Fiber reinforced high temperature thermal barrier composite ceramic thick coating material as well as preparation and application thereof
Technical Field The invention relates to a heat insulation function works with the surface of the coating material and its application, in particular to a kind of the fiber winding with high-temperature heat barrier and ablation composite thick coating material and its application. Background Art The current commonly used thermal barrier is a heat-insulation technology, thermal barrier coating is used to prevent the high thermal resistance of the material to the heat transfer as a heat insulation of the main mechanism. Zirconia because of the high melting point, very low thermal conductivity, good thermal stability, smaller high temperature creep, is an ideal high-temperature thermal barrier material. However, pure ZrO2 material generally not be directly used as the thermal barrier coating, this is because the conversion of the crystal will produce pitting phenomenon. ZrO2 there are three kinds of crystalline form: monoclinic, tetragonal, cubic, low-temperature to the monoclinic phase m-ZrO2; when the heating to about 1200 the [...] , transformed into the tetragonal phase t-ZrO2, accompanied by 7%-9% volume shrinkage of the; exceed the 2370 [...] , into the cubic phase c-ZrO2. When cooling to the 1000 when [...] , into a monoclinic structure and the volume expansion, the volume of the phase change caused by the contraction and expansion is not continuous with the temperature change, thus a coating is not stable, due to internal thermal stress and volume stress, caused by premature cracking or exfoliation of coating failure. In ZrO2 yttrium oxide is mixed (Y2 O3) as a stabilizer, can make the ZrO2 under the high temperature (YSZ) or partially stabilized to obtain the stabilization of the crystal structure of the (PYSZ). They commonly use stable is that some ZrO2/Y2 O3, it is composed of a monoclinic phase and the tetragonal phase mixing. Under the crystal structure at high temperature, the volume shrinkage phase monoclinic phase occurred, squar-phase with the increase of temperature and the volume expansion phase change, expansion and contraction to offset each other, so that the partially stabilized ZrO2/Y2 O3 crystal structure than a completely stable ZrO2/Y2 O3 crystal structure with a lower thermal expansion coefficient are, the more close to the coefficient of thermal expansion of the metal, therefore, and has more excellent thermal shock resistance, the highest temperature is PYSZ used at present a thermal barrier coating material. If the ZrO2/Y2 O3 crystal structure by adding a small amount of cerium oxide, can further improve the performance of this kind of coating. The research shows that: when the ceramic material grain control in less than 100 nm at the time, because the quantum effect will be caused by the sudden change of material properties, material strength and fracture toughness significantly improved, at the same time, a large number of experiments shows that nanometer ZrO2/Y2 O3 the porosity of the coating will also descend, high density of the coating will improve the ability of the coating and the substrate. Importantly, the thermal conductivity of the material will decrease and reducing of the crystal grain, coating of nano-zirconia and this is the fundamental reason for good heat insulation performance. A large number of research shows that, in a thermal barrier coating in the process of spraying preparation, the surface of the ceramic coating and inside adsorbs many microcracks. These microcracks tip to produce the stress concentration, and ceramic and lack of plastic deformation, the process of almost no energy absorption. In the course of preparing the coating including residual stress, thermal cycling stress, phase change stress, the stress caused by oxide, the role of various stress, energy is concentrated in the rapid expansion of the cracks. For performance, when cooling after the end of the spraying, coating will often brittle fracture in an instant, thereby constraining can be prepared of the thickness of the ceramic coating. In order to improve the thermal barrier ceramic coating the thickness of which can be prepared, from two aspects: the control coating a large number of microcracks expansion and reduce the effect of internal stress of the coating. Out of the above considerations, the fiber preparation of enhancement is applied to the ceramic coating, and not used compared with fiber-reinforced ceramic coating, has the advantages of this kind of coating: (1) when the crack encounters the fiber, the fiber can be a part of and absorb the energy, eliminating cracktip the concentrated stress, to continue to prevent it from extending, crack will be manifested to suspend or changes the propagation direction; (2) with high elastic modulus of the carbon fiber can share most of the stress, or fiber breakage of fiber pulled out to stop the destruction of the coating, the strength of the whole enhancing coating. In order to make the fiber not only can meet the transmission of stress, to play the enhancement effect, in the breaking and can be pulled out from the coating process, and a certain amount of energy consumption, buffer the entire fracture process, increase the rupture work, it is necessary to ensure the appropriate interface shear strength. In the experiment, to