 8A . Since the inner surface of the molded body is molded by using the support material  25 , a flat surface which is free from large irregularities is obtained. However, it can be confirmed that thin piece bodies oriented substantially in parallel to the surface direction as formed from flocks are exposed on the surface. Such thin piece bodies can be gradually peeled away from a site where an end thereof is exposed because the constituting carbon fibers are oriented substantially in parallel to the surface direction; however, the thin piece bodies are merely separated one by one, and it is considered that separation reaching the whole of the carbon fiber molded body does not occur. Such separation can also be similarly confirmed on the fracture surface formed by breaking the carbon fiber molded body in a layer direction thereof. 
       FIG. 9A  shows a scanning electron microscopic (SEM) photograph of a section of the molded body of Comparative Example 1, and  FIG. 9B  shows a schematic view of  FIG. 9A . The horizontal direction in the photograph is a thickness direction of the molded body (laminating direction of the sheet), and the vertical direction in he photograph is a surface direction. It can be confirmed that the fibers in a sheet interface part are strongly oriented in parallel along the boundary. 
       FIGS. 10A to 10C  are scanning electron microscopic (SEM) photograph of a section of the molded body of Example 1. The vertical direction in the photograph is a thickness direction of the molded body (laminating direction of the thin piece body), and the horizontal direction in the photograph is a surface direction.  FIG. 10A  is an SEM photograph of a section of the molded body of Example 1 with a magnification of 100;  FIG. 10B  is an SEM photograph of a section of the molded body of Example 1 with a magnification of 200; and  FIG. 10C  is an SEM photograph of a section of the molded body of Example 1 with a magnification of 500.  FIG. 10A  shows thin piece bodies observed in the SEM photograph of the section. A solid line region in  FIG. 10A  shows each of the thin piece bodies  3 .  FIG. 10B  is a more enlarged SEM photograph of the thin piece body portion of  FIG. 10A .  FIG. 10C  is a still more enlarged SEM photograph of the thin piece body portion of  FIG. 10B . As shown in  FIG. 10A , it can be confirmed that the thin piece bodies are laminated while being oriented substantially in parallel to the surface direction of the carbon fiber molded body. 
       FIGS. 11A to 11D  are scanning electron microscopic (SEM) photographs of a section of the molded body of Comparative Example 1, in which the vertical direction in the photograph is a thickness direction of the molded body (laminating direction of the thin piece body), and the horizontal direction in the photograph is a surface direction.  FIG. 11A  is an SEM photograph of a section of the molded body of Comparative Example 1 with a magnification of 100;  FIG. 11B  is an SEM photograph of a section of the molded body of Comparative Example 1 with a magnification of 200; and  FIG. 11C  is an SEM photograph of a section of the molded body of Comparative Example 1 with a magnification of 500.  FIG. 11B  is an enlarged SEM photograph of  FIG. 11A , and  FIG. 11C  is a more enlarged SEM photograph of  FIG. 11A . As is confirmed from  FIGS. 11B and 11C , a region where the carbon fibers are strongly oriented in parallel in the surface direction of the carbon fiber molded body is present, and it is confirmed that in this region, connection of fibers in the thickness direction is not substantially formed. For that reason, it is noted that in Comparative Example 1, the region where the fibers are strongly oriented relative to a tension in the vertical direction in each of the photographs of  FIGS. 11B and 11C  becomes a defect. 
       FIG. 23A  is a polarizing microscopic photograph of a section of the molded body of Example 1. The vertical direction in the photograph is a thickness direction of the molded body (laminating direction of the thin piece body), and the horizontal direction in the photograph is a surface direction. Also,  FIG. 23B  is a polarizing microscopic photograph of a section of the molded body of Comparative Example 1. The vertical direction in the photograph is a thickness direction of the molded body (laminating direction of the sheet), and the horizontal direction in the photograph is a surface direction. In a polarizing microscope, a different color is observed depending upon the orientation direction of a crystal, and hence, the fibers and the matrix can be easily distinguished from each other. The fibers are observed in a linear shape, an oval shape or a circular shape depending upon a relation with the observing surface. Also, a site which is deeply gray and is free light and shade in  FIGS. 23A and 23B  is an epoxy resin E used as a sealing resin, and other regions are the C/C composite material molded body  100  (thin piece body including the matrix and the carbon fibers) in  FIG. 23A  and a C/C composite material molded body C in  FIG. 23B , respectively. 
