32results about How to "Improve thermal compatibility" patented technology

The invention relates to a high-temperature-resistant high-strength aluminum oxide fiber enhanced composite material and a preparation method thereof. The preparation method comprises the following steps of: by taking a two-dimensional cloth paving layer and 2.5D woven or orthogonally three-dimensional woven continuous aluminum oxide fiber preform as an enhancer, preparing a matrix through a double nano composite impregnation liquid where silicon dioxide and aluminum oxide are uniformly mixed; and finally obtaining the aluminum oxide fiber enhanced composite material through the process of vacuum pressure impregnation, micro-positive pressure medium and low temperature pre-curing, micro-positive pressure curing and atmosphere temperature programming sub-sectional thermal treatment, wherein the mass ratio of silicon dioxide to aluminum oxide in the composite material is (19:1)-(12:8), and the volume content of the aluminum oxide fibers is 30-60%. The prepared composite material has a high-temperature-resistant property and a high-temperature mechanical property, and is high in compactness; the room temperature tensile strength of the material reaches 310+/-30MPa, the tensile strength at 1100 DEG C reaches 135+/-20MPa, and the tensile strength at 1200 DEG C reaches 90+/-10MPa; and compared with a similar quartz fiber enhanced silicon dioxide oxide/oxide composite material, the performance is improved by 4-5 times.

The invention discloses a novel ultrahigh-temperature ceramic (Zr0.8Ti0.2C0.74B0.26) integrally-modified anti-ablation carbon/carbon composite material and a preparation method thereof. The preparation method comprises the following steps: (1) performing high-temperature thermal treatment on a carbon fiber preform, and depositing pyrolytic carbon in a chemical gas phase permeation furnace to prepare a porous carbon/carbon composite material; (2) placing the carbon/carbon composite material on which the pyrolytic carbon is deposited on zirconium-titanium mixed powder, and preparing a zirconium-titanium carbide modified carbon/carbon composite material in a non-stoichiometric ratio through a high-temperature infiltration reaction method; (3) placing the composite material in mixed powder of C, B4C, SiC, Si and a penetration enhancer, and forming an integral ultrahigh-temperature ceramic modified carbon/carbon composite material by adopting an embedding method. The method is simple, is convenient to operate, can be used for preparing large-sized components, and is suitable for integrally modifying substrates and coatings of anti-ablation carbon/carbon composite materials in heat-resistant components of hypersonic aircrafts.

The invention relates to a method for preparing a ceramic protection layer on a C/SiC composite material, and the ceramic protection layer prepared therethrough. The method comprises the following steps: preparing a ZrC-SiC transition layer on the surface of the C/SiC composite material through an impregnation-solidification-high temperature cracking process by using an impregnation solution beinga zirconium-silicon integrated ceramic precursor solution containing zirconium and silicon according to a weight ratio of (1-8):1; preparing a ZrC anti-oxidation coating layer on the basis of the ZrC-SiC transition layer through a brush coating process; and depositing a SiC hole sealing layer on the surface of the obtained ZrC antioxidant coating through a chemical vapor deposition technology toprepare the ceramic protection layer on the C/SiC composite material. The prepared ceramic protection layer has excellent oxidation resistance at a temperature of 2000 DEG C or above, has high bindingforce with a substrate, and has wide application prospects in structural parts such as a wing rudder, a leading edge, an end and an engine of a novel hypersonic aircraft.

The invention discloses a graphene film frequency selective surface comprising a substrate and a graphene film layer disposed on the substrate. The substrate is prepared from fiber reinforced polymer composite material. The graphene film layer comprises a graphene film with periodically-arranged holes or graphene film chips arranged periodically. The graphene film frequency selective surface is simple in technique implementation, well matches the fiber reinforced resins composite material substrate, is low in weight increment, resistant to corrosion, and can be widely applied to devices such as composite material radomes or filters.