adhesive impregnated carbon fiber, the ceramic coating can be after winding has a suitable interface shear strength. plane net layer of carbon fiber in the covalently bonded atoms C, compared with the ordinary graphite, its orientation angle is relatively small, so the fiber along the fiber length direction and a relatively high strength and elastic modulus. Is about carbon melting point the 3652 [...] -3697 the (sublimation) [...] , in 2000 the above [...] under the high temperature of the strength and the elastic modulus of the carbon fiber can remain essentially unchanged, the sharp temperature rise can bear the coating without vaporization. Under the high temperature, the carbon fiber is very low thermal conductivity, high-temperature heat insulating performance is good, it is a kind of very good high-temperature heat-insulating material. When the fiber is embedded in ceramic coating, because the linear expansion coefficient similar to the ceramic fiber, the two can effectively in the change in the temperature environment better combination, "reinforced concrete" structure is formed, between the coating and the coating layer of the coating and the substrate and the bond strength between the. Furthermore, carbon fiber has good chemical corrosion resistance, radiation resistance and the capacity of the neutron rays. Glass fiber melting point is 1710 the [...] , silicon carbide fiber of higher melting point, is the 2500 [...] , and two kinds of fiber are has a relatively low coefficient of linear expansion, has very high strength. Therefore both of the sharp increase of the ambient temperature in the process is not easy to break, the coating can always get very good with the damascene role bound, can be very good "reinforced concrete" structure is formed, is reinforced by the ceramic coating. Content of the invention The invention the technical problem to be solved is to: provide a work substrate can be extended to reach the upper temperature limit time of high-temperature thermal barrier of the fiber-reinforced composite thick coating material, the material can be coated on various in the atmosphere of high-speed movement of the aircraft surface, high temperature thermal barrier and ablation play the role of the composite protective layer. To solve the technical problems of the present invention adopts the following technical scheme: The present invention provides fiber-reinforced high temperature thermal barrier composite ceramic thick coating material, the material has a multi-layer structure, in particular to: the spraying adhesive layer surface of the work piece of a metallic matrix, a is the role of "concrete" and is located between the spray of the sprayed layer has the role of "reinforced" enhancement layer. Sprayed coating are plasma spraying process by spraying powdered composite coating material to form a laminated structure, at least a coating layer 3 layer. High-temperature fibrous reinforcement layer is used to carry out parallel or are wound on the spray coating layer is one to two, the, temperature of the use of high-temperature cellosilk the ≥ 700 [...]. The powdered composite coating material, in the previously in the prior application of "a high-temperature heat barrier and ablation composite coating material and its application" (relates to number CN1884405) high temperature thermal barrier referred to in the double-effect heat and ablation of the composite coating material, it is mainly composed of graininess is 10-100nm of partially stabilized ZrO2/Y2 O3 powder, agglomerated and the ablation material, wherein: the partially stabilized ZrO2/Y2 O3 powder and ablation of the auxiliary weight percent is: the partially stabilized ZrO2/Y2 O3 powder 55-85, ablation accessories 15-45. The high temperature thermal barrier of the fiber-reinforced composite ceramic thick coating material, the material is preferably provided with four layers of coating, from the inside to the outside, their the thickness of 0.2 mm, 0.3 mm, 0.4 mm, 0 . 45 mm. The high temperature fiber is a glass fiber, carbon fiber or a silicon carbide fiber filament. The present invention provides the above high-temperature thermal barrier of the fiber-reinforced composite ceramic thick coating material, the preparation method is:a main by the granularity for 10-100nm of partially stabilized ZrO2/Y2 O3 powder, agglomerated and ablation auxiliary high-temperature thermal barrier of the double-effect heat and ablation of the composite coating material, and the temperature used for ≥ 700 [...] to the high temperature fiber is reinforced by the composite coating material, in the enhanced process, the roughening the metal matrix of the bottom layer of the adhesive surface of the workpiece with the plasma spraying process for preparing a layer of laminated structure composite coating, and then high-temperature fiber wire is wound one to two, wherein a composite coating material role "concrete", "reinforced" high-temperature fibrous role the silk gets up ; repeating the spraying and the winding process, in the last 1 is wound and then the mixture is sprayed after 1 time, from a fiber reinforced with "reinforced concrete" structural high-temperature thermal barrier composite ceramic thick coating material. The present invention provides fiber-reinforced high temperature thermal barrier composite ceramic thick coating material preparation method