CN103276325B - Preparation method of anisotropic composite material for spaceborne radar antenna panel - Google Patents
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Abstract
The invention provides a preparation method of an anisotropic composite material for a spaceborne radar antenna panel, and relates to a preparation method of a composite material for a spaceborne radar antenna panel. In the prior art, the existing composite material for spaceborne radar antenna panels can not concurrently meet a transverse tensile strength and longitudinal tensile strength, and has characteristics of poor comprehensive mechanical property and not high density. A purpose of the present invention is to solve problems in the prior art. The preparation method comprises: coating an aluminum nitride suspension on the surface of fibers, fixing into a bundle, injecting an aluminum alloy solution to impregnate, and spraying a cooling liquid to rapidly cool to obtain the composite material. The anisotropic composite material has characteristics of high density, high longitudinal tensile strength maintaining, high longitudinal thermal conductivity maintaining, transverse tensile strength increase, transverse thermal conductivity increase, and excellent comprehensive performance, and can be used in the field of spaceborne radar antenna panels and preparations thereof.
Description
Technical field
The present invention relates to the preparation method of the matrix material being applied to spaceborne radar aerial panel.
Background technology
Spaceborne radar aerial panel needs to have high heat conductivility in particular directions and has the anisotropic material of excellent comprehensive mechanical property.Nineteen ninety, the standby P100/6061Al matrix material of DWA company and Lockheed Martin Inc. is applied to Hubble antenna by NASA, its longitudinal thermal conductivity can reach 320W/ (mK), longitudinal tensile strength can reach 900MPa, but the transverse strength of this material is lower, be generally below 100MPa, due to the development of field of aerospace now, the performance of this material can not meet the demand of spaceborne radar aerial panel now preferably.
Domestic at present also have part experts and scholars to attempt the simple mechanical property usually improving matrix material by adding the units such as Mg, Si, Ni in alloy matrix aluminum, but the raising be mostly confined to unidirectional mechanical property, if this kind of matrix material longitudinal tensile strength is higher, its transverse tensile strength is often very low, its longitudinal tensile strength is generally 700MPa ~ 1000MPa, and transverse strength is now generally below 100MPa, comprehensive mechanical property is poor.
Pitch-Based Graphite Fibers has high thermal conductivity, is applicable to being applied to the material high to heat conductivility requirement, and aluminium alloy is also widely used in the preparation of aerospace material with its feature such as low density, high strength.But the wettability of extreme difference makes diffusion-bonded between graphite fibre and aluminium alloy, the matrix material that the modes such as powder metallurgy are prepared is difficult to reach higher density, its density is generally 80% ~ 90%, and the reaction that graphite fibre and aluminium alloy at high temperature produce, also the matrix material heat conductivility making common Pressure Infiltration preparation technology obtain and mechanical property are difficult to reach requirement, although its density is also higher, but its comprehensive mechanical property is poor, its longitudinal thermal conductivity is 200W/ (mK) ~ 350W/ (mK), longitudinal tensile strength is about 600MPa ~ 900MPa, transverse strength is below 100MPa.
Summary of the invention
The present invention solves the existing matrix material being applied to spaceborne radar aerial panel can not take into account the not high problem of transverse tensile strength and longitudinal tensile strength, comprehensive mechanical property difference and density, and provides a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel.
A kind of anisotropic composite material being applied to spaceborne radar aerial panel of the present invention is that aluminum matrix alloy is made by massfraction by the Pitch-Based Graphite Fibers reinforcement of 60% ~ 80%, the aluminum nitride particle of 4% ~ 6% and surplus.
A kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel of the present invention carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 4% ~ 6% and the aluminum matrix alloy of surplus of 60% ~ 80% is taken by massfraction;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 60% ~ 80%, then be the Pitch-Based Graphite Fibers reinforcement surface that takes to step one of aluminium nitride suspension of 60% ~ 80% by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains fiber preform;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 800 ~ 1000 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 70MPa ~ 80MPa, pressurize 4min ~ 6min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material with steel die with speed of cooling be 40 DEG C/min ~ 60 DEG C/min cooling, the demoulding after temperature is down to 150 ~ 250 DEG C, obtains anisotropic composite material.