The invention discloses a thermal protection device which comprises an upper panel, a bottom panel, an upper corrugated plate layer and a lower corrugated plate layer, wherein the upper corrugated plate layer comprises a plurality of upper corrugated plates which are arranged in sequence; the lower corrugated plate layer comprises a plurality of lower corrugated plates which are arranged in sequence; the upper corrugated plate layer is arranged above the lower corrugated plate layer; the upper and lower corrugated plate layers are arranged in a staggered manner; the lower ends of the at the upper part corrugated plates and the upper ends of the lower corrugated plates are connected with one another through a heat insulation and bearing bolt connection structure; the heat insulation and bearing bolt connection structure comprises joint bolts, upper heat insulation gaskets, middle heat insulation spacers, lower heat insulation gaskets, and connecting nuts; the gap between the upper panel and the lower ends of the upper corrugated plates is filled with a high-temperature resistant insulating material; the gap between the bottom panel and the upper ends of the lower corrugated plates is filled with a middle-temperature resistant insulating material. Due to the adoption of the thermal protection device provided by the invention, the problems of thermal short-circuiting of the connection structure and thermal mismatch of a cold-hot structure of the thermal protection device can be solved.

The invention relates to the technical field of high-temperature infrared stealth materials and particularly discloses a fiber-reinforced ceramic matrix composite surface antioxidant/infrared stealthcoating capable of resisting the temperature of 1650 DEG C. The infrared stealth coating is of a layered structure and comprises a ceramic inner layer, a ceramic middle layer, a ceramic outer layer and a low-infrared-emissivity functional layer from bottom to top, wherein the ceramic inner layer is a mullite layer, the ceramic middle layer is a rare earth silicate layer, the ceramic outer layer isan 8YSZ layer, and the low-infrared-emissivity functional layer is a coating with Pt as a conductive phase and Bi2O3 as a binding phase. The invention further provides a preparation method of the fiber-reinforced ceramic matrix composite surface antioxidant/infrared stealth coating capable of resisting the temperature of 1650 DEG C. According to the infrared stealth coating, the oxidation resistance and the high-temperature stability of the composite material are improved, the infrared radiation intensity of a base material can be remarkably reduced, and the infrared stealth coating has excellent oxidation resistance and an infrared stealth function.

The invention discloses high-strength vibration-reduction epoxy mortar with a nano improver. The high-strength vibration-reduction epoxy mortar consists of three components A, B and C, wherein the component A is a substrate mixture; the component B is an auxiliary mixture; the component C is a curing mixture; the component A consists of the following various raw materials in parts by weight: 80-100 parts of modified epoxy resin, 45-70 parts of cement and 100-300 parts of quartz sand; the component B consists of the following various raw materials in parts by weight: 10-50 parts of a nano improver, 3-5 parts of a silane coupling, 0-1 part of a defoaming agent and 10-15 parts of a diluent; the component C consists of the following various raw materials in parts by weight: 40-55 parts of a curing agent and 1-5 parts of a toughening agent; the weight ratio of the component A, the component B to the component C is (80-100):(5-100):(50-600). The high-strength vibration-reduction epoxy mortar disclosed by the invention has the advantages of being high in strength, good in vibration reduction effect, good in binding force with a concrete substrate, good in compatibility and the like, and can be used as a secondary grouting material of complex industrial vibration equipment.

The invention relates to an antioxidant coating for a C/ZrC-SiC composite material, and a preparation method thereof. The antioxidant coating comprises an HfC-HfB2 coating and a SiC coating which arealternately formed on the C/ZrC-SiC composite material. The preparation method comprises the following steps: the surface of the C/ZrC-SiC composite material is coated with a ceramic slurry containingHf powder, B powder, ethyl alcohol and phenolic resin, the HfC-HfB2 coating is formed after cracking, and then the SiC coating is deposited; and the above step is repeated (N-2)/2 times so as to formthe antioxidant coating on the surface of the C/ZrC-SiC composite material. The method has the advantages of simple process, low preparation cost, solving of the problems of uniform distribution of HfC-HfB2 and SiC and combination with a matrix, remarkable improvement of the ablation resistance and oxidation resistance of the C/ZrC-SiC composite material, and further improvement of the use temperature of the C/ZrC-SiC composite material.