comprises the following steps: (1) preparation of the substrate: the compressed air is of high-speed jet of the hard abrasive surface of the work piece metal substrate, the roughening; in the roughening treated surface of the work piece of metal base coated with a layer thickness 0.8-1.2 the nickel-clad aluminum (Ni/Al) m or NiCoCrAlY self-adhesive bottom layer, to obtain substrate; (2) spraying: the surface of the basal spraying -180-+ 325 purpose coating powder, "concrete" form a layered structure of the coating, spray coating thickness is 0.2-0.5 mm, (3) winding: of the spray on the base after winding a layer of high-temperature fiber filament, two adjacent in each layer parallel fibers wire spacing is 0.8-1.0 mm, parallel or staggered winding, form a reinforcing layer "reinforced" role; Repeating the above-mentioned spraying and the winding process, in the last 1 is wound and then the mixture is sprayed after 1 time, to obtain the high temperature thermal barrier composite ceramic thick coating material. In the winding process, on the surface of the coating layer can be in parallel with each other and winding shan Shusi two synnema cross-winding two way, wherein parallel with each other when winding shan Shusi , of two adjacent layers of fiber winding is between 60 to 90 degrees. The present invention provides fiber-reinforced high temperature thermal barrier composite ceramic thick coating material, the coating by plasma spray techniques in the atmosphere in the aircraft surface of high-speed movement of the, high-temperature thermal barrier and ablation play the role of the composite protective layer. The plasma coating process is a conventional process, the main means of atmospheric plasma spraying (APS). The aircraft, such as under a high Mach number flight rocket, missile, such as the fin of a supersonic aircraft, there are strict thickness and surface profile control of the empennage, such as thermal protection to the surface of component powders. Compared with the prior art, the present invention has the following main advantages: 1. The coating through the fiber wire is wound a plurality of times, make the coating overall form of the structure of "reinforced concrete", the thickness of the ceramic coating can be improved, the coating so as to have better heat insulation effect. 2. The nanometer grain size of zirconia powder raw material, the heat conductivity of the thermal barrier coating in addition to the decrease and reducing the crystal grain. 3. Prepare agglomerate type nano-zirconia can further enhance the thermal barrier effect of the coating. Agglomerate type of nano-zirconia and the whole process of preparing the physical agglomeration processing method, not only keeps the heat barrier in each agglomerate particles with the ablated coating component not segregate the statistical average, at the same time control the growth of the nano grains. 4. Less of the entire preparation process, the apparatus is simple, the process parameters is easy to control, is suitable for continuous mass production. 5. According to the specific requirements of the working conditions of to, appropriate adjust the fiber ingredient, the number of winding manner and winding, a preparation that is suitable for the operating conditions of satisfactory products. In the heat-insulating material of the present invention add ablation supplementary product, in the subsequent heating process by ablating the material of the temperature in the different combustion carbomorphism, melting and sublimation heat-absorbing first take a part of heat, the partially stabilized ZrO2/Y2 O3 powder in the ablative coating material component after depletion, can still play the role of thermal barrier coating; the fiber wound, reinforced manner high temperature thermal barrier coating can be increased with the ablation two kinds of heat-insulating and heat-resistant composite function, the substrate can be greatly prolonged (i.e. the workpiece) time of reaching the working temperature of the ceiling. The invention selects the graininess is 10-100nm of partially stabilized ZrO2/Y2 O3 powder raw material, the heat conductivity of the thermal barrier coating in addition to the decrease and reducing the crystal grain, the nanometer or nano-micron particle size after the ablation of the ablation material of the micro-pore, the coating to provide better heat insulation effect. The invention is particularly suitable for disposable heat insulation. Mode of execution With the embodiment of the invention provides the method for the preparation of further note, but not limited to the following embodiment. Embodiment 1: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)10 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spraying a coating material; (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. In the roughening processing workpiece surface is also coated with a layer thickness 0.8-1.2 the adhesive layer of the aluminum-clad nickel (Ni/Al) m. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. The glass fiber yarn is wound on the surface of the coating layer, two adjacent parallel fibers wire spacing is 0.8-1.0 mm, a parallel-winding; (4) the work piece after the winding again repeat step (3), a total of 3 fiber is wound, plasma spraying 4 layer coating, the thickness of each layer from the inside outward are respectively 0.2 mm, 0.3 mm, 0.4 mm, 0 . 