     In a region surrounded by a solid line in  FIG. 23A , a carbon fiber component  1   a  connecting the thin piece bodies adjoining in the vertical direction (laminating direction of the thin piece body) of the polarizing microscopic photograph to each other, can be confirmed. On the other hand, in  FIG. 23B , a carbon fiber component connecting the thin piece bodies to each other is not confirmed. 
     In the polarizing microscopic photograph as shown in  FIG. 23A , in order that carbon fibers connecting thin piece bodies to each other may be observed, not only the carbon fibers must be present on the observing surface, but the longitudinal direction of the carbon fibers must be contained in the observed surface. In  FIG. 23A , a carbon fiber component connecting the thin piece bodies adjoining in the vertical direction (laminating direction of the thin piece body) in the photograph to each other could be confirmed, and therefore, it may be considered that many other carbon fiber components connecting the thin piece bodies adjoining in the vertical direction (laminating direction of the thin piece body) to each other, which cannot be observed, are also present. 
     As shown in the measurement results of Table 1, in the molded body obtained in the present Example 1, the three-point bending strength of the molded body was 75.7 MPa in the vertical direction and 69.0 MPa in the parallel direction to the surface direction of the molded body, respectively, so that a substantially equal three-point bending strength was obtained in any of the vertical direction and the parallel direction to the surface direction of the molded body. This is because it may be considered that in the molded body of the invention, the thin piece bodies are constituted upon being laminated, and furthermore, a homogenous molded body is obtained due to the presence of a carbon fiber component connecting the thin piece bodies adjoining in the thickness direction (laminating direction of the thin piece body) to each other. 
     In the molded body obtained in the present Comparative Example 1, the three-point bending strength is 19.6 MPa in the vertical direction (laminating direction of the thin piece body) to the surface direction of the molded body, a value of which is considerably low as compared with 47.2 MPa in the parallel direction to the surface direction of the molded body (three-point bending strength in a P direction). 
     In the molded body obtained in the present Comparative Example 1, the strength in the vertical direction to the surface direction of the molded body is significantly lower than that in the parallel direction to the surface direction of the molded body. In the three-point bending test in the vertical direction to the surface direction of the molded body, the molded body was broken in such a manner that the laminated sheet was separated. 
     In the present Comparative Example 1, the molded body is configured through lamination of the sheets, and a carbon fiber component connecting the sheets to each other upon being oriented in the thickness direction is not present. Thus, a joining force between the sheets was weak, and in the three-point bending test in the vertical direction to the surface direction of the molded body, a remarkable lowering of the strength was found. Also, even in the three-point bending test in the parallel direction to the surface direction of the molded body, separation of the sheet was found, and only low strength was obtained as compared with that in Example 1. 
     It may be predicted that the same results are also obtainable in Example 2 and Comparative Examples 2 to 11. 
     Also, in the polarizing microscopic photograph of Example 1 shown in  FIG. 23A , it is noted that the carbon fiber component is present in a bare-fiber state. That is, the carbon fiber component connecting the thin piece bodies adjoining in the laminating direction of the thin piece body to each other, which is expressed by “ 1   a ”, and the carbon fiber component oriented in the horizontal direction in the photograph, namely the surface direction of the molded body, which is expressed by “ 1   b ”, do not form a strand. On the other hand, as shown in a region surrounded by a solid line in the polarizing microscopic photograph of Comparative Example 1 as shown in  FIG. 23B , it is noted that the carbon fibers form a strand. It may be conjectured that the substantially same results are also obtainable in Example 2 and Comparative Examples 2 to 11. 
     Since the C/C composite material molded body according to an embodiment of the present invention has high strength, high chemical stability and high heat resistance, it is useful for silicon single crystal pull-up apparatuses, compound semiconductor crystal pull-up apparatuses, manufacturing apparatuses of silicon for solar cell (for example, silicon thin film forming apparatuses, manufacturing apparatuses of silicon ingot, etc.), members to be used at a high temperature, such as apparatus parts in the atomic energy, nuclear fusion or metallurgy field or the like, fields required to keep high strength against a temperature change, such as space parts and aerospace parts, and so on.