Method of the present invention adopts and first aluminum nitride particle is coated on Pitch-Based Graphite Fibers reinforcement surface, then the Pitch-Based Graphite Fibers reinforcement being coated with aluminium nitride is pressed into precast body, be injected with in the steel die of precast body after again aluminum matrix alloy being melted, that aluminium alloy solution remains at above precast body, by spraying cooling fluid, material is cooled fast with mould after compacting, obtain anisotropic matrix material, the anisotropic matrix material prepared by method of the present invention has high-compactness, density can reach 99%, while the high longitudinal tensile strength of maintenance and high longitudinal thermal conductivity, improve transverse tensile strength and transverse thermal conductivity, its longitudinal tensile strength can reach 1130MPa, longitudinal thermal conductivity can reach 320W/ (mK), transverse strength can reach 340MPa, transverse thermal conductivity can reach 210W/ (mK), excellent combination property, preparation method is simple, can be applicable to spaceborne radar aerial panel and preparation field thereof.
Embodiment
Embodiment one: the anisotropic composite material that present embodiment a kind of is applied to spaceborne radar aerial panel is that aluminum matrix alloy is made by massfraction by the Pitch-Based Graphite Fibers reinforcement of 60% ~ 80%, the aluminum nitride particle of 4% ~ 6% and surplus.
Anisotropic matrix material prepared by the method for present embodiment has high-compactness, density can reach 99%, while the high longitudinal tensile strength of maintenance and high longitudinal thermal conductivity, improve transverse tensile strength and transverse thermal conductivity, its longitudinal tensile strength can reach 1130MPa, it is longitudinal that thermal conductivity can reach 320W/ (mK), transverse strength can reach 340MPa, transverse thermal conductivity can reach 210W/ (mK), excellent combination property, preparation method is simple, can be applicable to spaceborne radar aerial panel and preparation field thereof.
Embodiment two: present embodiment and embodiment one are that aluminum matrix alloy make by massfraction by the Pitch-Based Graphite Fibers reinforcement of 75%, the aluminum nitride particle of 5% and surplus unlike: this matrix material.Other step and parameter identical with embodiment one.
Embodiment three: present embodiment and embodiment one or two are that porosity is less than 8%, the Pitch-Based Graphite Fibers reinforcement of diameter 5 μm ~ 10 μm unlike: described Pitch-Based Graphite Fibers reinforcement, described aluminum nitride particle particle diameter 4 μm ~ 6 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the massfraction of Mg is 15% ~ 20%.Other step and parameter identical with embodiment one or two.
Embodiment four: a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel of present embodiment carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 4% ~ 6% and the aluminum matrix alloy of surplus of 60% ~ 80% is taken by massfraction;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 60% ~ 80%, then be the Pitch-Based Graphite Fibers reinforcement surface that takes to step one of aluminium nitride suspension of 60% ~ 80% by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains fiber preform;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 800 ~ 1000 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 70MPa ~ 80MPa, pressurize 4min ~ 6min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material with steel die with speed of cooling be 40 DEG C/min ~ 60 DEG C/min cooling, the demoulding after temperature is down to 150 ~ 250 DEG C, obtains anisotropic composite material.
The method of present embodiment adopts and first aluminum nitride particle is coated on Pitch-Based Graphite Fibers reinforcement surface, then the Pitch-Based Graphite Fibers reinforcement being coated with aluminium nitride is pressed into precast body, be injected with in the steel die of precast body after again aluminum matrix alloy being melted, that aluminium alloy solution remains at above precast body, by spraying cooling fluid, material is cooled fast with mould after compacting, obtain anisotropic matrix material, the anisotropic matrix material prepared by the method for present embodiment has high-compactness, density can reach 99%, while the high longitudinal tensile strength of maintenance and high longitudinal thermal conductivity, improve transverse tensile strength and transverse thermal conductivity, its longitudinal tensile strength can reach 1130MPa, longitudinal thermal conductivity can reach 320W/ (mK), transverse strength can reach 340MPa, transverse thermal conductivity can reach 210W/ (mK), excellent combination property, preparation method is simple, can be applicable to spaceborne radar aerial panel and preparation field thereof.
Embodiment five: present embodiment and embodiment four unlike: take Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 4% ~ 6% and the aluminum matrix alloy of surplus of 60% ~ 80% in step one by massfraction.Other step and parameter identical with embodiment four.