45 mm, the total thickness of coatings are up to 1.35 mm; (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal the crystal structure of the powder diffraction measurements, on the stainless steel substrate preparing the powder coating, in order to compare, is of the same conditions without fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 1. Embodiment 2: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)6.5 kg and silicon oxide 1.5 kg, ≤ 30 the grain size of the copper powder m 0.5 kg and particle size of 10-30 the phenolic resin m 1.5 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the adhesive layer of the aluminum-clad nickel (Ni/Al) m. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. The carbon fiber thread is wound on the surface of the coating layer, two adjacent parallel fibers wire pitch of 0.4-0.6 mm, parallel winding. (4) the work piece after the winding again repeat step (3), a total of 4 fiber is wound, the coating is divided into 5 layer, the thickness of each layer from the inside outward are respectively 0.3 mm, 0.3 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, the total thickness of coatings are up to 1.9 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 2. Embodiment 3: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)6.5 kg and silicon nitride 1.5 kg, ≤ 30 the grain size of the copper powder m 0.5 kg and particle size of 10-30 the modified organic silicon resin m 1.5 kg, spray-drying of the agglomerated spherical powder is made. Heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the NiCoCrAlY μm of the adhesive layer. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. The carbon fiber thread is wound on the surface of the coating layer, two adjacent parallel fibers wire interval is 0.3-0.5 mm, parallel winding. (4) the work piece after the winding again repeat step (3), a total of 5 fiber is wound, the coating is divided into 6 layer, the thickness of each layer from the inside outward are respectively 0.2 mm, 0.3 mm, 0.4 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, the total thickness of coatings are up to 2.2 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 3. Embodiment 4: (1) to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)5.5 kg and silicon nitride 1.5 kg, ≤ 30 the grain size of the copper powder m 2.0 kg and particle size of 10-30 the modified organic silicon resin m 1.0 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the NiCoCrAlY m of the adhesive layer. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. The carbon fiber thread is wound on the surface of the coating layer, two adjacent parallel fibers wire distance is 1.3-1.5 mm, mesh winding. (4) the work piece after the winding again repeat step (3), a total of 5 fiber is wound, the coating is divided into 6 layer, the thickness of each layer are respectively from the inside to outside 0.25 mm, 0.3 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, 0 . 45 mm, the total thickness of coatings are up to 2.3 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 4. Embodiment 5: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)8.0 kg and silicon oxide 1.0 kg, graininess is 10-30 the polyester m 1.0 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the adhesive layer of the aluminum-clad nickel (Ni/Al) m. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. The carbon fiber thread is wound on the surface of the coating layer, two adjacent parallel fibers wire pitch of 1.1-1.3 mm, mesh winding. (4) the work piece after the winding again repeat step (3), a total of 6 fiber is wound, the coating is divided into 7 layer, the thickness of each layer are respectively from the inside to outside 0.25 mm, 0.3 mm, 0 . 35 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, 0 . 45 mm, than the total thickness of coatings 2.65 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 5. Embodiment 6: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)5.5 kg and silicon oxide 1.5 kg, graininess is 10-30 the high-carbon iron powder m 2.0 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the adhesive layer of the aluminum-clad nickel (Ni/Al) m. The plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. In the lamellar coating silicon carbide fiber is wound on the surface of the wire, two adjacent parallel fibers wire pitch of 0.9-1.1 mm, mesh winding. (4) the work piece after the winding again repeat step (3), a total of 7 fiber is wound, the coating is divided into 8 layer, the thickness of each layer are respectively from the inside to outside 0.25 mm, 0.3 mm, 0 . 35 mm, 0.4 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, 0 . 45 mm, the total thickness of coatings are up to 3.05 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 6. Embodiment 7: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)8.0 kg, ≤ 30 the grain size of the copper powder m 2.0 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the adhesive layer of the aluminum-clad nickel (Ni/Al) m. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. In the lamellar coating silicon carbide fiber is wound on the surface of the wire, two adjacent parallel fibers wire pitch of 1.1-1.3 mm, mesh winding. (4) the work piece after the winding again repeat step (3), a total of 5 fiber is wound, the former 3 the mesh winding, two adjacent parallel fibers wire pitch of 0.9-1.1 mm, the rear 2 the parallel winding, two adjacent parallel fibers wire interval is 0.3-0.5 mm, the coating is divided into 6 layer, respectively from the inside to outside is 0.25 mm, 0.3 mm, 0.4 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, the total thickness of coatings are up to 2.25 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 7. Embodiment 8: (1) in order to fetch the granularity 10-100nm part of the stabilized ZrO2/Y2 O3 powder (PYSZ powder, Y2 O3 content is 5-7wt %)9.0 kg, graininess is 10-30 the polyester m 1.0 kg, is made of agglomerated spherical powder by spray drying, heating -180-+ 325 mesh powder between, its particle size range for the 40-90 m, as plasma spray coating material. (2) by compressed air (brown fused alumina) the hard abrasive surface of the work piece of high-speed jet, so that the roughening. The surface of the treated workpiece coated with a layer thickness 0.8-1.2 the adhesive layer of the aluminum-clad nickel (Ni/Al) m. Plasma spraying process the main technical parameters are: power 35-40KW, voltage 70-80V, current 450-500A. (3) the surface of the adhesive layer by plasma spraying the powder coating material preparing layered coating layer, the thickness of the coating is more than 0.2-0.5 mm, the power is used for spraying the 40-45KW, voltage 75-85V, current 500-550A. In the lamellar coating silicon carbide fiber is wound on the surface of the wire, two adjacent parallel fibers wire distance is 0.6-1.0 mm, parallel winding. (4) the work piece after the winding again repeat step (3), a total of 5 fiber is wound, the former 3 the mesh winding, two adjacent parallel fibers wire pitch of 0.9-1.1 mm, the rear 2 the parallel winding, two adjacent parallel fibers wire interval is 0.3-0.5 mm, the coating is divided into 6 layer, respectively from the inside to outside is 0.25 mm, 0.3 mm, 0.4 mm, 0.4 mm, 0 . 45 mm, 0 . 45 mm, the total thickness of coatings are up to 2.25 mm. (5) a scanning electron microscope for measuring the topography of the powder and coating, X-ray powder crystal powder diffraction measurement of the crystal structure, the stainless steel substrate thick coating to prepare this kind, for the sake of comparison, the same conditions without the use of fiber reinforced nano yttrium oxide stabilized zirconium oxide powder coating for contrast, measuring coating thickness by a micrometer, through the plasma flame simulation condition test by ablation, through the laser thermometer measuring the temperature, the time required for recording a stopwatch. Results are presented in table 7. The fiber of the invention wire winding pitch and the lower limit value of the interval of the present invention can be realized, cellosilk specific raw materials, cellosilk various winding mode of the present invention can be realized, in this embodiment it is not an enumeration. Schedule Table 1 the fiber-reinforced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating Table 2 through fiber-reinforced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating Table 3 the fiber enhanced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating Table 4 the fiber enhanced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating Table 5 the fiber enhanced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating Table 6 through the fiber enhanced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating Table 7 the fiber enhanced nano-zirconia composite thermal barrier coatings compared with ordinary nanometer zirconia coating The invention relates to a fiber reinforced high temperature thermal barrier composite ceramic thick coating material. The fiber reinforced high temperature thermal barrier composite ceramic thick coating material has the following structure: spray coating layers having the 'concrete' action and reinforced layers which are arranged between the spray coating layers and have the 'steel bar' action are arranged in turn on the surface of a metallic matrix workpiece of a spray coating and cementing bottom layer; the spray coating layers at least have 3 layers and are prepared from a powdery composite coating material with double effects of high temperature thermal barrier and ablative heat protection by a plasma spraying process; and the reinforced layers are formed by high temperature fibers which wrap the spray coating layers in a paralleled or staggered mode for one or two times, and the use temperature of high temperature fibers is more than or equal to 700 DEG C. The material is prepared by the following steps: preparation of a matrix, spray coating, wrapping and the like. The material can be coated on the surfaces of various aircrafts moving at a high speed in the atmospheric layer through the plasma spraying process so as to have the actions of the high temperature thermal barrier and the ablative composite protective layer. The material can improve the upper limit of the working temperature of a metallic matrix in a high temperature environment and simultaneously prolong the service time of the metallic matrix in a high temperature extreme environment. The material has high practicability and is suitable for the industrialized production. 