The invention relates to a carbon fiber reinforced carbon-tantalum hafnium carbide solid solution composite material and a preparation method thereof. The preparation method comprises the following steps: preparing a pyrolytic carbon interface layer on a carbon fiber preform by utilizing a chemical vapor infiltration technology, preparing a C matrix by using a pyrolysis technology or a precursor infiltration and pyrolysis technology, then preparing a C-TaxHfC transition matrix from a tantalum hafnium carbide ceramic by using the precursor infiltration and pyrolysis technology, and finally preparing a TaxHfC matrix from the tantalum hafnium carbide by using the infiltration and pyrolysis technology. The Cf/C-TaxHfC composite material contains the C-TaxHfC transition matrix which is uniformly distributed, so that the thermal matching property of the first C matrix and the antioxidant TaxHfC matrix can be improved, and the mechanical properties of the composite material are enhanced; andthe Cf/C-TaxHfC composite material has a high TaxHfC content, so the oxidation resistance of the composite material can be obviously enhanced.

The invention relates to a supporting truss rod and a space truss structure. The problems that according to an existing space truss structure, the glue joint position is large in stress, and the bonding technology is poor in reliability are solved. The supporting truss rod comprises a truss rod body and connecting assemblies arranged at the two ends of the truss rod body. The truss rod body is a hollow rod formed through winding of carbon fiber materials. Each connecting assembly comprises an embedded piece and a metal bottom plate, wherein the material of the embedded piece is a carbon fiberenhanced SiC ceramic composite material and comprises a tubular embedded end and a connecting flange located at one end portion of the embedded end, the embedded end is embedded in the rod wall of thetruss rod body, the outer wall diameter of the embedded end is smaller than the outer diameter of the truss rod body, the inner wall diameter of the embedded end is larger than the inner diameter ofthe truss rod body, and the metal bottom plate is an annular metal plate adaptive to the connecting flange and is bonded and fixed to the connecting flange. The low-stress embedding manner is adopted,assembling stress and heat stress possibly generated during truss rod and metal piece bonding are relieved, and the truss structure assembling technology is simplified.

The invention discloses a solid oxide fuel cell gradient porosity anode and a solid oxide fuel cell. The solid oxide fuel cell gradient porosity anode comprises an anode function layer, an anode transition layer and an anode support layer which are connected in sequence from top to bottom. The opening porosity of the anode transition layer is greater than or equal to the opening porosity of the anode function layer. The opening porosity of the anode transition layer is smaller than or equal to the opening porosity of the anode support layer. The opening porosity of the anode function layer, the opening porosity of the anode transition layer and the opening porosity of the anode support layer are in gradient gradual decrease along a horizontal direction, or the opening porosity of the anodefunction layer, the opening porosity of the anode transition layer and the opening porosity of the anode support layer are in gradient gradual increase. The anode is characterized by relatively low activation polarization, concentration polarization and ohm polarization loss. The fuel cell is characterized by high output electrical property and high intensity.

The invention relates to a multilayer structure environmental barrier coating for a silicon carbide ceramic matrix composite material and a preparation method of the multilayer structure environmental barrier coating. The method comprises the following steps: carrying out sand blasting, polishing, ultrasonic cleaning and drying on the silicon carbide ceramic matrix composite material; sequentially preparing a bonding layer Si, a middle first layer Yb2O3-2SiO2, a middle second layer Yb2O3-SiO2 and an outer layer La2O3-2MgO-11Al2O3 on the surface of a pretreated silicon carbide ceramic matrix composite material by using an atmospheric plasma spraying method. The multilayer structure environmental barrier coating prepared by the method is compactly combined with the silicon carbide ceramic matrix composite material, can provide effective protection for the composite material in an oxygen-enriched high-temperature environment, and can be used at the temperature of 1350 DEG C for more than 500 hours.

The invention relates to a polyurethane elastic fiber with an ultrasonic bonding performance. The polyurethane elastic fiber contains a polymer A, wherein the polymer A contains a structural formula I and a structural formula II of the following units, wherein R in the formula I and the formula II is independently selected from hydrogen group, alkyl group, alkoxy group, hydroxyl group, halogen, amino group, amino group, nitro group or sulfonic acid group; in the formula I, a saturated or unsaturated aliphatic hydrocarbon group of C2-C18 is used; the mass of the structure in the formula I accounts for 1 to 25 percent of the total mass of the polymer A; the balance is the mass of the structure shown in the formula II, and the polymer A accounts for 0.5 to 15 percent of the mass of the polyurethane elastic fiber; and the thermal compatibility and the adhesiveness of the polyurethane elastic fiber and non-woven fabrics or other textiles are improved under the condition of an ultrasonic welding process and on the premise that no glue is used.