Embodiment six: present embodiment and embodiment four or five unlike: take Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 5% and the aluminum matrix alloy of surplus of 75% in step one by massfraction.Other step and parameter identical with embodiment four or five.
Embodiment seven: one of present embodiment and embodiment four to six are that porosity is less than 8%, the Pitch-Based Graphite Fibers reinforcement of diameter 5 μm ~ 10 μm unlike: the Pitch-Based Graphite Fibers reinforcement described in step one, described aluminum nitride particle particle diameter 4 μm ~ 6 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the massfraction of Mg is 15% ~ 20%.Other step and parameter identical with one of embodiment four to six.
Embodiment eight: one of present embodiment and embodiment four to seven unlike: be configured to the aluminium nitride suspension that mass concentration is 70% ~ 75% in step 2.Other step and parameter identical with one of embodiment four to seven.
Embodiment nine: one of present embodiment and embodiment four to eight unlike: in step 4, the aluminum matrix alloy that step one takes is heated to 900 DEG C, under pressure is 75MPa, pressurize 5min.Other step and parameter identical with one of embodiment four to eight.
Embodiment ten: one of present embodiment and embodiment four to nine unlike: be that 50 DEG C/min cools with speed of cooling in step 5, the demoulding after temperature is down to 200 DEG C.Other step and parameter identical with one of embodiment four to nine.
With following verification experimental verification beneficial effect of the present invention:
Test one: a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 5% and the aluminum matrix alloy of surplus of 60% is taken by massfraction; Wherein Pitch-Based Graphite Fibers reinforcement porosity is 5%, mean diameter is the Pitch-Based Graphite Fibers reinforcement of 7 μm, described aluminum nitride particle median size is 5 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the mass percentage of Mg is 15%;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 70%, then be that the aluminium nitride suspension of 70% is to Pitch-Based Graphite Fibers reinforcement surface by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement, the massfraction of wherein said aqueous ethanolic solution is 60%;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains the fiber preform of 150mm × 20mm × 15mm;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 900 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 70MPa, pressurize 5min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material be that 50 DEG C/min cools with steel die with speed of cooling, temperature takes out material after being down to 200 DEG C, obtains anisotropic composite material.
Employing model is that the electronic universal drawing machine of Instron-5569 carries out comprehensive mechanical property detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its along fiber transverse tensile strength be 242MPa, be 870MPa along fiber longitudinal tensile strength, Young's modulus is 152GPa, comprehensive mechanical property is excellent.
Adopt model to be that the laser heat conducting instrument of LFA447 carries out thermal conductivity detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its be 152W (m along fiber transverse thermal conductivity
-1k
-1), be 320W (m along the longitudinal thermal conductivity of fiber
-1k
-1), comprehensive thermal conductance excellent performance.
The anisotropic composite material density using Archimedes drainage to measure this test to obtain, and anisotropic composite material density that this test obtains is 99.8% to utilize mixing rule to calculate.
Test two: a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 5% and the aluminum matrix alloy of surplus of 75% is taken by massfraction; Wherein Pitch-Based Graphite Fibers reinforcement porosity is 6%, mean diameter is the Pitch-Based Graphite Fibers reinforcement of 7 μm, described aluminum nitride particle median size is 4 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the mass percentage of Mg is 17%;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 75%, then be that the aluminium nitride suspension of 75% is to Pitch-Based Graphite Fibers reinforcement surface by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement, the massfraction of wherein said aqueous ethanolic solution is 60%;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains the fiber preform of 150mm × 20mm × 15mm;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 900 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 75MPa, pressurize 5min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material be that 50 DEG C/min cools with steel die with speed of cooling, temperature takes out material after being down to 200 DEG C, obtains anisotropic composite material.
Employing model is that the electronic universal drawing machine of Instron-5569 carries out comprehensive mechanical property detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its along fiber transverse tensile strength be 271MPa, be 930MPa along fiber longitudinal tensile strength, Young's modulus is 173GPa, comprehensive mechanical property is excellent.
Adopt model to be that the laser heat conducting instrument of LFA447 carries out thermal conductivity detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its be 168W (m along fiber transverse thermal conductivity
-1k
-1), be 287W (m along the longitudinal thermal conductivity of fiber
-1k
-1), comprehensive thermal conductance excellent performance.