1. A high-temperature thermal barrier composite ceramic thick coating material, comprising a mainly by the granularity for 10-100nm of partially stabilized ZrO2/Y2 O3 powder, agglomerated and ablation auxiliary high-temperature thermal barrier of the double-effect heat and ablation of the composite coating material, is characterized in that a high-temperature thermal barrier kind of fiber-reinforced composite ceramic thick coating material, the material has a multi-layer structure, in particular to: the spraying adhesive layer surface of the work piece of a metallic matrix, a is the role of "concrete" and is located between the spray coating layer is a sprayed layer of a reinforcing layer of "reinforced" role; sprayed coating are plasma spraying process by spraying the above-mentioned composite coating powder to form a laminated structure, at least a coating layer 3 layer; high-temperature fibrous reinforcement layer is used to carry out parallel or are wound on the spray coating layer is one to two, the, temperature of the use of high-temperature cellosilk the ≥ 700 [...]. 2. High temperature thermal barrier composite ceramic thick coating material according to Claim 1, characterized in that the material has a four-layer coating, from the inside to the outside, their the thickness of 0.2 mm, 0.3 mm, 0.4 mm, 0 . 45 mm. 3. High temperature thermal barrier composite ceramic thick coating material according to Claim 1, which is characterized in that high-temperature fibers to glass fiber, carbon fiber or a silicon carbide fiber filament. 4. A high-temperature thermal barrier composite ceramic thick coating material preparation method, a is mainly composed of a particle size of 10-100 nm of partially stabilized ZrO2/Y2 O3 powder, agglomerated and ablation auxiliary high-temperature thermal barrier of the double-effect heat and ablation of the composite coating material, which is characterized in that the temperature used for ≥ 700 [...] to the high temperature fiber is reinforced by the composite coating material, in the enhanced process, the roughening the metal matrix of the bottom layer of the adhesive surface of the workpiece with the plasma spraying process for preparing a layer of laminated structure composite coating, and then high-temperature fiber wire is wound one to two, wherein a composite coating material role "concrete", "reinforced" high-temperature fibrous role the silk gets up ; repeating the spraying and the winding process, in the last 1 time and then the mixture is sprayed after winding 1 layer coating, the structure of the "reinforced concrete" high temperature thermal barrier composite ceramic thick coating material, the material is a fiber reinforced high temperature thermal barrier composite ceramic thick coating material. 5. Preparation method according to Claim 4, which is characterized in that the method comprising the steps of: (1) preparation of the substrate: the compressed air is of high-speed jet of the hard abrasive surface of the work piece metal substrate, the roughening; in the roughening treated surface of the work piece of metal base spraying thick 0.8-1.2 the nickel-clad aluminum (Ni/Al) m or NiCoCrAlY self-adhesive bottom layer, to obtain substrate; (2) spraying: the surface of the substrate by plasma spraying -180-+ 325 the compound coating powder, "concrete" form a layered structure of the coating, spray coating thickness is 0.2-0.5 mm, (3) winding: of the spray on the base after winding a layer of high-temperature fiber filament, two adjacent in each layer parallel fibers wire spacing is 0.8-1.0 mm, parallel or staggered winding, form a reinforcing layer "reinforced" role; Repeating the above-mentioned spraying and the winding process, in the last 1 is wound and then the mixture is sprayed after 1 time, to obtain the high temperature thermal barrier composite ceramic thick coating material. 6. Preparation method according to Claim 5, characterized in that high temperature thermal barrier composite ceramic thick coating material has a four-layer coating, from the inside to the outside, this four layer the thickness of the coating layer are respectively 0.2 mm, 0.3 mm, 0.4 mm, 0 . 45 mm. 7. Preparation method according to Claim 5, characterized in that the high temperature fiber is a glass fiber, carbon fiber or a silicon carbide fiber filament. 8. High temperature thermal barrier composite ceramic thick coating material preparation method according to Claim 5, characterized in that in parallel with each other on the surface of the coating layer of mesh and shan Shusi two synnema cross-winding two way, wherein parallel with each other when winding shan Shusi , of two adjacent layers of fiber winding is between 60 to 90 degrees. 9. To 8 the right of any one of the preparation method according to Claim 4, is characterized in that the high-temperature thermal barrier made of composite ceramic thick coating material, the coating by plasma spray techniques in the atmosphere in the aircraft surface of high-speed movement of the, high-temperature thermal barrier and ablation play the role of the composite protective layer. Ordinary nanozirconia example 1 composite coating 0.4 1 . 35 1640 1640 23 48 Ordinary nanozirconia example 1 composite coating 0.4 1.9 1640 1640 23 65 Ordinary nanozirconia example 1 composite coating 0.4 2.2 1640 1640 23 73 Ordinary nanozirconia example 1 composite coating 0.4 2.3 1640 1640 23 78 Ordinary nanozirconia example 1 composite coating 0.4 2 . 65 1640 1640 23 88 Ordinary nanozirconia example 1 composite coating 0.4 3 . 05 1640 1640 23 101 Ordinary nanozirconia example 1 composite coating 0.4 2 . 25 1640 1640 23 74