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Anisotropic composite material for spaceborne radar antenna panel, and preparation method thereof

A technology for composite materials and antenna panels, which is applied in the field of composite materials and its preparation, can solve the problems that composite materials cannot take into account both transverse tensile strength and longitudinal tensile strength, poor comprehensive mechanical properties, and low density, and achieve simple preparation methods Ease of operation, increase the transverse tensile strength, and improve the effect of transverse thermal conductivity

Active Publication Date: 2013-09-04
HARBIN XIANGKE NEW MATERIAL
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] In order to solve the problems that the existing composite materials used in spaceborne radar antenna panels cannot take into account the transverse tensile strength and longitudinal tensile strength, the comprehensive mechanical properties are poor and the density is not high, and the present invention provides a spaceborne radar antenna Anisotropic composite material for panel and method for its preparation

Method used

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specific Embodiment approach 1

[0014] Specific Embodiment 1: An anisotropic composite material applied to spaceborne radar antenna panels in this embodiment consists of 60% to 80% pitch-based graphite fiber reinforcement and 4% to 6% aluminum nitride by mass fraction The particles and balance are made of the base aluminum alloy.

[0015] The anisotropic composite material prepared by the method of this embodiment has high density, and the density can reach 99%. While maintaining high longitudinal tensile strength and high longitudinal thermal conductivity, the transverse tensile strength and transverse Thermal conductivity, its longitudinal tensile strength can reach 1130MPa, longitudinal thermal conductivity can reach 320W / (m·K), transverse strength can reach 340MPa, transverse thermal conductivity can reach 210W / (m·K), excellent comprehensive performance , the preparation method is simple and feasible, and can be applied to the field of spaceborne radar antenna panels and its preparation.

specific Embodiment approach 2

[0016] Specific embodiment 2: The difference between this embodiment and specific embodiment 1 is that the composite material is made of 75% pitch-based graphite fiber reinforcement, 5% aluminum nitride particles and the balance is made of matrix aluminum alloy according to the mass fraction . Other steps and parameters are the same as those in Embodiment 1.

specific Embodiment approach 3

[0017] Specific embodiment three: The difference between this embodiment and specific embodiment one or two is that the pitch-based graphite fiber reinforcement is a pitch-based graphite fiber reinforcement with a porosity of less than 8% and a diameter of 5 μm to 10 μm. The grain size of the aluminum nitride particles is 4 μm-6 μm, the base aluminum alloy is Al-Mg alloy, wherein the mass fraction of Mg in the Al-Mg alloy is 15%-20%. Other steps and parameters are the same as those in Embodiment 1 or Embodiment 2.

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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 [0001] The invention relates to a composite material applied to a spaceborne radar antenna panel and a preparation method thereof. Background technique [0002] Spaceborne radar antenna panels require anisotropic materials with extremely high thermal conductivity in specific directions and excellent comprehensive mechanical properties. In 1990, NASA applied the P100 / 6061A1 composite material prepared by DWA and Lockheed Martin to the Hubble Space Telescope antenna. Its longitudinal thermal conductivity can reach 320W / (m K), and its longitudinal tensile strength can reach 900MPa. However, The lateral strength of this material is low, generally below 100MPa. Due to the continuous development of the aerospace field, the performance of this material can no longer meet the needs of today's spaceborne radar antenna panels. [0003] At present, some domestic experts and scholars try to improve the mechanical properties of composite materials simply by adding Mg, Si...

Claims

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Application Information

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IPC IPC(8): C22C49/06C22C49/14C22C47/12C22C101/10
Inventor 陈国钦王晨充姜龙涛张强康鹏超修子扬芶华松武高辉
Owner HARBIN XIANGKE NEW MATERIAL
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