The anisotropic composite material density using Archimedes drainage to measure this test to obtain, and anisotropic composite material density that this test obtains is 99.2% to utilize mixing rule to calculate.
Test three: a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 5% and the aluminum matrix alloy of surplus of 80% is taken by massfraction; Wherein Pitch-Based Graphite Fibers reinforcement porosity is 5%, mean diameter is the Pitch-Based Graphite Fibers reinforcement of 7 μm, described aluminum nitride particle median size is 5 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the mass percentage of Mg is 20%;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 75%, then be that the aluminium nitride suspension of 75% is to Pitch-Based Graphite Fibers reinforcement surface by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement, the massfraction of wherein said aqueous ethanolic solution is 60%;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains the fiber preform of 150mm × 20mm × 15mm;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 900 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 75MPa, pressurize 5min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material be that 50 DEG C/min cools with steel die with speed of cooling, temperature takes out material after being down to 200 DEG C, obtains anisotropic composite material.
Employing model is that the electronic universal drawing machine of Instron-5569 carries out comprehensive mechanical property detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its along fiber transverse tensile strength be 309MPa, be 1012MPa along fiber longitudinal tensile strength, Young's modulus is 173GPa, comprehensive mechanical property is excellent.
Adopt model to be that the laser heat conducting instrument of LFA447 carries out thermal conductivity detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its be 189W (m along fiber transverse thermal conductivity
-1k
-1), be 241W (m along the longitudinal thermal conductivity of fiber
-1k
-1), comprehensive thermal conductance excellent performance.
The anisotropic composite material density using Archimedes drainage to measure this test to obtain, and anisotropic composite material density that this test obtains is 99.0% to utilize mixing rule to calculate.
Test four: a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 5% and the aluminum matrix alloy of surplus of 80% is taken by massfraction; Wherein Pitch-Based Graphite Fibers reinforcement porosity is 6%, mean diameter is the Pitch-Based Graphite Fibers reinforcement of 6 μm, described aluminum nitride particle median size is 4 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the mass percentage of Mg is 20%;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 70%, then be that the aluminium nitride suspension of 70% is to Pitch-Based Graphite Fibers reinforcement surface by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement, the massfraction of wherein said aqueous ethanolic solution is 60%;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains the fiber preform of 150mm × 20mm × 15mm;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 900 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 80MPa, pressurize 5min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material be that 50 DEG C/min cools with steel die with speed of cooling, temperature takes out material after being down to 200 DEG C, obtains anisotropic composite material.
Employing model is that the electronic universal drawing machine of Instron-5569 carries out comprehensive mechanical property detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its along fiber transverse tensile strength be 340MPa, be 1130MPa along fiber longitudinal tensile strength, Young's modulus is 188GPa, comprehensive mechanical property is excellent.
Adopt model to be that the laser heat conducting instrument of LFA447 carries out thermal conductivity detection to the anisotropic composite material that this test obtains, obtain this test anisotropic composite material its be 210W (m along fiber transverse thermal conductivity
-1k
-1), be 265W (m along the longitudinal thermal conductivity of fiber
-1k
-1), comprehensive thermal conductance excellent performance.
The anisotropic composite material density using Archimedes drainage to measure this test to obtain, and anisotropic composite material density that this test obtains is 99.0% to utilize mixing rule to calculate.
Claims (6)
1. be applied to a preparation method for the anisotropic composite material of spaceborne radar aerial panel, it is characterized in that a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel carries out according to the following steps:
One, Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 4% ~ 6% and the aluminum matrix alloy of surplus of 60% ~ 80% is taken by massfraction;
Two, the aluminum nitride particle that step one takes is scattered in aqueous ethanolic solution, be configured to the aluminium nitride suspension that mass concentration is 60% ~ 80%, then be the Pitch-Based Graphite Fibers reinforcement surface that takes to step one of aluminium nitride suspension of 60% ~ 80% by mass concentration, air-dry under room temperature, obtain aluminium nitride coating Pitch-Based Graphite Fibers reinforcement;
Three, aluminium nitride coating Pitch-Based Graphite Fibers reinforcement step 2 obtained utilizes graphite jig to be fixed into tabular fibrous bundle, obtains fiber preform;
Four, first the fiber preform that step 3 obtains is transferred in steel die, and steel die inner cavity size and fiber preform fit like a glove, again the aluminum matrix alloy that step one takes is heated to 800 ~ 1000 DEG C, obtain aluminium alloy solution, then the aluminium alloy solution obtained is injected with in the steel die of fiber preform, under pressure is 70MPa ~ 80MPa, pressurize 4min ~ 6min, obtains matrix-precast body matrix material;
Five, in steel die, spray cooling fluid, make matrix-precast body matrix material with steel die with speed of cooling be 40 DEG C/min ~ 60 DEG C/min cooling, the demoulding after temperature is down to 150 ~ 250 DEG C, obtains anisotropic composite material.
2. a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel according to claim 1, is characterized in that the Pitch-Based Graphite Fibers reinforcement, the aluminum nitride particle of 5% and the aluminum matrix alloy of surplus that take 75% in step one by massfraction.
3. a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel according to claim 2, it is characterized in that the Pitch-Based Graphite Fibers reinforcement described in step one is that porosity is less than 8%, the Pitch-Based Graphite Fibers reinforcement of diameter 5 μm ~ 10 μm, described aluminum nitride particle particle diameter 4 μm ~ 6 μm, described aluminum matrix alloy is Al-Mg alloy, and in wherein said Al-Mg alloy, the massfraction of Mg is 15% ~ 20%.
4. a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel according to claim 2, is characterized in that being configured to the aluminium nitride suspension that mass concentration is 70% ~ 75% in step 2.
5. a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel according to claim 2, is characterized in that, in step 4, the aluminum matrix alloy that step one takes is heated to 900 DEG C, under pressure is 75MPa, and pressurize 5min.
6. a kind of preparation method being applied to the anisotropic composite material of spaceborne radar aerial panel according to claim 2, to is characterized in that in step 5 with speed of cooling being that 50 DEG C/min cools, the demoulding after temperature is down to 200 DEG C.
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| CN112952364A (en) * | 2021-01-27 | 2021-06-11 | 宇联星程(浙江)科技有限公司 | High-thermal-conductivity carbon fiber composite material antenna and preparation method thereof |
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| JPH01259137A (en) * | 1988-04-06 | 1989-10-16 | Mitsubishi Alum Co Ltd | Aluminum alloy composite material and aluminum alloy for composite material |
| CN1029926C (en) * | 1992-03-09 | 1995-10-04 | 中国人民解放军国防科学技术大学 | Carbon fibre with aluminium nitride coating and its preparation method |
| JP4340485B2 (en) * | 2003-07-07 | 2009-10-07 | サカイオーベックス株式会社 | Method for producing carbon fiber reinforced aluminum matrix composite |
| WO2005059194A1 (en) * | 2003-12-18 | 2005-06-30 | Shimane Prefectural Government | Metal base carbon fiber composite material and process for producing the same |
| CN102115857A (en) * | 2009-12-30 | 2011-07-06 | 常熟市东涛金属复合材料有限公司 | Metal composite material containing AlN (aluminum nitride) |
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Address after: Room 408-94, No.15 building (No.192 Mingyue Street), innovation and entrepreneurship square, science and technology innovation city, Harbin high tech Industrial Development Zone, Heilongjiang Province Patentee after: Harbin longzhuo new materials partnership (L.P.) Address before: Room 408-94, No.15 building (No.192 Mingyue Street), innovation and entrepreneurship square, science and technology innovation city, Harbin high tech Industrial Development Zone, Heilongjiang Province Patentee before: Harbin Lingsheng new material partnership (limited partnership) |
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Effective date of registration: 20210423 Address after: 150028 3rd floor, unit 1, 14955 Zhongyuan Avenue, building 9, innovation and entrepreneurship square, science and technology innovation city, hi tech Zone, Harbin, Heilongjiang Province Patentee after: HARBIN XIANGKE NEW MATERIAL Co.,Ltd. Address before: Room 408-94, No.15 building (No.192 Mingyue Street), innovation and entrepreneurship square, science and technology innovation city, Harbin high tech Industrial Development Zone, Heilongjiang Province Patentee before: Harbin longzhuo new materials partnership (L.P.) |
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